| Corporal | ||||||||||||||||||||
At request of Army Ordnance, Cal Tech's rocket laboratory developed the first US long-range missiles. Project ORDCIT resulted in development of the Private A and Corporal missiles. Historical Essay © Andreas Parsch JPL/Firestone SSM-A-17/M2/MGM-5 Corporal The Corporal was the first U.S. guided missile system to be approved for nuclear armament, and the first operational guided missile of the U.S. Army. It evolved from a series of Army research rockets begun in 1944/45. The first missile to carry the name Corporal was the small WAC Corporal (designated RTV-G-1 in 1947) sounding rocket, first launched in September 1945. The WAC Corporal B was later also used to create an experimental two-stage research rocket, when it was mounted on top of captured German V-2 missiles. 8 of these vehicles, known as RTV-G-4 Bumper, were used for tests between 1948 and 1950. The immediate forerunner of the tactical Corporal SSM was the RTV-G-2 Corporal E surface-to-surface test vehicle. It was first flown in May 1947. The Corporal E was used to evaluate basic principles of ballistic guided missile construction, flight, and guidance. Because of continuing problems with the Army's SSM-G-9 Hermes program, it was decided in 1950 to develop the Corporal E into a tactical nuclear-armed ballistic missile, designated SSM-G-17 Corporal. In 1951, the Army's missile designation system changed slightly, and the RTV-G-2 and SSM-G-17 became RV-A-2 and SSM-A-17, respectively. However, the RV-A-2 designation was dropped almost at the same time, and all Corporal test rounds were known as XSSM-A-17. Main contractor for Corporal was the Jet Propulsion Laboratory (JPL), and the early Corporal E missile airframes were built by Douglas. However, the contract for the production of the operational missiles went to Firestone in 1951, after missile design had been frozen. The first tactical SSM-A-17 Corporal version was also known as Corporal Type I. The first flight occurred in August 1952, and in April 1954 the first Army units began training with the missile, which was designated as Guided Missile XM2 in service. The SSM-A-17 was armed with a W-7 nuclear fission warhead (20 kT). The SSM-A-17 Corporal had many inherent problems, some of which resulted from it being essentially a slightly modified research missile. Its JPL liquid fueled rocket motor was not only rather complex and unreliable, but also used red fuming nitric acid (RFNA) as oxidizer. RFNA is a highly toxic and corrosive substance, and fueling was a very dangerous process. The other major problem was the guidance system. The missile's trajectory and velocity was tracked by a ground radar (a modified SCR-584 designated AN/MPQ-12), which computed necessary course corrections, which were transmitted to the missile's autopilot. The missile was steered in flight by rudders and jet vanes, and range was controlled by sending a motor shut-off command at the appropriate time. This guidance system was very complex and hard to maintain, and also prone to electronic jamming. All these problems resulted in a less than 50% reliability of the Corporal missile system. Furthermore, a Corporal battalion consisted of about 35 vehicles, and was rather cumbersome to move. After a launch site had been reached, it took around 9 hours before the first missile could be fired. In 1953, JPL started to look for improvement of the Corporal's reliability. The major changes in the new system (called Corporal Type II) were new radar/radio components, including a new Doppler unit. The missile launcher, erector, and servicing platform were also redesigned. The Type II missiles were initially known as XSSM-A-17a, and later as XM2E1. Beginning in 1956, Type II quickly replaced all Type I systems, and the Corporal missile was designated as Guided Missile, Artillery M2. Type IIa, introduced in 1957, had an improved guidance system, which changed much of the system's electronic components, but resulted in no external changes to the missile. From 1958, production missiles were of Type IIb, which had an air-turbine alternator (ATA) instead of the unreliable internal batteries, and quick-disconnect fins for faster missile setup. The Type IIb missiles were designated as M2A1 (it is possible, but not likely, that the M2A1 designation also applied to the Type IIa missiles). Although the Corporal Type II/IIa/IIb somewhat improved the system's reliability, the basic problems of the Corporal remained. The Army originally planned to develop a Corporal Type III missile with a further improved guidance system, but in 1958 this was cancelled, because development of the much more advanced MGM-29 Sergeant made good progress. After the Sergeant became operational in 1962, the Corporal was quickly phased out, and the last Corporal was retired in 1964. In 1963, the M2 and M2A1 missiles had been redesignated as MGM-5A and MGM-5B, respectively. About 1100 Corporal Type I, II, IIa and IIb missiles were delivered to the U.S. Army. SpecificationsNote: Data given by several sources show slight variations. Figures given below may therefore be inaccurate! Data for M2/M2A1 (MGM-5A/B):
