|
Class: Manned. Type: Spacecraft. Destination: Maximum Payload Orbit. Nation: USA. Agency: NASA. Manufacturer: McDonnell. Mercury was America's first man-in-space project. The capsule had to be as small as possible to match the payload capability of America's first ICBM, the Atlas, which would be used for orbital missions. The resulting design was less than a third of the weight of the Russian Vostok spacecraft, and more limited as a result. Setting the precedent for the later Gemini, Apollo, and Shuttle programs, any capsule configuration proposed by the contractors was acceptable as long as it was the one NASA's Langley facility, and in particular, Max Faget, had developed. McDonnell, at that time a renegade contractor of innovative Navy fighters that had a history of problems in service, received the contract.
While the Vostok was capable of missions of up to a week, the Mercury's final 24 hour mission was barely completed, with virtually all of the spacecraft's systems having broken down by the end. NASA felt lucky to have astronaut Cooper back alive (although the flight demonstrated a pinpoint re-entry was possible with no electrical power, no ECS, no guidance or instruments!) and cancelled Alan Shepard's desired week-long Mercury 10 flight. Unit Cost $: 5.500 million. Crew Size: 1. Design Life: 1.5 days. Orbital Storage: 1.00 days. Typical orbit: 157 km x 260 km at 33 degrees inclination. Length: 4.03 m (13.22 ft). Maximum Diameter: 1.89 m (6.20 ft). Habitable Volume: 1.70 m3. Mass: 1,355 kg (2,987 lb). RCS Impulse: 30 kgf-sec. Main Engine Thrust: 13.330 kN (2,997 lbf). Main Engine Propellants: Solid. Main Engine Propellants: 219 kg (482 lb). Spacecraft delta v: 98 m/s (321 ft/sec). Electrical System: Batteries. Electric System: 2.16 average kW. Electric System: 151.00 kWh. Associated Launch Vehicle: Atlas D, Redstone, Redstone Mercury. - Mercury Capsule. Other Designations: Capsule. Part of: Mercury. Class: Manned. Type: Spacecraft Module. Purpose: Reentry capsule.
Crew Size: 1. Length: 3.51 m (11.51 ft). Basic Diameter: 1.89 m (6.20 ft). Maximum Diameter: 1.89 m (6.20 ft). Habitable Volume: 1.70 m3. Mass: 1,118 kg (2,464 lb). Structure Mass: 340 kg (740 lb). Heat Shield Mass: 272 kg (599 lb). Reaction Control System: 40 kg (88 lb). Recovery Equipment: 60 kg (132 lb). Navigation Equipment: 40 kg (88 lb). Telemetry Equipment: 50 kg (110 lb). Electrical Equipment: 80 kg (176 lb). Communications Systems: 20 kg (44 lb). Crew Seats and Provisions: 80 kg (176 lb). Crew mass: 72 kg (158 lb). Environmental Control System: 50 kg (110 lb). RCS Coarse No x Thrust: 6 x 107 N. RCS Fine No x Thrust: 6 x 5 N. RCS Propellants: H2O2. RCS Isp: 220 sec. RCS Impulse: 30 kgf-sec. Main Engine Propellants: 14 kg (30 lb). Electrical System: Batteries. Electric System: 0.54 average kW. Electric System: 12.96 kWh.
Mercury Chronology
- 1957 November 1 - Faget presentation on manned orbital flight. -
A presentation on manned orbital flight was made by Maxime A. Faget. The concept included the use of existing ballistic missiles for propulsion, solid-fuel retrorockets for reentry initiation, and a nonlifting ballistic shape for the reentering capsule. This concept was considered to be the quickest and safest approach for initial manned flights into orbit.
- 1958 April 1 - Faget conceived contour couch to withstand the high g-loads. -
Maxime A. Faget and associates conceived the idea of using a contour couch to withstand the high g-loads attendant to acceleration and reentry forces of manned space flight. Fabrication of test-model contour couches was started in the Langley shops in May 1958, and the concept was proved feasible on July 30 of that same year.
- 1958 August 1 - Eisenhower assigns the manned space flight program to NASA. - Program: Mercury.
President Eisenhower assigned the responsibility for the development and execution of a manned space flight program to the National Aeronautics and Space Administration. However, NASA did not become operational until October 1, 1958.
- 1958 August 8 - Project Adam -
A memorandum from the Secretary of the Army to the Secretary of Defense recommended Project Adam for a manned space flight program. This plan proposed a ballistic suborbital flight using existing Redstone hardware as a national political-psychological demonstration. This memo proposed that funds in the amount of $9 million and $2.5 million for fiscal years 1959 and 1960, respectively, be approved for program execution.
- 1958 December 11 - Eleven firms submitted proposals for the development of Mercury manned spacecraft. - Program: Mercury.
These were AVCO, Chance-Vought, Convair, Douglas, Grumman, Lockheed, Martin, McDonnell, North American, Northrop, and Republic. In addition, Winzen Research Laboratories submitted an incomplete proposal.
- 1958 February 27 - NACA estimated weights for manned reentry vehicle too low. -
Experience with the X-15 design indicated that many of the weight figures advanced by the Langley Aeronautical Laboratory for the drag or lift configurations of the reentry vehicle (later to become the Mercury spacecraft) were too low, according to Walter C. Williams, Chief of the NACA High-Speed Flight Station. Weights of auxiliary-power fuel, research instrumentation, and cockpit equipment as set by Langley were too low in terms of X-15 experience. Williams stated the total weight should be 2,300 pounds for the drag configuration and 2,500 pounds for the lifting configuration.
- 1958 January 29 - Conference reviews concepts for manned orbital vehicles. - Program: Mercury.
A conference was held at Wright-Patterson Air Force Base, Ohio, to review concepts for manned orbital vehicles. The NACA informally presented two concepts then under study at Langley Aeronautical Laboratory: the one proposed by Maxime A. Faget involved a ballistic, high-drag capsule with heat shield on which the pilot lies prone during reentry, with reentry being accomplished by reverse thrust at the apogee of the elliptical orbit involving a deceleration load of about 8g, and proceeding to impact by a parachute landing; the other Langley proposal called for the development of a triangular planform vehicle with a flat bottom having some lift during reentry. At this same meeting there were several Air Force contractor presentations. These were as follows: Northrop, boost-glide buildup to orbital speed; Martin, zero-lift vehicle launched by a Titan with controlled flight estimated to be possible by mid-1961; McDonnell, ballistic vehicle resembling Faget's proposal, weighing 2,400 pounds and launched by an Atlas with a Polaris second stage; Lockheed, a 20 degree semiapex angle cone with a hemispherical tip of 1-foot radius, pilot in sitting position facing rearward, to be launched by an Atlas-Hustler combination; Convair reviewed a previous proposal for a large-scale manned space station, but stated a minimum vehicle - a 1,000-pound sphere - could be launched by an Atlas within a year; Aeronutronics, cone-shaped vehicle with spherical tip of 1-foot radius, with man enclosed in sphere inside vehicle and rotated to line the pilot up with accelerations, and launched by one of several two-stage vehicles; Republic, the Ferri sled vehicle, a 4,000 pound, triangular plan with a two-foot diameter tube running continuous around the leading and trailing edge and serving as a fuel tank for final-stage, solid-propellant rockets located in each wing tip, with a man in small compartment on top side, and with a heat-transfer ring in the front of the nose for a glide reentry of 3,600 miles per hour with pilot ejecting from capsule and parachuting down, and the launch vehicle comprising three stages (also see July 31, 1958 entry); AVCO, a 1,500-pound vehicle sphere launched by a Titan, equipped with a stainless-steel-cloth parachute whose diameter would be controlled by compessed air bellows and which would orient the vehicle in orbit, provide deceleration for reentry, and control drag during reentry; Bell, reviewed proposals for boost-glide vehicles, but considered briefly a minimum vehicle, spherical in shape, weighing about 3,000 pounds; Goodyear, a spherical vehicle with a rearward facing tail cone and ablative surface, with flaps deflected from the cone during reentry for increased drag and control, and launched by an Atlas or a Titan plus a Vanguard second stage; North American, extend the X-15 program by using the X-15 with a three-stage launch vehicle to achieve a single orbit with an apogee of 400,000 feet and a perigee of 250,000, range about 500 to 600 miles and landing in the Gulf of Mexico, and the pilot ejecting and landing by parachute with the aircraft being lost.
- 1958 January 31 - USAF proposes NACA participation in the Air Force effort in the manned ballistic rocket program. - Program: Mercury.
Lieutenant General Donald Putt, Air Force Director of Research and Development, sent a letter to Dr. Hugh Dryden, Director of NACA, inviting NACA participation in the Air Force effort in the manned ballistic rocket program. Dr. Dryden informed the Air Force that NACA was preparing manned spacecraft designs for submission in March 1958.
