German engineer in WW2, member of the Rocket Team in the United States thereafter. Liaison between Huntsville and Rocketdyne for development of the engines for the Redstone, Jupiter, and Saturn I rockets; managed development of the Saturn V in the early years; developed concepts for Saturn V-launched space stations. Retired 1973.

Segmented solid-propellent rocket engine fired by United Technology Corp. at Sunnyvale, generating over 200,000 pounds of thrust in 80-second firing. Developed under NASA contract, center section of engine contained over 55,000 pounds of propellant, the largest single piece yet manufactured in the United States.

The second Jupiter to be fired under the operational control of NATO troops in the Combat Training Launch program was fired from AMR at 1919 hours and 06 seconds EST to a range of 1,516 nm. The missile was originally scheduled for firing on 3 August but was postponed because of problems with the fuel probe in the fuel start tank and the micro-switch on the fuel pumping lever arm which controls the fuel flow rate. All missions assigned to the missile and to the NATO training launch crew were successfully accomplished.

In what was to have been an acceptance test, the Douglas Aircraft Company static fired the first Saturn S-IV flight stage at Sacramento, Calif. An indication of fire in the engine area forced technicians to shut down the stage after little more than one minute's firing. A week later the acceptance test was repeated, this time without incident, when the vehicle was fired for over seven minutes. (The stage became part of the SA-5 launch vehicle, the first complete Saturn I to fly.)

During tests of the Apollo earth landing system (ELS) at El Centro, Calif., boilerplate (BP) 6A sustained considerable damage in a drop that was to have demonstrated ELS performance during a simulated apex-forward pad abort. Oscillating severely at the time the auxiliary brake parachute was opened, the spacecraft severed two of the electrical lines that were to have released that device. Although the ELS sequence took place as planned, the still-attached brake prevented proper operation of the drogues and full inflation of the mains. As a result, BP-6A landed at a speed of about 50 fps.

The Saturn V's booster, the S-IC stage, made a "perfect" full-duration static firing by burning for the programmed 2.5 minutes at its full 33,360-kilonewton (7.5-million-lbs) thrust in a test conducted at MSFC. The test model demonstrated its steering capability on command from the blockhouse after 100 sec had elapsed; the firing consumed 2.133-million liters (537,000 gallons) of kerosene and liquid oxygen.

Ballistic Systems Division directed Autonetics Division of North American Aviation to proceed with the development of a Post Boost Control System for Minuteman. This would incorporate guidance, propulsion, and directional control of a reentry vehicle after it separated from the third-stage motor.

At a meeting at LII MAP Zazakov, Litvinov, Mishin, Tsybin, Bushuev, Severin, Alekseyev, and Komarov spar over the hatch and spacesuit problem. Severin only agrees to modifying the ECS under immense pressure, but the modified suit will not be ready until November. Severin could not get Mishin to agree to an increased hatch diameter from Soyuz s/n 8 - Mishin will only "study the problem". An arrangement of the ECS around the waist of the cosmonaut is finally agreed. Mishin and Litvinov categorically rejected any modification of the hatch in the first production run of Soyuz.

In turn, Factory 918 insisted on a final decision on Soyuz crews. They cannot build 16 of the custom-built spacesuits for all possible candidates for the flights (8 from VVS and 8 from OKB-1). It was therefore agreed that the commanders of the first two missions would be Komarov and Bykovsky, with Nikolayev and Gagarin as their backups. It was finally decided to assume that the other crew members would be either Khrunov and Gorbatko from the VVS, or Anokhin and Yeliseyev from OKB-1.

Following the decision to implement the Saturn V dry Workshop, LM-2 was the only flight LM article to remain on Earth. Therefore, NASA Hq requested MSC consideration for early disposition of it to the Smithsonian Institution as an artifact of historical interest. Since it was expected that the Smithsonian would exhibit LM-2 as a replica of LM-5, Headquarters also requested that MSC consider refurbishment to provide a more accurate representation of the LM- 5 configuration before its transfer to the Smithsonian.