[1] James N. Gibson: "Nuclear Weapons of the United States", Schiffer Publishing Ltd, 1996 Manufacturer: JPL/Firestone. Launches: 148. Failures: 3. Success Rate: 97.97%. First Launch Date: 1947-05-22. Last Launch Date: 1955-06-14. Launch data is: complete. Liftoff Thrust: 89.200 kN (20,053 lbf). Total Mass: 5,440 kg (11,990 lb). Core Diameter: 0.76 m (2.49 ft). Total Length: 14.02 m (45.99 ft). Span: 1.92 m (6.29 ft). Standard warhead mass: 680 kg (1,490 lb). Maximum range: 121 km (75 mi). Number Standard Warheads: 1. Standard warhead: W7. Standard warhead yield: 60 KT. Boost Propulsion: Storable liquid rocket. Guidance: Command Link. Maximum speed: 3,870 kph (2,400 mph). Development Cost $: 50.100 million. in: 1955 average dollars. Recurring Price $: 0.260 million. Total Number Built: 1101. Total Development Built: 55. Total Production Built: 1046. Flyaway Unit Cost $: 0.110 million. in: 1959 unit dollars. Model: Corporal E. Year: 1947. Country: USA. Experimental version of Corporal Missile The US Army ORDCIT program to develop ballistic rockets as potential weapons began with the Private-A and Private-F, continued with the Wac Corporal, and then the Corporal-E, before finally becoming a separate weapon development program. The first test flight of the Coporal-E, on 22 May 1947, was a complete success. In September 1949, after the firing of Corporal-E Round 4, the Missiles and Rockets Branch of the Office of the Chief of Ordnance requested Jet Propulsion Laboratory to develop a guidance system for the improved version of the Corporal missile. During the next two years, while work on this new guidance system was being carried out, seven more Corporal-E rounds were fired at White Sands Proving Ground. On January 18, 1950, the Chief of Ordnance directed Jet Propulsion Laboratories to accelerate the Corporal-E research test vehicle program and reorient the project to a guided missile weapon system. On August 11, 1950, the Deputy Assistant Chief of Staff for Research and Development proposed that the Army undertake development of a modified version of the Corporal-E, the Corporal I. The Corporal-E was terminated as a specific project. Manufacturer: JPL. Apogee: 50 km (31 mi). Liftoff Thrust: 89.000 kN (20,007 lbf). Total Mass: 4,500 kg (9,900 lb). Core Diameter: 0.76 m (2.49 ft). Total Length: 14.00 m (45.00 ft). Model: Corporal Type 1. Year: 1952. Country: USA. First prototype of Corporal missile. US Army Corporal Type 1 Fact Sheet: The CORPORAL Type I (XSSM-A-17 to XSSM-G-17) program was initiated in 1949 while the CORPORAL-E firing tests were still under way. The Type I missile system utilized some HERMES components and a DOVAP type transponder, but with the exception of the propulsion system it left something to be desired in the way of a tactical weapon. This fact eventually led to development of the Type II CORPORAL, which will be described later. Type I firings were carried out from January 1951 through December 1954. A total of 64 Type I rounds were fired, including 20 in the Engineer-User testing program and 44 by JPL in its contractor testing, evaluation and development programs. A reliable propulsion system was developed. Malfunctions in the propellant shutoff mechanism, encountered frequently in the earlier tests, eventually were solved by redesigning components. A right azimuth bias, observed repeatedly in the early tests, was effectively removed by incorporating accelerometer control in azimuth. The Type I CORPORAL was 45 feet long, 30 inches in diameter and weighed 11,400 pounds. The propulsion system, with a burning time of 63 seconds, developed 20,000 pounds of thrust. The fuel was liquid aniline, with inhibited red fuming nitric acid (IRFNA) as the oxidizing agent. Capable of carrying a 1,500-pound payload at ranges of 50,000 to 120,000 meters, or 25 to 75 nautical miles, the Type I system was fired from a mobile ground installation. It was designed to fly a series of standard trajectories. The range of the missile was controlled primarily by terminating thrust at a velocity, determined by a shutoff computer, that would minimize the range error at impact. So that the missile would be in the proper region of position-velocity space at shutoff, an elevation computer system guided the missile along a predetermined trajectory from 22 seconds to