- 1958 July 15 - McDonnell manned orbital spacecraft concept. -
Cook Electric Company submitted a proposal to the McDonnell Aircraft Corporation as a part of a preliminary study and design effort by McDonnell for a manned satellite. McDonnell, prior to being awarded the Mercury prime development contract in February 1959, spent 11 months under a company research budget working on a manned orbital spacecraft concept.
- 1958 July 18 - NASA heritage from NACA. -
In a memorandum to Dr. James R. Killian, Jr., Special Assistant to the President for Science and Technology, Dr. Hugh L. Dryden, Director of NACA, pointed out that NASA would inherit from NACA a rich technical background, competence, and leadership in driving toward the objective of a manned satellite program. For years NACA groups had been involved in research on such items as stabilization of ultra-high speed vehicles, provision of suitable controls, high temperature structural designs, and all the problems of reentry. In fact, a part of this work had been directed specifically toward the problem of designing a manned satellite. Also, the X-15 program had provided much experience in human factors applicable to the orbital flight of man. Therefore, Dr. Dryden concluded, in consonance with the intent of the Space Act of 1958, the assignment of the program to the NACA would be consistent.
- 1958 July 30 - Test subject withstood a 20g load on the centrifuge using Langley contour couch. -
By using the development model of the Mercury contour couch designed by Maxime A. Faget and associates, Carter C. Collins withstood a 20g load on the centrifuge at Johnsville, Pennsylvania. This test proved that the reentry accelerations of manned space flight could be withstood.
- 1958 July 31 - Republic Aviation man-in-space studies. -
Republic Aviation representatives briefed NACA Headquarters personnel on the man-in-space studies in which the company had been engaged since the first of the year. They envisioned a four-stage solid launch vehicle system and a lifting reentry vehicle, which was termed a sled. The vehicle was to be of triangular shape with a 75 degree leading-edge sweep. Aerodynamic and reaction controls would be available to the pilot. For the launch vehicle, Republic proposed a Minuteman first stage, a Polaris first stage, a Minuteman upper stage, and a Jumbo rocket fourth stage. Other details relative to reentry and recovery were included in the briefing.
- 1958 June 1 - Preliminary specifications of the first manned satellite vehicle. -
Preliminary specifications of the first manned satellite vehicle were drafted by Langley Aeronautical Laboratory personnel under the supervision of Maxime Faget and Charles W. Mathews. After a number of revisions and additions, these specifications were used for the Project Mercury spacecraft contract with McDonnell Aircraft Corporation. A working group of representatives from the Langley Aeronautical Laboratory and the Lewis Flight Propulsion Laboratory was formed for the purpose of outlining a manned satellite program.
- 1958 June 5 - Advanced Research Projects Agency manned space project. - Program: Mercury.
After serving as a liaison officer of NACA and as a participating member of an Advanced Research Projects Agency panel, Maxime A. Faget reported to Dr. Hugh Dryden on resulting studies and attending recommendations on the subject of manned space flight. He stated that the Advanced Research Projects Agency panel was quite aware that the responsibility for such a program might be placed with the soon-to-be-created civilian space agency, although they recommended program management be placed with the Air Force under executive control of NACA and the Advanced Research Projects Agency. The panel also recommended that the program start immediately even though the specific manager was, as yet, unassigned. Several of the proposals put forth by the panel on the proposed development were rather similar to the subsequent evolvement. The system suggested by the Advanced Research Projects Agency was to be based on the use of the Atlas launch vehicle with the Atlas-Sentry system serving as backup; retrorockets were to be used to initiate the return from orbit; the spacecraft was to be nonlifting, ballistic type, and the crew was to be selected from qualified volunteers in the Army, Navy, and Air Force.
- 1958 March 1 - NACA design concepts to achieve manned orbital flights. -
Robert R. Gilruth, Clotaire Wood, and Hartley A. Soule of NACA transmitted a document to the Air Research and Development Command, which listed the design concepts NACA believed should be followed to achieve manned orbital flights at the earliest possible date. These were: (1) design and develop a simple ballistic vehicle, (2) use existing intercontinental ballistic missile propulsion systems, and (3) use the heat sink method for reentry from orbital conditions.
- 1958 March 10 - MISS Working Conference - Program: Mercury.
A working conference in support of the Air Force 'Man-in-Space Soonest' (MISS) was held at the Air Force Ballistic Missile Division in Los Angeles, California. General Bernard Schriever, opening the conference, stated that events were moving faster than expected. By this statement he meant that Roy Johnson, the new head of the Advanced Research Projects Agency, had asked the Air Force to report to him on its approach to putting a man in space soonest. Johnson indicated that the Air Force would be assigned the task, and the purpose of the conference was to produce a rough-draft proposal. At that time the Air Force concept consisted of three stages: a high-drag, no-lift, blunt-shaped spacecraft to get man in space soonest, with landing to be accomplished by a parachute; a more sophisticated approach by possibly employing a lifting vehicle or one with a modified drag; and a long-range program that might end in a space station or a trip to the moon.
- 1958 March 10 - NACA manned satellite configurations -
Reports were made on recoverable manned satellite configurations being considered by NACA. One involved a blunt, high-drag, zero-lift vehicle that would depend on a parachute landing for final deceleration. Another was a winged vehicle that would glide to a landing after reentering the atmosphere. The third proposal involved features of each of the above. Besides the configuration studies, significant reports were completed relative to motion and heating, stabilization, and attitude control.
- 1958 March 12 - The NACA staff completed a program outline for conducting the manned satellite program. - Program: Mercury.
At that time, NACA was already actively engaged in research and study of several phases. For example, in the basic studies category effort had been expended on the study of orbits and orbit control, space physical characteristics, configuration studies, propulsion system research, human factors, structures and materials, satellite instrumentation, range requirements, and noise and vibration during reentry and exit. In addition, NACA outlined the complete program covering full-scale studies of mockups, simulators, and detail designs; full-scale vertical and orbiting flights involving unmanned, animal, and manned flights and recovery; and exploitation of the program to increase the payloads. As to the design concepts for such a program, NACA believed that the Atlas launch vehicle was adequate to meet launch-vehicle requirements for manned orbital flights; that retrograde and vernier controllable thrust could be used for orbital control; that heat-sink or lighter material could be used against reentry heating; that guidance should be ground programed with provisions for the pilot to make final adjustments; that recovery should be accomplished at sea with parachutes used for letdown; that a network of radar stations should be established to furnish continuous tracking; and that launchings be made from Cape Canaveral. It was estimated that with a simple ballistic shape accelerations would be within tolerable limits for the pilot. Temperature control, oxygen supply, noise, and vibration were considered engineering development problems, which could be solved without any special breakthroughs.
- 1958 March 18 - Preliminary Studies of Manned Satellites, Wingless Configuration, Non-Lifting -
An NACA report was published entitled, 'Preliminary Studies of Manned Satellites, Wingless Configuration, Non-Lifting,' by Maxime A. Faget, Benjamine Garland, and James J. Buglia. Later this document became the basic working paper for the Project Mercury development program, and was reissued as NASA Technical Note D-1254, March 1962.
- 1958 March 18 - NACA Conference on High-Speed Aerodynamics -
An 'NACA Conference on High-Speed Aerodynamics' was held at the Ames Aeronautical Laboratory, Moffett Field, California, to acquaint the military services and industrial contractors interested in aerospace projects with the results of recent research conducted by the NACA laboratories on the subject of space flight. The conference was attended by more than 500 representatives from the NACA, industry, the military services, and other appropriate government agencies. Some 46 technical papers were presented by NACA personnel, and included specific proposals for manned space flight vehicle projects. One of these was presented by Maxime A. Faget. Other papers within the category of manned orbital satellites included: 'Preliminary Studies of Manned Satellites, Wingless Configuration, Lifting Body' by Thomas J. Wong and others; 'Preliminary Studies of Manned Satellites, Winged Configurations' by John V. Becker; 'Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations' by Jim A. Penland and William O. Armstrong; and 'Structural Design Considerations for Boost-Glide and Orbital Reentry Vehicles' by William A. Brooks and others.
- 1958 November 1 - Study on spacecraft recovery operations. -
Study was started on spacecraft recovery operations. During this study period, it was learned that the retrieving operation could be very difficult; but with properly designed equipment, helicopter pickup could be used and appeared to be the most favorable method.
- 1958 November 1 - Mercury scale model transonic tests. - Program: Mercury.
A scale model of the Mercury spacecraft (without escape tower), oriented for the reentry phase, was tested at transonic Mach numbers in a 1-foot transonic test tunnel at the Arnold Engineering Development Center, Tullahoma, Tennessee.
- 1958 November 14 - Specifications for Mercury issued. - Program: Mercury.
Specifications for the manned spacecraft (Specification Number S-6) were issued, and final copies were mailed on November 17, 1958, to 20 firms which had indicated a desire to be considered as bidders.
- 1958 November 5 - Space Task Group (STG) organized to implement the manned satellite project - Program: Apollo.