Mars probe intended to make a soft landing on Mars. Total fueled launch mass of the lander and orbital bus was 3260 kg. It reached Mars on 12 March 1974, separated from the bus, and entered the atmosphere, where a parachute opened, slowing the descent. As the probe descended through the atmosphere it transmitted data for 150 seconds, representing the first data returned from the atmosphere of Mars. Unfortunately, the data were largely unreadable due to a flaw in a computer chip which led to degradation of the system during its journey to Mars. When the retro-rockets fired for landing, contact was lost with the craft. Mars 6 landed at about 24 degrees south, 25 degrees west in the Margaritifer Sinus region of Mars. Bus ended up in a final heliocentric orbit 1.01 x 1.67 AU, 2.2 degree inclination, 567 day period.

Failure of a liquid oxygen valve led to the oxidiser tank over-pressurising, collapse of the liquid oxygen to kerosene tank bulkhead; intermixing of the propellants, and finally an on-pad explosion without lift-off. The vehicle was funded by Space Services, Inc of Houston, Texas and was built by GCH, Inc (Gary C. Hudson). The booster featured a modular design using liquid oxygen-kerosene stages 18 m long and 1.2 m in diameter, with an engine producing 27,300 kgf of thrust.

High resolution photo surveillance; film capsule; maneuverable; also performed earth resource tasks. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation.

CS-2b (Sakura 2b). Launch time 2029 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle flight no. 11 (N-II launch vehicle). Domestic satellite communications; development of communications satellite technolog y. Positioned in geosynchronous orbit at 136 deg E in 1983-1989; 128 deg E in 1989-1990 As of 4 September 2001 located at 154.41 deg E drifting at 5.251 deg W per day. As of 2007 Mar 10 located at 13.72E drifting at 5.257W degrees per day.

15 Ku-band transponders; boosted into geosynch orbit by satellite thrusters following Delta failure that left satellite in LEO; unplanned use of satellite propellant cut usable satellite lifetime by approx. 50 percent. Stationed at 116.0 deg E. Stage 1 SRM failure Positioned in geosynchronous orbit at 116 deg E in 1995-1999 As of 5 September 2001 located at 47.22 deg E drifting at 0.022 deg E per day. As of 2007 Mar 9 located at 152.88E drifting at 2.155W degrees per day.

Flight Time: 1.5 hours Pilot: Shane Copilot: Siebold. Objectives: First flight test card repeat. Flying qualities assessment and basic performance evaluation. Avionics and pneumatic systems evaluation. Cabin un-pressurized. Results: Envelope expansion to 15,000 feet and 140 knots. Overall satisfactory stability, good control harmony and impressive performance. Heavy airframe buffet at high speeds with both sets of speed brakes deployed. "Best airplane the company has ever built"

Jupiter Near-polar Orbiter, accelerated by the AV-029 Centaur to a hyperbolic escape orbit at 17:15 GMT into a 1.0 AU x 2.26 AU x 0.1 deg solar orbit. A 500-km flyby of Earth on 9 October 2013 pumped this orbit towards Jupiter. It is planned to enter Jovian orbit in July 2016, and be commaned to bun up in Jupiter's atmosphere in October 2017. Payloads included magnetometers, plasma and particle instruments, UV auroral imagers and spectrometers, and the JunoCam imager. The probe has a massmof 1593 kg and carries a further 2032 kg of propellant. Its three large solar arrays span around 22 meters; it is the first spacecraft to fly to the outer solar system without radioisotope power sources.

Used an R-4D bipropellant thruster to reach GEO. The first R-4D burn on August 6 raised the orbit from 180 km x 35,762 km x 24.3 deg to 7,137 x 35,751 km x 10.7 deg. By August 11 the satellite was in a 35,725 x 35,732 km x 0.1 deg orbit drifting east over 104 deg E.