shutoff. Range error was further reduced by determining, on the basis of measured position and velocity, the predicted impact error, near the peak of the trajectory, and by programming a terminal maneuver to compensate for this error. The azimuth error was controlled by commands calculated to keep the missile heading on target from 22 seconds to impact minus 10 seconds. The missile was controlled to fly close to the standard trajectory by means of yaw and pitch programs, and by autopilot control. Deviations were determined by a combination of Doppler and radar data. These data were transmitted to the missile as commands. Type I Contractors The first Type I CORPORAL missiles were fabricated by the Douglas Aircraft Company, Santa Monica, California. During 1949, Douglas built seven CORPORAL airframes under Contract W-04-200-ORD-1504. Propulsion and guidance were added by the Jet Propulsion Laboratory. During 1950 and early in 1951, Douglas built an additional 20 rounds (Rounds 12 through 31) under Contract DA-04-495-ORD-21. The Douglas rounds were used in the R&D flight testing program. Production information also was generated under these contracts. Even before the demonstration of guidance feasibility, the Department of Defense ordered the CORPORAL into production. Thus, in the summer of 1951, several companies were invited to submit bids for the initial Type I production contract. In October 1950, the Office of the Director of Guided Missiles had been established in the Office of the Secretary of Defense, and Mr. K.T. Keller had been appointed to this office. On 15 March 1951, the Department of the Army had recommended to Mr. Keller an industrial program calling for the procurement of CORPORAL missiles, spare parts and ground equipment. Upon approval of the Secretary of Defense, bids for production of 200 missiles, plus spare parts and manuals, were solicited from several selected companies. A Board of Awards met at Redstone Arsenal on 29 June 1951 and selected the Firestone Tire and Rubber Company as the successful bidder. A letter order in the amount of $6,888,796 was placed with the Firestone Company on 17 July 1951. This was replaced, when funds became available for the Fiscal Year 1952 program, with Contract DA-04-495-ORD-159, dated 10 December 1951, in the amount of $13,695,592. In June 1952, implementing another program approved by the Secretary of Defense, this contract was supplemented to call for production of 120 additional missiles, at a cost of $9,000,000, or $75,000 per unit. This brought the total to be produced under the ORD-159 contract to 320 Type I CORPORAL missiles. Type I Evaluation Program The first Firestone-manufactured CORPORAL,which incorporated all the significant features of CORPORAL-E Round 11, was fired at White Sands Proving Ground on 7 August 1952. Two more Firestone missiles were launched during the month of August. These missiles were incomplete with reference to guidance equipment -- the radar command unit and the range correction unit had not reached a satisfactory production stage and could not be used in the production flight tests. However, all rounds manufactured by Firestone under the initial contract were delivered to JPL, where they were dismantled, inspected, reassembled and preflight tested before shipment to WSPG for flight testing. As a result of this preflight evaluation program, JPL was able to submit suggestions to Firestone to assist in expediting factory production of acceptable rounds. Various difficulties were encountered during the Type I flight evaluation program, which continued in 1953 and 1954. The most flagrant of these involved the propellant shutoff circuit, which affected the range control mechanism. The missiles were fired at ranges of 30, 50 and 70 statute miles. This system showed a greater dispersion in range than in azimuth, and the Type I program demonstrated a CPE of approximately 500 meters. This was considered satisfactory in view of the fact that many unique experiments were being conducted during this phase, and these experiments were more likely to cause errors or failures than would be the case in normal tactical operations. While these experiments themselves did not necessarily result in improvement of the overall accuracy record of the Type I CORPORAL, they were necessary during the design and development stage of such a new weapon system. Corporal missile launch on Oct. 25, 1955 Type I Engineer-User Program As early as the spring of 1952, planning was under way for the CORPORAL Engineer-User program. The first E-U missile, scheduled to arrive in September 1952, was delayed until early January 1953. Concerning the E-U testing program, a JPL report said: "Past conventions have usually