The Space Task Group (STG) was officially organized at Langley Field, Va., to implement the manned satellite project (later Project Mercury), NASA Administrator T. Keith Glennan had approved the formation of the Group, which had been working together for some months, on October 7. Its members were designated on November 3 by Robert R. Gilruth, Project Manager, and authorization was given by Floyd L. Thompson, Acting Director of Langley Research Center. STG would report directly to NASA Headquarters.
- 1958 November 7 - Contractor briefing on the Mercury manned spacecraft - Program: Mercury.
A contractor briefing, attended by some 40 prospective bidders on the manned spacecraft, was held at the Langley Research Center. More detailed specifications were then prepared and distributed to about 20 manufacturers who had stated an intention to bid on the project.
- 1958 October 1 - Drop tests of full-scale Mercury capsules started -
Drop tests of full-scale capsules from a C-130 airplane were started to check parachute deployment and spacecraft stability. Preliminary drops of the parachute system were made from a NASA helicopter at West Point, Virginia. These drops involved the use of a concrete-filled drum attached to an operating canister system. The purpose of this phase was to demonstrate the adequacy of the mechanical system of deploying the parachutes. Subsequently, the drops were made by the C-130's at Pope Field, North Carolina, from low levels to perfect a means of extracting the spacecraft from the aircraft. Full-scale spacecraft and operating parachutes were used in these drops, and all operational features of the drop-test program were worked out. The next phase was the research and development drops offshore of Wallops Island, Virginia, and the objectives here were as follows: to study the stability of the spacecraft during free fall and with parachute support; to study the shock input to the spacecraft by parachute deployment; and to study and develop retrieving operations.
- 1958 October 3 - Plans of the Mercury manned satellite project presented to Advanced Research Projects Agency. - Program: Mercury.
Studies and plans of the manned satellite project were presented to Advanced Research Projects Agency on October 3 and to Dr. T. Keith Glennan, NASA Administrator, on October 7. On October 7, 1958, Dr. Glennan approved the project by saying, in effect, 'Let's get on with it.'
- 1958 October 7 - Study of Mercury reentry methods. -
Personnel from the Space Task Group involved in the study of reentry methods visited the Air Force Wright Air Development Center, Dayton, Ohio, for the purpose of preparing test specimens. Along with individuals from the center and the Air Force Ballistic Missile Division, the group then met at the Chicago Midway Laboratories, Chicago, Illinois, to investigate various ablation methods of reentry. Concurrently, these same methods were being investigated at high-temperature test facilities at Langley.
- 1958 October 7 - Project Mercury organized. - Program: Mercury.
NASA formally organized Project Mercury to: (1) place manned space capsule in orbital flight around the earth; (2) investigate man's reactions to and capabilities in this environment; and (3) recover capsule and pilot safely. A NASA Space Task Group organized at Langley Research Center drew up specifications for the Mercury capsule, based on studies by the National Advisory Committee for Aeronautics during the preceding 12 months, and on discussions with the Air Force which had been conducting related studies.
- 1958 September 17 - NASA/ARPA Manned Satellite Panel -
A joint National Aeronautics and Space Administration/Advanced Research Projects Agency Manned Satellite Panel was formed. This panel, with the aid of technical studies prepared by the Langley and Lewis Research Centers and assistance from the military services, drafted specific plans for a program of research leading to manned space flight.
- 1959 April 1 - Mercury parachute design unsafe for operation. - Program: Mercury.
In the recovery landing system, the extended-skirt main parachute was found to be unsafe for operation at altitudes of 10,000 feet and was replaced by a 'ring-sail' parachute of similar size. This decision was made after a drop when the main parachute failed to open and assumed a 'squidding' condition. Although little damage was sustained by the spacecraft on water impact, parachute experts decided that the ring-sail configuration should be adopted, and the air drop spacecraft were fitted.
- 1959 April 12 - Mercury impact tests - Program: Mercury.
Tests were in progress at Langley in which an aluminium honeycomb structure was used partially to absorb the spacecraft impact load. Robert R. Gilruth, Project Mercury Director, had stated his belief of this requirement on January 16, 1959.
- 1959 April 12 - Space Task Group conducted the second full-scale Mercury beach abort test on Wallops Island. - Program: Mercury.
A deliberate thrust misalignment of 1 inch was programed into the escape combination. Lift-off was effected cleanly, and a slow pitch started during the burning of the escape rocket motor. The tower separated as scheduled and the drogue and main parachutes deployed as planned. The test was fully successful.
- 1959 April 13 - Mercury small-scale escape-tower combinations launched - Program: Mercury.
Two small-scale spacecraft escape-tower combinations were launched successfully at Wallops Island. On the next day a full-scale spacecraft escape system was launched. The complete sequence of events - escape system firing, escape tower jettisoning, parachute deployment, landing, and helicopter recovery - was satisfactory.
- 1959 April 16 - Plans for Mercury Big Joe I reentry spacecraft test vehicle. - Program: Mercury.
Space Task Group, Langley Research Center, and Lewis Research Center personnel met to discuss development plans regarding construction and instrumentation of Big Joe Number I reentry spacecraft test vehicle. During the course of this meeting, milestone objectives of the work to be accomplished were drafted.
- 1959 April 2 - Seven astronauts selected for Mercury project. - Program: Mercury.
Seven astronauts were selected for Project Mercury after a series of the most rigorous physical and mental tests ever given to U.S. test pilots. Chosen from a field of 110 candidates, the finalists were all qualified test pilots: Capts. Leroy G. Cooper, Jr., Virgil I. Grissom, and Donald K. Slayton, (USAF); Lt. Malcolm S. Carpenter, Lt. Comdr. Alan B. Shepard, Jr., and Lt. Comdr. Watler M. Schirra, Jr. (USN); and Lt. Col. John H. Glenn (USMC).
- 1959 April 2 - Project Mercury animal payload program. - Program: Mercury. Launch Vehicle: Little Joe.
NASA and the military services conducted meetings to draft final plans for the Project Mercury animal payload program. The animal program was planned to cover nine flights, involving Little Joe, Redstone, Jupiter, and Atlas launch vehicles.
- 1959 April 22 - Tower configuration best escape system for the Mercury spacecraft. - Program: Mercury.
In a meeting at Langley, NASA officials concluded that the tower configuration was the best escape system for the Mercury spacecraft and development would proceed using this concept. However, limited studies of alternate configurations would continue.
- 1959 April 27 - Project Mercury was accorded the DX priority procurement rating. - Program: Mercury.
- 1959 April 27 - Mercury search and rescue procedures developed. - Program: Mercury.
Meeting of DOD working group on Project Mercury search and recovery operations was held at Patrick Air Force Base, with major emphasis placed on the first two ballistic Atlas shots, and command relationships.
- 1959 April 9 - Escape configurations for Mercury spacecraft - Program: Mercury.
Investigations of two escape configurations for Mercury spacecraft were conducted in a 16-foot transonic circuit at the Arnold Engineering Development Center, Tullahoma, Tennessee, for determination of static stability and drag characteristics of the configurations.
- 1959 August 1 - Qualification tests completed for the Mercury main parachute. - Program: Mercury.
Qualification tests, which were started in May 1959, were completed for the 63-foot ringsail, main parachute. After this, complete parachute landing tests were initiated by spacecraft drops from a C-130 at Salton Sea, California.
- 1959 August 21 - Mercury LJ-1 - Program: Mercury. Launch Site: Wallops Island. Launch Vehicle: Little Joe. FAILURE: Failure. Apogee: 0.61 km (0.38 mi).
During the countdown of the first programed Little Joe launching (LJ-1 beach abort test) at Wallops Island, the escape rocket fired prematurely 31 minutes before the scheduled launch. The spacecraft rose to an altitude of 2,000 feet and landed about 2,000 feet from the launch site. Premature firing was caused by a faulty escape circuit.
- 1959 August 25 - Testing completed on Mercury drogue parachute effectiveness - Program: Mercury.
Testing was completed to check the effectiveness of the drogue parachute as a stabilizing device. The drogue parachute was fully qualified for deployment at speeds up to Mach 1.5 and altitudes of up to 70,000 feet. Ordinarily, during the operational phase of Project Mercury the drogue parachute was deployed at 40,000 feet, so the component well met operational requirements.
- 1959 August 4 - Tests were started to check the operation of the redesigned Mercury drogue parachute - Program: Mercury.
- 1959 December 31 - NASA funds in support of Project Mercury - Program: Mercury.
At the end of the year, NASA funds in support of Project Mercury had been obligated to the listed organizations as follows: Air Force Ballistic Missile Division, NASA Order HS-36, Atlas launch vehicles, $22,830,000; Army Ordnance Missile Command, NASA Order HS-44, Redstone launch vehicles, $16,060,000; and McDonnell Aircraft Corporation, NASA Order 5-59, Mercury spacecraft, $49,407,540.
- 1959 December 31 - McDonnell exceeds one million labor-hours on Mercury. - Program: Mercury.