dictated that any new weapon development be given engineering tests by that arm of the Army which has had responsibility for the particular weapon program. These tests have then been followed by tests of the weapon under operational conditions, as conducted by the using arm of the service. This practice was somewhat altered insofar as the CORPORAL was concerned. In the interests of conserving time, money and manpower, a joint team of Army Ordnance Corps and Field Forces personnel was formed as an Engineer-User team for the CORPORAL missile. This team was organized at White Sands Proving Ground; the testing program initially used missiles which had been modified by the Jet Propulsion Laboratory preparatory to release to the Engineer-User team. This team also used ground guidance and handling equipment which was obtained by this Laboratory and subjected to various modification prior to the release for Engineer-User tests." Fourteen rounds were fired in the E-U program from 30 January 1953 through 22 January 1954. CORPORAL EU-1 (Firestone Serial No. 1247), fired on 30 January 1953, impacted 70.61 meters right and 6,629.6 meters short of the target, after 165.8 seconds of flight. Propellant shutoff occurred four seconds prematurely, causing the range correction system to operate at an improper time. An extra high trajectory also contributed to the shortness of range. After 23 seconds of flight, the missile was 200 meters above the standard trajectory. This was to be the largest deviation from a standard pitch program of any of the 14 rounds, but was not considered excessive as the elevation system was capable of compensating for at least 600 meters. CORPORAL EU-2 (Firestone 1251) was fired on 26 February 1953 and impacted 6,936 meters right and 84,072.3 meters long after 183.18 seconds of flight. The Doppler unit transmitted the fuel shutoff signal at the proper time, 54.05 seconds, but the missile failed to respond. It burned until the fuel was exhausted, accounting for the extremely long range. Evaluation of the flight data indicated that the Doppler shutoff signal from the ground was not acted upon by the shutoff circuitry of the missile Doppler transponder. Round 3 (Firestone 1261), launched on 23 March 1953, impacted 3,606.94 meters right and 1,351.2 meters long after 171.59 seconds of flight. In this round, the missile responded properly to the shutoff signal. The missile achieved a satisfactory flight and flew a trajectory that deviated only slightly from the standard. Of the remaining 11 round fired in the Engineer-User program for the Type I CORPORAL, only Round 8 on 13 August 1953 and Round 14 on 22 January 1954 were evaluated as complete failures. However, only Rounds 7, 12, 13, fired on 4 August 1953, 15 December 1953 and 12 January 1954 respectively, were fully successful. These three rounds averaged approximately 170 seconds of flight time each and achieved an average range of around 64 kilometers (40 miles). Miss-distance ranged from 25.6 meters right and 548.7 meters long for Round 7 to 12,960.7 meters left and 7, 799.8 meters short for Round 13. Round 4, on 14 May 1953, was shut off by Range Safety at 68 seconds because it entered a heavy overcast of clouds and was lost by the radar and optical trackers. It traveled only 23.7 kilometers. Round 5, 8 June 1953, was late in reaching range correction velocity -- 170 seconds instead of 116 seconds as programmed -- but flew for 183.5 seconds and impacted 45.22 miles from the launcher. An error in the shutoff equation sent to Round 6 during flight, on 7 July 1953, resulted in a large miss-distance, but the missile flew for 205 seconds and achieved a range of 82.3 kilometers. After Round 8 was fired, the central power system failed and the forward and aft sections of the missile broke apart at 30.5 seconds, terminating thrust. The aft section impacted 61.14 seconds later, 7.029 miles from the launcher. The nose section followed a shorter trajectory and impacted 2.34 miles from the launcher. Rounds 9 (1 October 1953), 10 (13 October) and 11 (27 October), all had large miss-distances due to malfunctions in the range correction systems, but otherwise were satisfactory tests. Ranges averaged more than 52 kilometers, and flight times averaged about 160 seconds. A dense cloud of smoke was seen pouring from the side of Round 14 just before takeoff. Post flight studies indicated that this vaporization probably was caused by an aniline leak, and that it had no apparent effect on the function of the propellant system. At takeoff plus one second, the missile yawed hard to the right. At nine seconds, it began to roll. It continued in a northeast direction for five more seconds, then impacted only 3,070.21 feet from the launcher, just 14.2 seconds after takeoff. Data indicated that a failure of the north servo system, due to intense vibration during the count-down and takeoff, caused the hard right yaw. The roll was caused by abrupt action of the south fin in response to the yaw-right error signal. An evaluation of this 14-round Engineer-User program indicated: (1) that accuracy of the azimuth system met military requirements; (2) that accuracy in range could not be determined; (3) that component malfunctions occurred approximately 54 percent of the time; (4) that the majority of the malfunctions occurred in the missiles; (5) that malfunctions in components during preparations for missions caused excessive increases in preparation times, and (6) that operating personnel for the CORPORAL system would have to be extremely well trained. After the firing of E-U Round 14 on 22 January 1954, the Engineer-User team suspended firings for a few months. In March 1954, the Jet Propulsion Laboratory conducted a school on the CORPORAL system, attended by 14 E-U personnel including officers, enlisted men and civilians. The course continued for three months and covered all aspects of firing and check out of the missile. E-U Rounds 15 and 16 were fired jointly by the Engineer-User team and JPL personnel in May 1954. In June 1954, a high altitude shoot employing extensive instrumentation for the Ballistic Research Laboratories was highly successful. From August until November 1954, at the request of the Chief of Ordnance, the E-U team conducted various climatic tests with the CORPORAL missile. One phase involved extreme cold and extreme heat, ranging from 60 degrees below zero to 180 degrees above zero, Fahrenheit. The other phase involved temperature variations and humidity tests. These E-U tests were conducted in addition to the JPL firing schedule and resulted in extra efforts on the part of firing crews, who used the same check out equipment for both regular firing and the climatic tests. Field Forces Program Late in 1953, after troops had been trained at the Guided Missile School at Fort Bliss, Texas, three CORPORAL Field Artillery Missile Battalions -- the 246th, 247th and 259th -- were activated. These units were still receiving items of basic equipment as late as mid 1954, when field firing operations were under way at Red Canyon Range Camp on White Sands Proving Ground. Initial flight tests in the Field Forces program were considered unsatisfactory for a variety of reasons. A fact finding conference was held at Fort Bliss on 29 June 1954. It was attended by representatives from WSPG, Fort Bliss, the Office of the Chief of Ordnance, Redstone Arsenal, Jet Propulsion Laboratory, Firestone and Gilfillan Brothers. A committee was appointed to establish the facts and make recommendations to the agencies involved. This committee determined that supplies of spare parts were deficient and that usable information about the CORPORAL system was not being distributed freely to those having a need for it at the lower operating levels. Over a period of time, these difficulties were rectified. JPL began publication of a biweekly newsletter for the exchange of pertinent information among the contractors, training schools, user troops, test agencies and administrative organizations. The committee produced detailed instructions concerning operating and maintenance procedures, resulting in standardization in all phases of the program. An office for technical consultants was opened and staffed at Fort Bliss, to provide direct engineering field service and consultation for user units. Late in 1954, the 259th Field Artillery Missile Battalion fired four successful training rounds in the Field Forces program at Red Canyon Range Camp, on White Sands Proving Ground. In January 1955, the 259th was deployed to Europe with full Type I CORPORAL field equipment. It was accompanied by an Ordnance support company. Early in 1955, the British government decided to integrate the CORPORAL missile into its field program, providing a missile potential until such time as the British could design, test and produce similar weapons of their own. As a result, 113 CORPORAL missiles and several sets of guidance and handling equipment were ordered for the British Army. British troops were brought to Redstone Arsenal and the Fort Bliss - White Sands area later in 1955 for technical training. Field firing experience for these troops was scheduled at White Sands Proving Ground. Conclusion of Type I Program Starting in 1954, a new type of CORPORAL missile had begun to replace the Type I system among deliveries from the Firestone plant at Los Angeles. Phasing of this newer design into the flight testing program began, although a number of