Since being awarded the Mercury contract, McDonnell had expended 942,818 man-hours in engineering; 190,731 man-hours in tooling; and 373,232 man-hours in production.
- 1959 December 4 - Mercury Little Joe 2 (LJ-2) - Program: Mercury. Launch Site: Wallops Island.
LJ-2 was launched from Wallops Island to determine the motions of the spacecraft escape tower combination during a high-altitude abort, entry dynamics without a control system, physiological effects of acceleration on a small primate, operation of the drogue parachute, and effectiveness of the recovery operation. Telemetry was set up to record some 80 bits of information on the flight. The abort sequence was initiated by timers after 59 seconds of elapsed flight time at an altitude of about 96,000 feet and a speed of Mach 5.5. Escape motor firing occurred as planned and the spacecraft was whisked away at a speed of about Mach 6 to an apogee of 53.03 statute miles. All other sequences operated as planned, and spacecraft recovery was effected in about 2 hours from lift-off. The primate passenger, 'Sam,' an American-born rhesus monkey, withstood the trip and the recovery in good condition. All objectives of the mission were met.
- 1959 December 7 - Tenney Engineering to construct Mercury altitude test chamber in Hanger S at Cape Canaveral. - Program: Mercury.
Tenney Engineering Corporation was chosen by the Space Task Group to construct the Mercury altitude test chamber in Hanger S at Cape Canaveral. When completed, altitude pressure would simulate 225,000 feet. The chamber, a vertical cylinder with domed ends, was 12 feet in diameter and 14 feet high. The chamber was designed to allow a partial spacecraft functional check in a near-vacuum environment.
- 1959 February 10 - Wiind tunnel tests of Project Mercury configuration models were started. - Program: Mercury.
By the end of the year, over 70 different models had been tested by facilities at the Air Force's Arnold Engineering Development Center and the NASA Langley, Ames, and Lewis Research Centers.
- 1959 February 11 - Redstone and Jupiter flight phases of Project Mercury. - Program: Mercury. Launch Vehicle: Redstone, Jupiter.
Space Task Group and Army Ballistic Missile Agency personnel met at Huntsville, Alabama, to discuss Redstone and Jupiter flight phases of Project Mercury. During the course of the meeting the following points became firm: (1) Space Task Group was the overall manager and technical director of this phase of the program, (2) ABMA was responsible for the launch vehicle until spacecraft separation, (3) ABMA was responsible for the Redstone launch vehicle recovery (this phase of the program was later eliminated since benefits from recovering the launch vehicle would have been insignificant), (4) Space Task Group was responsible for the spacecraft flight after separation, (5) McDonnell was responsible for the adapters for the Mercury-Redstone configuration, and (6) ABMA would build adapters for the Mercury-Jupiter configuration. Because many points could only be settled by detailed design studies, it was decided to establish several working panels for later meetings.
- 1959 February 17 - Program for wind tunnel and free-flight tests in support of Project Mercury. - Program: Mercury.
Members of the Space Task Group, Langley, Ames, McDonnell and NASA Headquarters drafted a coordinated program for wind tunnel and free-flight tests in support of Project Mercury.
- 1959 February 24 - Mercury-Redstone-Jupiter trajectory, aerodynamics, and flight loads - Program: Mercury. Launch Vehicle: Redstone, Jupiter.
Mercury-Redstone-Jupiter Study Panel Number IV (choice of trajectory, aerodynamics, and flight loads) met at Redstone Arsenal. Subjects studied included pilot safety, simulation of entry from orbit, length of zero-g time, missile stability and aerodynamics, ascent accelerations, and range. This group reconvened on March 13, 1959.
- 1959 February 26 - AEDC facilities to perform tests on scale models of the Mercury spacecraft. - Program: Mercury.
Space Task Group and Langley Research Center personnel visited the Arnold Engineering Development Center, Tullahoma, Tennessee, to ascertain if the AEDC facilities were equipped to perform tests on scale models of the Mercury spacecraft and to arrange a testing schedule.
- 1959 February 6 - Formal contract for 12 Mercury spacecraft with McDonnell. - Program: Mercury.
Following industry-wide competition, a formal contract for research and development of the Mercury spacecraft was negotiated with the McDonnell Aircraft Corporation. The contract called for design and construction of 12 Mercury spacecraft, but it did not include details on changes and ground support equipment which were to be negotiated as the project developed. Later, orders were placed with the company for eight additional spacecraft, two procedural trainers, an environmental trainer, and seven checkout trainers. McDonnell had been engaged in studying the development of a manned spacecraft since the NACA presentation in mid-March of 1958.
- 1959 January 1 - Honeywell named subcontractor for the Mercury stabilization system. - Program: Mercury.
McDonnell, as prime contractor, selected Minneapolis-Honeywell as subcontractor for the Mercury stabilization system. At that time, other subcontractors were under consideration for the fabrication of various components: Bell Aircraft Rockets Division, reaction control system; and General Electric, Barnes Instruments, and Detroit Controls were being considered for fabrication of the horizon scanner. Later Bell and Barnes were awarded contracts for respective components.
- 1959 January 1 - Balloon flights planned for Mercury. - Program: Mercury.
Balloon flights were planned for high-altitude qualification tests of the complete spacecraft, including all instrumentation, retrorockets, drogue parachute system, and recovery. Later balloon flights would be manned to provide as much as 24 hours of training followed by recovery at sea. The Space Task Group made surveys of organizations experienced in the balloon field and recommended that the Air Force Cambridge Research Center be given responsibilities for designing, contracting, and conducting the balloon program.
- 1959 January 1 - Arnold Engineering Development Center Project Mercury work. - Program: Mercury.
Investigations were conducted at the Arnold Engineering Development Center, Tullahoma, Tennessee, in support of Project Mercury. Models of the Mercury spacecraft were tested at speeds of Mach 8, 16, and 20 to investigate stability, heat transfer, and pressure distribution of Mercury components.
- 1959 January 16 - Mercury design details negotiated. - Program: Mercury.
During a meeting of the Space Task Group, it was decided to negotiate with McDonnell for design of spacecraft that could be fitted with either a beryllium heat sink or an ablation heat shield. Robert R. Gilruth, the project director, considered that for safety purposes, both should be used. He also felt that the recovery landing bag should be replaced by a honeycombed crushable structure. At this same meeting, a tentative decision was also made that design, development, and contract responsibilities for the Mercury tracking network would be assigned to the Langley Research Center.
- 1959 January 6 - Mercury spacecraft heat protection. -
A meeting was held at the National Aeronautics and Space Administration Headquarters to discuss the method for spacecraft heat protection. Two plans were considered: beryllium heat sink and ablation. Based on this meeting a decision was made to modify the spacecraft structure in order to accomodate interchangeably ablation heat shields and beryllium heat sinks , and orders were placed for 12 and 6, respectively. The material chosen for the ablation heat was Fiberglas bonded with a modified phenolic resin. This material was found to have good structural properties even after being subjected to reentry heating.
- 1959 January 9 - McDonnell selected to produce the Mercury spacecraft. - Program: Mercury.
The Source Selection Board at NASA Headquarters composed of Abe Silverstein, Ralph Cushman, George Low, Walter Schier, DeMarquis Wyatt, and Charles Zimmerman, completed their findings and reported to Dr. T. Keith Glennan, the Administrator. McDonnell Aircraft Corporation was selected as the prime contractor to develop and produce the Mercury spacecraft.
- 1959 July 13 - Spacecraft horizon scanner qualification tests were started. - Program: Mercury.
- 1959 July 21 - Cape Canaveral. Building S for Project Mercury support - Program: Mercury.
Alterations to Building 'S' at Cape Canaveral for Project Mercury support were discussed in a meeting at Cape Canaveral. A target date of December 1, 1959, was set for project completion. Therefore, this meant that Vanguard activities would have to be phased out of the building.
- 1959 July 28 - Second beach abort test leading to the Mercury Little Joe test series. - Program: Mercury. Launch Vehicle: Little Joe.
A boilerplate spacecraft, instrumented to measure sound pressure level and vibration, was launched in the second beach abort test leading to the Little Joe test series. The purpose of the instrumentation was to obtain measurement of the vibration and sound environment encountered on the capsule during the firing of the Grand Central abort rocket. Memo, Charles A. Hardesty to NASA Langley IRD files, subject: Sound Measurements on the Second Beach Abort Test on the Little Joe Capsule, Oct. 9, 1959.
- 1959 July 6 - Mercury spacecraft energetic particles research. - Program: Mercury.
As a result of a discussion between Maxime A. Faget, Space Task Group, and John E. Naugle, Space Science Division, NASA Headquarters, it was concluded that there were several important scientific experiments in the field of energetic particles research that could be performed by placing packets of emulsion within the Mercury spacecraft. Work was started to determine a suitable packet location, along with other details associated with conducting such experiments.
- 1959 June 1 - Northrop to fabricate the landing system for Mercury. - Program: Mercury.