Type I rounds were still available. These subsequently were used by Jet Propulsion Laboratory, the Army Field Forces and the Chemical Warfare Service as test vehicles for the new Type II program. The last Type I round was fired at WSPG in December 1954. Manufacturer: Sperry/JPL. Apogee: 50 km (31 mi). Liftoff Thrust: 89.000 kN (20,007 lbf). Total Mass: 5,400 kg (11,900 lb). Core Diameter: 0.76 m (2.49 ft). Total Length: 14.00 m (45.00 ft). Model: Corporal Type 2. Year: 1953. Country: USA. Second prototype of Corporal Missile US Army Fact Sheet Type II Corporal As the testing program had continued from 1951 through 1952, many shortcomings of the Type I CORPORAL system had become apparent. Deficiencies became particularly obvious as the participating agencies began planning for the Army's tactical utilization of the system. But solutions were made possible by the increased knowledge of the flight environment and the determination of the effects of vibration on components, achieved as the program progressed. The resulting redesign of components led to development of the Type II (XM2E-I) CORPORAL. In January 1953, an Army Ordnance Corps contract, ORD-437, was awarded to Firestone for production of 465 of the new Type II missiles. At the time, the Type II components had not yet been fully defined. But by the end of the year 1953, JPL had given most of the information to the contractor. A significant change from the Type I system was in the Doppler unit. The operating frequency was increased from the fixed-tuned DOVAP instrumentation frequency of 38 megacycles to the UHF region, using a tunable missile transponder with an input frequency range of 450 to 480 megacycles. Minor improvements were incorporated in the radar link to provide better tactical operation. The launcher, erector and servicing platform also were redesigned for the Type II system. Originally, the CORPORAL missile was intended as a general test vehicle for the study of guided missile problems. Its design was undertaken at a time when most phases of the science of missile aerodynamics were relatively unknown. The design progressed through a series of configurations, and with each new configuration the accuracy with which aerodynamic data could be predicted showed improvement. The CORPORAL missiles fired after Round 11, on 10 October 1951, all had essentially the same aerodynamic configuration. The two standard versions, Type I and Type II, differed principally in that Type I carried four DOVAP antenna spikes mounted on two farings in the yaw plane of the missile. As part of the redesign for Round 11, the 96-inch long nose shape used in earlier CORPORAL rounds was abandoned, and a 68.5-inch nose shape was adopted. This change was effected in order to reduce overall missile length. In the absence of adequate flight instrumentation directed specifically toward the measurement of aerodynamic characteristics of the CORPORAL missile, data obtained from individual rounds were of limited usefulness. However, data and experience gained from firing a large number of rounds were used to determine drag coefficients and atmospheric densities. Estimates were based on published meteorological data and pre shoot and post shoot data obtained at WSPG. DOVAP measurements gave information on position in space, velocity and acceleration. The basic specification for the CORPORAL propulsion unit required that the rocket motor be capable of delivering 20,000 pounds of thrust for approximately 60 seconds. A liquid cooled motor was selected for development. The Type II fuel-cooled motor developed 20,000 pounds of thrust for durations up to 64 seconds and utilized compressed air to pump a propellant combination of stabilized fuming nitric acid (SENA) as the oxidizer and aniline-furfuryl alcohol-hydrazine mixture as the fuel. Selection of this propellant system and development of the axially cooled rocket motor eventually proved to be one of the major achievements of the CORPORAL program. The motors used in all the Firestone rounds were static tested on facilities at WSPG before being flight tested with the other missile components. Type II Firing Program Concerning the first firings of the Type II CORPORAL rounds at White Sands Missile Range, the JPL report said: "The first Type II prototype round was flown on 8 October 1953. This missile was a Type I with components modified by this Laboratory. This round impacted 234 meters short and 116 meters right, well within the tactical CPE." The first ORD-437 missile manufactured by Firestone was flown on 28 October 1954, just one year after the first prototype operation. This round impacted 43 meters short and 169 meters right of the target. During the interval between the prototype and production Type II firings, most of the flights were Type I rounds containing nearly complete Type II modifications. These rounds used electronic components manufactured by Gilfillan, whereas, in Type I, Firestone had contracted directly with various electronic manufacturers for flight electronic equipment. In Type II production, all of the missile electronic units were procured through Gilfillan. On an ORD-468 contract, Gilfillan also undertook improvement of both the ground and flight electronic equipment. The Jet Propulsion Laboratory provided technical advice and consultation and performed evaluation testing in the field. The Jet Propulsion Laboratory fired 57 Type II rounds between the first ORD-437 firing on 28 October 1954 and the end of the Calendar Year 1955. This contractor program was scheduled to continue in 1956. The Engineer-User team fired 21 Type II rounds between February and December 1955. This program also was incomplete as of the end of 1955 and was scheduled to continue during the following year. Meanwhile, both CORPORAL R&D rounds and CORPORAL Test Vehicle rounds were being fired by project personnel at White Sands Proving Ground. The Type II evaluation program was expected to be completed by mid 1957. In the fall of 1954, the Engineer-User team and Jet Propulsion Laboratory worked together on four missile firings which comprised Operation Sandspit. This program was both an evaluation of Type II procedures testing and check out equipment, and a training exercise on the Type II missile. After a limited amount of training, the E-U team members in turn instructed other E-U personnel in Type II operational procedures. A complete Type II system arrived in February 1955 and the E-U team then proceeded with thorough proof tests of the Type II equipment. The team also undertook the check out of three Type II rounds which had been scheduled for climatic experimentation by the WSPG Electro-Mechanical Laboratories (EML). Although some formal classroom training was conducted, a new Engineer-User team learned mostly through actual work on the missiles. The aggregate CPE for all of the production Type II rounds fired by Jet Propulsion Laboratory was 350 meters, as compared with the desired CPE of 300 meters. Other rounds were fired for special experiments, but no attempt was made to record those flights for accuracy because accuracy was only incidental to their operations. While aborted flights would be considered as penalties in tactical operations, one evaluation was made with "aborts" not counted and thus showed a much better accuracy record for the systems. In this evaluation, the aggregate CPE for all of the production Type II rounds fired by JPL was only 150 meters. Future Projection By the end of Fiscal Year 1955, the total dollar value of all CORPORAL contracts which had been executed was $199,423,694. This included $39,470,388 in the Research and Development program, $159,248,719 in the Industrial program, and $704,587 in the Field Service program. However, even though the contracts had been awarded by 30 June 1955, actual delivery of many items contracted for in the Industrial and Field Services programs was not scheduled until the Calendar Year 1956. Completion of some contracts awarded in the Research and Development program also was scheduled for 1956 or later. As the Calendar Year 1955 ended, the Army was preparing to send several Type II CORPORAL battalions to Europe to replace the 259th Field Artillery Missile Battalion, which was still equipped with the Type I CORPORAL. Meanwhile, the Type II evaluation program was scheduled to continue at White Sands Proving Ground, with firings planned both by Jet Propulsion Laboratory and the Engineer-User team. Training firings by Army Field Forces units and by British troops also were scheduled at WSPG for 1956. Plans for improving the Type II CORPORAL were being made. It had been decided to simplify equipment and operations wherever possible, to redesign the electronic components, and to replace the batteries and motor generator with an air turbines alternator. Studies also were being initiated to determine design improvements that would increase the systems's reliability and reduce its vulnerability to electronic countermeasures.
Model: MGM-5A. Country: USA. Department of Defence Designation: MGM-5A. Popular Name: Corporal. Alternate Designation: SSM-A-17 / M2A1.
Manufacturer: JPL/Firestone. Model: MGM-5B. Country: USA. Department of Defence Designation: MGM-5B. Popular Name: Corporal. Alternate Designation: SSM-A-17 / M2.
Manufacturer: JPL/Firestone. Corporal Chronology 1944 January 1 - Launch Vehicle: Corporal.
Bibliography and Further Reading
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