McDonnell selected Northrop as the subcontractor to design and fabricate the landing system for Project Mercury. Northrop technology for landing and recovery systems dated back to 1943 when that company developed the first parachute recovery system for pilotless aircraft. For Project Mercury, Northrop developed the 63-foot ring-sail main parachute.
- 1959 June 14 - Mercury spacecraft being designed to withstand 149 decibels. - Program: Mercury.
A visit was made to McDonnell and it was learned that the Mercury spacecraft was being designed structurally to withstand 149 decibels overall noise level. McDonnell, however, anticipated that the actual maximum level would not be above 128 decibels. Space Task Group personnel felt that even the 128 decibels were too high for pilot comfort, and extensive research toward the resolution of this matter was started.
- 1959 June 19 - Mercury Capsule Review Board established - Program: Mercury.
A Mercury Capsule Review Board was established to review, at regular intervals, action taken by the Capsule Coordination Office. Paul E. Purser was appointed chairman, with division heads, Coordination Office head, and Project and Assistant Project Directors serving as members.
- 1959 June 19 - The Mercury Capsule (spacecraft) Coordination Office was organized within the Space Task Group. - Program: Mercury.
J. A. Chamberlin was appointed head of the office. Duties were divided into four major categories as follows: (1) loads, thermodynamics, structures, and aerodynamics; (2) cabin, life support, and controls; (3) electronics, recovery, and sequencing; and (4) transportation and handling, schedules and testing, and standards and specifications. This action assured continuity of effort in monitoring the McDonnell contract. Also, this office arranged and coordinated meetings with McDonnell personnel and served as a clearing house for all NASA-McDonnell contracts. The committee, of course, received a majority of its data from technical sources within the formal Space Task Group organization.
- 1959 June 21 - STG worked on advanced design concepts of earth orbital and lunar missions - Program: Apollo.
Members of STG - including H. Kurt Strass, Robert L. O'Neal, Lawrence W. Enderson, Jr., and David C. Grana - and Thomas E. Dolan of Chance Vought Corporation worked on advanced design concepts of earth orbital and lunar missions. The goal was a manned lunar landing within ten years, rather than an advanced Mercury program.
- 1959 June 25 - Research Steering Committee briefed on technical studies - Program: Apollo.
Alfred J. Eggers, Jr., of the Ames Research Center told the members of the Research Steering Committee of studies on radiation belts, graze and orbit maneuvers on reentry, heat transfer, structural concepts and requirements, lift over drag considerations, and guidance systems which affected various aspects of the manned lunar mission. Eggers said that Ames had concentrated on a landing maneuver involving a reentry approach over one of the poles to lessen radiation exposure, a graze through the outer edge of the atmosphere to begin an earth orbit, and finally reentry and landing.Additional Details: Research Steering Committee briefed on technical studies (15618).
- 1959 June 25 - Mercury recovery airdrop test. - Program: Mercury.
Navy surface vessels and aircraft were used in a recovery operation after an airdrop of a spacecraft off the coast from Jacksonville, Florida. The spacecraft was purposely dropped 40 miles away from the predicted impact point and 45 miles away from the nearest ship. Recovery was effected in 2 and one half hours.
- 1959 June 28 - Ablation materials for the Mercury Little Joe flights. - Program: Mercury. Launch Vehicle: Little Joe.
Between June 28 and July 11, 1959, 12 heat-transfer tests were made in the Preflight Jet Test facility at Wallops Island on several ablation materials being considered for use on the spacecraft afterbody (not heat shield) for the Little Joe flights. Test conditions simulated those of actual Little Joe trajectories. Of the materials used, triester polymer and thermolag demonstrated the capability to protect the spacecraft against expected heat loads.
- 1959 June 8 - Mercury survival kits - Program: Mercury.
The Space Task Group advised the Navy's Bureau of Aeronautics of Government-furnished survival items that McDonnell would package in containers. These included desalter kits, dye marker, distress signal, signal mirrors, signal whistle, first aid kits, shark chaser, PK-2 raft, survival rations, matches, and a radio transceiver. Navy assistance was requested in the procurement of these items.
- 1959 March 1 - Heatshield test of Mercury at lunar reentry speeds - Program: Apollo.
H. Kurt Strass and Leo T. Chauvin of STG proposed a heatshield test of a fullscale Mercury spacecraft at lunar reentry speeds. This test, in which the capsule would penetrate the earth's radiation belt, was called Project Boomerang. An advanced version of the Titan missile was to be the launch vehicle. The project was postponed and ultimately dropped because of cost.
- 1959 March 11 - First full-scale test simulating a Mercury pad-abort situation. - Program: Mercury.
Langley's Pilotless Aircraft Research Division conducted, at Wallops Island, the first full-scale test simulating a pad-abort situation. A full weight and size spacecraft was used. For the first 50 feet the flight was essentially straight, indicating the successful functioning of the abort rocket. Thereafter, the spacecraft pitched through several turns and impacted a short distance from the shore. The malfunction was traced to the loss of a graphite insert from one of the three abort rocket nozzles, which caused a misalignment of thrust.
- 1959 March 17 - Mercury mock-up inspection. - Program: Mercury.
A Mock-Up Inspection Board meeting was held at the McDonnell plant to review the completed spacecraft mock-up. As a result of this meeting, the contractor was directed to restudy provisions made for pilot egress; rearrange crew space to make handles, actuators, and other instruments more accessible to the pilot; and modify the clock, sequence lights, and other displays. This same type of meeting was held on many subsequent occasions to review production spacecraft.
- 1959 March 20 - Mercury-Redstone and Mercury-Jupiter test objectives. - Program: Mercury. Launch Vehicle: Redstone, Jupiter.
Mercury-Redstone and Mercury-Jupiter test objectives were discussed in a meeting at Langley between Space Task Group and Army Ballistic Missile Agency personnel. At that time it was decided that the first flights of both the Redstone and Jupiter would be unmanned. The second flights would be 'manned' with primates, and the Jupiter phase would end at that point. The six remaining Redstones would be used in manned flights for astronaut training.
- 1959 March 23 - DX priority procurement rating in support of Project Mercury. - Program: Mercury.
As of this date, the McDonnell Aircraft Corporation listed some 32 items that required a DX priority procurement rating in support of Project Mercury. This highest national priority procurement rating had been requested by NASA on November 14, 1958.
- 1959 March 26 - Hypersonic flight tests for the Mercury spacecraft. - Program: Mercury.
The Langley Research Center received approval for funds to conduct hypersonic flight tests for the Mercury spacecraft. Langley's Pilotless Aircraft Research Division would conduct tests on heat transfer rates at a velocity of mach 17, and dynamic behavior tests from a velocity of mach 10 to a subsonic speed.
- 1959 March 26 - Bio-pack experiments for Mercury Little Joe flights. - Program: Mercury. Launch Vehicle: Little Joe.
Space Task Group, Langley Research Center, and Air Force School of Aviation Medicine personnel met to plan bio-pack experiments that would be placed in several of the Little Joe research and development test flights.
- 1959 March 27 - Instructions for the marking of vehicles launched for the NASA. -
Dr. T. Keith Glennan, the NASA Administrator, provided instructions for the marking of vehicles launched for the NASA, including the Mercury spacecraft. He stated that policy would be to paint UNITED STATES in bold block form.
- 1959 March 28 - Mercury escape system changes - Program: Mercury.
Space Task Group officials were involved in an investigation as to whether the escape system should be changed. In the original proposal, McDonnell's plan was to use eight small rockets housed in a fin adapter, but this plan was set aside for a NASA developed plan in which a single-motor tripod would be used. Later, during a test of the escape system, the escape rockets appeared to fire properly but the spacecraft began to tumble after launch. This tumbling action caused concern, and Space Task Group engineers felt that the tower-escape system might have to be discarded, and a 'second look' was taken at the McDonnell proposal. The engineers concluded, however, that there were too many problems involved and the single-motor tripod concept was retained and has been proven to be quite effective.
- 1959 March 31 - Mercury abort methods. - Program: Mercury.
Range Safety personnel at the Atlantic Missile Range were briefed by Space Task Group personnel on the description of the Mercury spacecraft, how it would function during a normal flight on an Atlas launch vehicle, and suggest methods for initiation of an abort during different powered phases of a flight. Atlantic Missile Range personnel discussed their past experience, and work was started to draft a Project Mercury range safety plan.
- 1959 March 6 - Spare part and ground support equipment requirements for Project Mercury. - Program: Mercury.
Space Task Group and McDonnell officials met in St. Louis, Missouri, to discuss spare part and ground support equipment requirements for Project Mercury. Shortly thereafter, McDonnell submitted a preliminary plan for spare parts and check-out equipment to Space Task Group and NASA Headquarters for review.
- 1959 March 8 - Mercury abort test conducted at Wallops Island - Program: Mercury.
An abort test was conducted at Wallops Island on a full-scale model of the spacecraft with the escape tower, using a Recruit escape rocket. The configuration did not perform as expected (erratic motion), and as a result, the Langley Research Center was requested to test small-scale flight models of the abort system to determine its motion in flight.
- 1959 May 12 - An informal meeting of the Mock-Up Inspection Board. - Program: Mercury.
An informal meeting of the Mock-Up Inspection Board was held at McDonnell to review changes to the spacecraft development program resulting from the March mock-up meeting. Besides the review, a number of suggestions were made for changes in the crew space layout to permit more effective use of the controls, particularly when the astronaut was in the pressure suit in a full-pressurized condition. Among suggested changes were the shoulder harness release, the spacecraft compression and decompression handles, the ready switch, and the spacecraft squib switch. Test subjects also found that when in the fully pressurized suit none of the circuit breakers could be reached. McDonnell was directed to act on these problem areas.
- 1959 May 22 - The Project Mercury balloon flight test program was canceled. - Program: Mercury.
The Space Task Group oficials determined that the spacecraft could be tested environmentally in the Lewis Research Center's altitude wind tunnel. This included correct temperature and altitude simulations to 80,000 feet. The pilot could exercise the attitude control system and retrorockets could be fired in the tunnel. Because an active contract did exist with the Air Force, it was decided the two balloon drop tests with unmanned boiler-plate spacecraft would be accomplished.
- 1959 May 25 - First meeting of the Research Steering Committee on Manned Space Flight - Program: Apollo.
The first meeting of the Research Steering Committee on Manned Space Flight was held at NASA Headquarters. Members of the Committee attending were: Harry J. Goett, Chairman; Milton B. Ames, Jr. (part-time); De E. Beeler; Alfred J. Eggers, Jr.; Maxime A. Faget; Laurence K. Loftin, Jr.; George M. Low; Bruce T. Lundin; and Harris M. Schurmeier. Observers were John H. Disher, Robert M. Crane, Warren J. North, Milton W. Rosen (part-time), and H. Kurt Strass. The purpose of the Committee was to take a long-term look at man-in-space problems, leading eventually to recommendations on future missions and on broad aspects of Center research programs to ensure that the Centers were providing proper information. Committee investigations would range beyond Mercury and Dyna-Soar but would not be overly concerned with specific vehicular configurations. The Committee would report directly to the Office of Aeronautical and Space Research.
- 1959 May 25 - Tentative manned space flight priorities - Program: Apollo.
Tentative manned space flight priorities were established by the Research Steering Committee: Project Mercury, ballistic probes, environmental satellite, maneuverable manned satellite, manned space flight laboratory, lunar reconnaissance satellite, lunar landing, Mars Venus reconnaissance, and Mars-Venus landing. The Committee agreed that each NASA Center should study a manned lunar landing and return mission, the study to include the type of propulsion, vehicle configuration, structure, anti guidance requirements. Such a mission was an end objective; it did not have to be supported on the basis that it would lead to a more useful end. It would also focus attention at the Centers on the problems of true space flight.
- 1959 May 25 - National booster program, Dyna-Soar, and Mercury discussed - Program: Apollo. Launch Vehicle: Saturn C-2, Nova 4L, Saturn C-3BN, Saturn C-5N.
The national booster program, Dyna-Soar, and Project Mercury were discussed by the Research Steering Committee. Members also presented reviews of Center programs related to manned space flight. Maxime A. Faget of STG endorsed lunar exploration as the present goal of the Committee although recognizing the end objective as manned interplanetary travel. George M. Low of NASA Headquarters recommended that the Committee: - Adopt the lunar landing mission as its long-range objective.
- Investigate vehicle staging so that Saturn could be used for manned lunar landings without complete reliance on Nova.
- Make a study of whether parachute or airport landing techniques should be emphasized.
- Consider nuclear rocket propulsion possibilities for space flight.
- Attach importance to research on auxiliary power plants such as hydrogen-oxygen systems.
- 1959 May 5 - Mercury recovery test program. - Program: Mercury.
Space Task Group personnel held a meeting to discuss the complete recovery test program. Items of consideration included the availability of model spacecraft for the test, deciding the areas in which the tests would be held (Phase I - Wallops Island drops, and Phase II - Atlantic drops), and establishing the time schedule for the test program.
- 1959 May 6 - Pigs not to fly in space in Project Mercury - Program: Mercury. Launch Vehicle: Little Joe.
Pigs were eliminated as Little Joe flight test subjects when studies disclosed that they could not survive long periods of time on their backs. However, McDonnell did use a pig, 'Gentle Bess,' to test the impact crushable support, and the test was successful.
- 1959 November 1 - Mercury Horizon Scanner Handbook published. - Program: Mercury.
The 'Handbook of Operation and Service Instructions, Horizon Scanner Test, Serial MDE 4590011' was published. This document was revised and reissued on June 6, 1960.
- 1959 November 1 - Mercury first manned development system tests - Program: Mercury.
The first manned development system tests were completed at the AiResearch Manufacturing Division, Garrett Corporation. Tests were conducted in the altitude chamber to determine proper functioning of all system valves and components. A McDonnell subject was clothed in a Mercury-type presure suit for these tests. Preliminary data from these tests indicated that the system functioned satisfactorily.
- 1959 November 16 - Mercury astronauts familiarized with the expected reentry heat pulse - Program: Mercury.
Wearing the Mercury pressure suits, the astronauts were familiarized with the expected reentry heat pulse at the Navy Aircrew Equipment Laboratory, Philadelphia, Pennsylvania.
- 1959 November 20 - Open-circuit television system in the Mercury-Redstone MR-2 and MR-3 flights - Program: Mercury. Flight: Mercury MR-3. Launch Vehicle: Redstone.
At the fifth Mercury Coordination Meeting, the Army Ballistic Missile Agency proposed the installation of an open-circuit television system in the Mercury-Redstone second and third flights (MR-2 and MR-3). The purpose of the system was to observe and relay launch vehicle and spacecraft separation data.
- 1959 November 27 - Biopack experiment for Mercury Little Joe 2 flight. - Program: Mercury.
The Air Force School of Aviation Medicine agreed to provide a biopack experiment for the Mercury Little Joe 2 flight. Included in the pack were track plates of barley, nerve cells from a rat, tissue culture, and other specimens of that type.
- 1959 November 4 - Mercury LJ-1A - Program: Mercury. Launch Site: Wallops Island. Launch Vehicle: Little Joe. Apogee: 14 km (8 mi).
Little Joe 1-A (LJ-1A) was launched in a test for a planned abort under high aerodynamic load conditions. This flight was a repeat of the Little Joe (LJ-1) that had been planned for August 21, 1959 (escape rocket fired 31 min before the intended launch of the Little Joe launch vehicle). After lift-off, the pressure sensing system was to supply a signal when the intended abort dynamic pressure was reached (about 30 sec after launch). An electrical impulse was then sent to the explosive bolts to separate the spacecraft from the launch vehicle. Up to this point, the operation went as planned, but the impulse was also designed to start the igniter in the escape motor. The igniter activated, but pressure failed to build up in the motor until a number of seconds had elapsed. Thus the abort maneuver, the prime mission of the flight, was accomplished at a dynamic pressure that was too low. For this reason a repeat of the test was planned. All other events from the launch through recovery occurred without incident. The flight attained an altitude of 9 statute miles, a range of 11.5 statute miles, and a speed of 2,021.6 miles per hour.
- 1959 November 8 - Design of the Mercury Control Center was completed. - Program: Mercury.
Between this date and December 5, 1959, the tentative design and layout of the Mercury Control Center to be used to monitor the orbiting flight of the Mercury spacecraft were completed. The control center would have trend charts to indicate the astronaut's condition and world map displays to keep continuous track of the Mercury spacecraft.
- 1959 October 1 - McDonnell received the first Mercury ablative heat shield - Program: Mercury.
McDonnell received the first ablative heat shield, designated for installation on Spacecraft No. 1. This particular heat shield was based on the Big Joe design, and was manufactured by General Electric.
- 1959 October 1 - Funds approved for major changes to the Mercury spacecraft - Program: Mercury.
Funds were approved by NASA Headquarters for the following major changes to the Mercury spacecraft: egress hatch installation (CCP-58-1), astronaut observation window installation (CCP-73); rate stabilization and control system (CCP-61-2), main instrument and panel redesign (CCP-76), installation of reefed ringsail landing parachute (CCP-41), and nonspecification configurations of spacecraft (CCP-8). With reference to the last item, the original contract with McDonnell had specified only one spacecraft configuration, but the various research and development flight tests required changes in the configuration.
- 1959 October 30 - Mercury escape-system qualification-test results. - Program: Mercury.
A meeting of Space Task Group, Wallops Station, and McDonnell personnel was held to review and evaluate Mercury escape-system qualification-test results. In the continuing efforts of this activity, the responsibility in attaining test objectives was apportioned among the three organizations.
- 1959 September 1 - Mercury spacecraft modified to withstand lunar reentry conditions - Program: Apollo.
McDonnell Aircraft Corporation reported to NASA the results of several company-funded studies of follow-on experiments using Mercury spacecraft with heatshields modified to withstand lunar reentry conditions. In one experiment, a Centaur booster would accelerate a Mercury spacecraft plus a third stage into an eccentric earth orbit with an apogee of about 1,200 miles, so that the capsule would reenter at an angle similar to that required for reentry from lunar orbit. The third stage would then fire, boosting the spacecraft to a speed of 36,000 feet per second as it reentered the atmosphere.
- 1959 September 10 - Mercury spacecraft mock-up review - Program: Mercury.
At a spacecraft mock-up review, the astronauts submitted several recommended changes. These involved a new instrument panel, a forward centerline window, and an explosive side egress hatch.
- 1959 September 11 - Mercury astronaut food and water requirements - Program: Mercury.
After a preliminary study of the Mercury environment with regard to astronaut food and water requirements, Dr. Douglas H. K. Lee estimated that water use would be in the order of 500 cu cm/hr and that the caloric intake per day would be about 3,200 calories of food. Dr. Lee was a member of the Natick Quartermasters Research and Engineering Laboratory.
- 1959 September 19 - Mark II Mercury parachute test vehicle air launch - Program: Mercury.
An air launch of a Mark II parachute (drogue) test vehicle was conducted by the NASA Flight Research Center. This test, the 15th in the series, concluded the Project Mercury drogue parachute development and qualification tests.
- 1959 September 21 - Effects of sustained acceleration on the pilot's ability to control a vehicle. - Program: Mercury.
Between September 21 and October 10, 1959, a research program was carried out by the Aviation Medical Acceleration Laboratory to measure the effects of sustained acceleration on the pilot's ability to control a vehicle. Various side-arm controllers were used, and it appeared that the three-axis type (yaw, roll, and pitch) was the most satisfactory. Later this configuration was extensively evaluated and adopted for use in the control system of the Mercury spacecraft.
- 1959 September 9 - Mercury Astronauts' Handbook. - Program: Mercury.
The Space Task Group provided McDonnell with guidance in the development of the 'Astronauts' Handbook.' Topics included such items as a descriptive resume of normal and emergency procedures to be followed on the check lists. The book was divided into three sections: 'The Normal Operational Procedures,' 'The Emergency Operational Procedures,' and 'The Failure Analysis Procedures.'
- 1960 April 15 - Qualification tests for the Mercury spacecraft retrorockets were started. - Program: Mercury.
One of the main purposes of this program was the development of a better igniter. The igniter tested was attached to the head end of the propellant grain and coated with a pyrotechnic. Based on three tests it appeared that the delayed ignition problem had been resolved. Thereafter, several other tests were run until the igniter was adjudged to be reliable.
- 1960 August 1 - Mercury astronaut side-hatch-egress training was completed with no difficulties encountered. - Program: Mercury.
The astronauts later received refresher training prior to mission flights. In fact, during the refresher phases, better procedures were developed. An example was the helicopter mode in which a line was attached to the top of the spacecraft and the spacecraft was partially raised by the helicopter. Then, the astronaut emerged from the side egress hatch and was raised by a second line to the helicopter.
- 1960 August 1 - Mercury impact skirt water and land tests was completed. - Program: Mercury.
The first phase of the program in which boilerplate spacecraft with impact skirts were dropped by helicopters on water and land surfaces was completed. These tests were performed to investigate spacecraft dynamics, effects of parachute restraint and release time on spacecraft dynamics, and to determine maximum landing decelerations. During the drops into the water spacecraft water stability was shown to be unacceptable, because a portion of the spacecraft cylindrical section remained under water. McDonnell immediately investigated this problem and performed such experiments as redistribution of weight to obtain center-of-gravity positions which were acceptable but yet provided satisfactory flotation characteristics. Space Task Group was investigating the possibility of extending the heat shield from the remainder of the spacecraft and thereby creating a greater stabilizing moment. Results from the drops on land appeared to be acceptable because of the relatively low decelerations and the overall low probability of a landing on land.
- 1960 August 11 - The Mercury spacecraft landing system qualification test program was completed. - Program: Mercury.
The entire qualification testing program consisted of 56 airdrops of full-scale engineering models of the Mercury spacecraft from C-130 aircraft at various altitudes up to 30,000 feet and from helicopters at low altitudes to simulate off-the-pad abort conditions. This test program, under contract to Northrop, had spanned one and one half years.
- 1960 August 16 - Mercury spacecraft No. 7 astronaut inspection results in changes in the control panel - Program: Mercury.
At the design engineering inspection of spacecraft No. 7, a number of requests for changes in the control panel area were made by the astronauts to facilitate pilot operation. Later, meeting procedures for design engineering inspections were standardized and conducted by a permanent team at appropriate intervals.
- 1960 December 14 - Mercury satellite clock canceled. - Program: Mercury.
A contract with the Waltham Precision Instrument Company for the development of a satellite clock was canceled. Technical difficulties were encountered in the manufacturing of the device, previously scheduled for delivery in August 1960, and there was little assurance that these problems could be resolved in time for the clock to be used in any of the Mercury flights. McDonnell fabricated an orbital timing device, which proved to be very satisfactory.
- 1960 December 19 - Mercury MR-1A - Program: Mercury. Launch Site: Cape Canaveral. Launch Vehicle: Redstone. Apogee: 210 km (130 mi).
Mercury-Redstone 1A (MR-1A) was launched from Cape Canaveral in a repeat of the November 21, 1960, mission and was completely successful. This was the third attempt to accomplish the objectives established for this flight. The first attempt on November 7, 1960, was canceled as a result of a helium leak in the spacecraft reaction control system relief valve, and on November 21, 1960, the mission could not be completed because of premature cut-off of the launch vehicle engines. Objectives of the MR-1A flight were to qualify the spacecraft for space flight and to qualify the flight system for a primate flight scheduled shortly thereafter. Close attention was given to the spacecraft-launch vehicle combination as it went through the various flight sequences: powered flight; acceleration and deceleration; performance of the posigrade rockets; performance of the recovery system; performance of the launch, tracking, and recovery phases of the operation; other events of the flight including retrorocket operation in a space environment; and operation of instrumentation. Except that the launch vehicle cut-off velocity was slightly higher than normal, all flight sequences were satisfactory; tower separation, spacecraft separation, spacecraft turnaround, retrofire, retropackage jettison, and landing system operation occurred or were controlled as planned. The spacecraft reached a maximum altitude of 130.68 statute miles, a range of 234.8 statute miles, and a speed of 4,909.1 miles per hour. Fifteen minutes after landing in the Atlantic Ocean, the recovery helicopter picked up the spacecraft to complete the successful flight mission.
- 1960 February 1 - External and Internal Noise of Mercury Space Capsules. - Program: Mercury. Launch Vehicle: Little Joe.
A study was completed on the 'External and Internal Noise of Space Capsules.' This study covered the acoustic environments of missile and space vehicles including noise generated by the rocket engines, air-boundary layers, and on-board equipment. Data used included noise measurements compiled from the Big Joe I and Little Joe 2 flight tests. These tests were a part of the internal and external noise study that had been in progress since early 1959. NASA officials were still of the opinion that the internal noise level was too high for pilot comfort. Space Task Group felt that data were needed on noise transmission through an actual production-model spacecraft structure.
- 1960 February 1 - Qualification tests of the Mercury spacecraft periscope were completed. - Program: Mercury.
- 1960 February 15 - Mercury spacecraft battery qualification tests were completed. - Program: Mercury.
- 1960 February 15 - Mercury landing system and post-landing equipment tests were completed. - Program: Mercury.
- 1960 February 22 - Tests were completed on the Mercury spacecraft automatic stabilization and control system. - Program: Mercury.
- 1960 February 27 - Design approval and reliability tests of the Mercury command receivers were completed. - Program: Mercury.
- 1960 January 1 - Training of Mercury remote-site flight controllers - Program: Mercury.
Specifications for equipment and systems to be used for the training of the remote-site flight controllers and Mercury control center operations personnel were forwarded to the Western Electric team. The remote-site training was divided into two stages: off-range and on-range. The off-range portion consisted of practice runs on a typical set of controllers' consoles tied into an astronaut procedures trainer. The on-range part was planned at two stations within the United States and from here, controllers would be assigned to tracking sites for full range rehearsals and a mission.
- 1960 January 19 - English vendors for Project Mercury components. - Program: Mercury.
In keeping with a concept of using certain off-the-shelf hardware items that were available for the manufacture of Project Mercury components, companies around London, England, were visited throughout 1959. Potential English vendors of such items as the SARAH beacon batteries (later chosen), miniature indicators, time delay mechanisms, hydrogen-peroxide systems, and transducers were evaluated. A report of the findings was submitted on the cited date.
- 1960 January 21 - Mercury LJ-1B - Program: Mercury. Launch Site: Wallops Island. Launch Vehicle: Little Joe. Apogee: 14 km (8 mi).
Little Joe 1-B (LJ-1B) was launched from Wallops Island with a rhesus monkey, 'Miss Sam,' aboard. Test objectives for this flight were the same as those for Little Joe 1 (LJ-1) in which the escape tower launched 31 minutes before the planned launch, and Little Joe 1-A (LJ-1A), wherein the dynamic buildup in the abort maneuver was too low. A physiological study of the primate, particularly in areas applying to the effects of the rapid onset of reverse acceleration during abort at maximum dynamic pressure, was also made. In addition, the Mercury helicopter recovery system was exercised. During the mission, all sequences operated as planned; the spacecraft attained a peak altitude of 9.3 statute miles, a range of 11.7 statute miles, and a maximum speed of 2,021.6 miles per hour. Thirty minutes from launch time, a Marine recovery helicopter deposited the spacecraft and its occupant at Wallops Station. 'Miss Sam' was in good condition, and all test objectives were successfully fulfilled.
- 1960 January 25 - McDonnell delivered first production Mercury spacecraft. - Program: Mercury.
McDonnell delivered the first production-type Mercury spacecraft to the Space Task Group at Langley in less than 1 year from the signing of the formal contract. This spacecraft was a structural shell and did not contain most of the internal systems that would be required for manned space flight. After receipt, the Space Task Group instrumented the spacecraft and designated it for the Mercury-Atlas 1 (MA-1) flight.
- 1960 July 29 - Mercury spacecraft No. 3 was delivered to Langley Field for a noise and vibration test. - Program: Mercury.
- 1960 July 29 - Mercury MA-1 - Program: Mercury. Launch Site: Cape Canaveral. Launch Vehicle: Atlas D. FAILURE: Structural failure of Atlas. Apogee: 13 km (8 mi).
Mercury-Atlas 1 (MA-1) was launched from the Atlantic Missile Range in a test of spacecraft structural integrity under maximum heating conditions. After 58.5 seconds of flight, MA-1 exploded and the spacecraft was destroyed upon impact off-shore. None of the primary capsule test objectives were met. The mission objectives were to check the integrity of the spacecraft structure and afterbody shingles for a reentry associated with a critical abort and to evaluate the open-loop performance of the Atlas abort-sensing instrumentation system. The spacecraft contained no escape system and no test subject. Standard posigrade rockets were used to separate the spacecraft from the Atlas, but the retrorockets were dummies. The flight was terminated because of a launch vehicle and adapter structural failure. The spacecraft was destroyed upon impact with the water because the recovery system was not designed to actuate under the imposed flight conditions. Later most of the spacecraft, the booster engines, and the liquid oxygen vent valve were recovered from the ocean floor. Since none of the primary flight objectives was achieved, Mercury-Atlas 2 (MA-2) was planned to fulfill the mission.
- 1960 June 1 - Mercury recoverable experiments - Program: Mercury.
In the overall NASA space program, Project Mercury was the only program which included a recovery capability. For this reason, Space Task Group officials felt there were a number of experiments in the science and bioscience fields that could be placed aboard Mercury spacecraft during mission flights. An example of such experiments would be an ultra-violet camera which would provide data to assist in the design and development of an orbiting astronautical observatory; another might be bio-specimens. Obviously, decisions in experiment selections would have to be made to prevent any dilution of the primary Mercury mission.
- 1960 June 2 - Possible meteoroid damage to the Mercury spacecraft. - Program: Mercury.
In considering the possible meteoroid damage to the Mercury spacecraft in orbital flight, it was concluded by the Space Task Group that damage likelihood was small even during periods of meteor showers. However, it was recommended that Mercury missions not be scheduled during forecasted shower periods.
- 1960 June 20 - Manned tests of the Mercury environmental control system began. - Program: Mercury.
The subjects were clothed in pressure suits and subjected to postlanding conditions for 12 hours without serious physiological effects. The purpose of this test was to evaluate human tolerance, and the results indicated that no modification to the system were necessary. However, the postlanding ventilation conditions would continue to be monitored and requirements for any modifications would be evaluated.
- 1960 June 20 - Tests were completed on the Mercury spacecraft horizon scanner. - Program: Mercury.
A sandblast technique was employed in these tests, and measurements revealed that transmissibility was reduced in direct proportion to the area sand blasted. Tests covered 25, 50, and 75 percent of a germanium specimen.
- 1960 June 27 - Mercury Project Orbit - Program: Mercury.
As a complement to the Mercury spacecraft reliability program, a decision was made that one production spacecraft would be withdrawn from the operational program for extensive testing. The test environment would involve vacuum, heat, and vibration conditions. This test series was later designated 'Project Orbit.'
- 1960 June 3 - As of this date, the funding status of Contract NAS 5-59, Mercury spacecraft, was $75,565,196. - Program: Mercury.
- 1960 June 30 - Mercury spacecraft No. 2 was delivered to Huntsville. - Program: Mercury.
Spacecraft No. 2 was delivered to the Marshall Space Flight Center, Huntsville, Alabama, for compatibility tests with the Redstone launch vehicle, and was shipped to Cape Canaveral on July 23, 1960.
- 1960 March 1 - Qualification tests started on the Mercury escape tower rocket. - Program: Mercury.
These tests were completed at the end of July 1960. As a part of the qualification program, three escape-rocket motors were successfully fired on a spacecraft model at conditions corresponding to approximately 100,000 feet altitude in the Lewis Research Center altitude wind tunnel. One motor was tested on a four-component balance system to determine thrust misalignment of the rocket motor. According to test results, the rocket motor appeared to meet operational requirements.
- 1960 March 11 - Pioneer V - Program: Mercury.
Pioneer V, launched as a probe of the space between Earth and Venus, began to provide invaluable information on solar flare effects, particle energies and distributions and magnetic phenomena. Pioneer V continued to transmit such data until on June 26, 1960, when at a distance of 22.5 million miles from Earth, it established a new communications record.
- 1960 March 16 - The Space Task Group published recovery requirements for the Mercury-Atlas 1 (MA-1) flight test. - Program: Mercury. Launch Vehicle: Atlas D.
- 1960 March 28 - Mercury astronaut first open-water egress training. - Program: Mercury.
Between March 28,1960 and April 1, 1960, the astronauts received their first open-water egress training in the Gulf of Mexico off the coast of Pensacola, Florida, in cooperation with the Navy's School of Aviation Medicine. The training was conducted in conditions of up to 10-foot swells, and no problems were experienced. The average egress time was about 4 minutes from a completely restrained condition in the spacecraft to being in the life raft.
- 1960 March 29 - Mercury spacecraft facility at Huntsville no longer required. - Program: Mercury.
A decision was made by NASA Headquarters that the spacecraft prelaunch operation facility at Huntsville, Alabama, was no longer required. Spacecraft that were designated for Mercury-Redstone missions were to be shipped directly from McDonnell to Cape Canaveral, thereby gaining approximately 2 months in the launch schedule.
- 1960 May 1 - Pressurized animal couches delivered for Mercury flight test program. - Program: Mercury.
McDonnell delivered the flight-pressurized couches to be used in the animal phase of the Mercury flight test program. According to test results, the couches appeared to be satisfactory, with the exception of a slight sealing problem. McDonnell was attempting to resolve this problem.
- 1960 May 1 - Two McDonnell Mercury Procedures Trainers delivered to NASA. - Program: Mercury.
Number 1, delivered on May 4, 1960, was used for astronaut training in the management of the spacecraft systems at Langley Field and Number 2, delivered on July 5, 1960, was installed at Cape Canaveral, also for space flight preparations. The trainer at Langley Field, along with other equipment, later designated flight simulator, was moved in 1962 to Houston, Texas, location of the Manned Spacecraft Center, the successor to the Space Task Group.
- 1960 May 15 - Qualification tests for the Mercury spacecraft explosive egress hatch were completed. - Program: Mercury.
- 1960 May 23 - Mercury Spacecraft No. 4 delivered to Cape Canaveral. - Program: Mercury.
Spacecraft No. 4 (production number), after being instrumented and prepared by the Space Task Group and the Langley Research Center for flight tests, was delivered to Cape Canaveral for the first Mercury-Atlas mission (MA-1).
- 1960 May 9 - Mercury Pad Abort 1 - Program: Mercury.
McDonnell's first production spacecraft, with its escape rocket serving as the propulsion force, was launched from Wallops Island. Designated the beach-abort test, the objectives were a performance evaluation of the escape system, the parachute and landing system, and recovery operations in an off-the-pad abort situation. The test was successful.
- 1960 May 9 - Beach Abort 1 - Program: Mercury. Launch Site: Wallops Island.
First production model of Project Mercury spacecraft was successfully launched from NASA Wallops Station to test escape, landing, and recovery systems. Known as the "beach abort" shot, the Mercury capsule reached 775 m before parachute landing and pickup by Marine helicopter returned it to Wallops' hangar 17 minutes after launch.
|
