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The Terrier a Capsule History of Missile Development

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The Terrier a Capsule History of Missile Development THE TERRIER M. R. Kelley a capsule history of missile developm The history of the Applied Physics the canine breeds of relatively small vehicle that incorporated a device for Laboratory between mid-1948 and size, aggressive and tenacious by na­ roll stabilization could be tested. mid-1956 was characterized by sig­ ture, but readily controlled by their Neither test provided the desired data nificant technological achievement, masters. This name was approved by because of malfunctions in the tele­ an outstanding part of which was the the Chief of the Bureau of Ordnance metering equipments, cause un­ successful development of the missile on December 29, 1948. known. named Terrier I. This was the first Development of Terrier presented In October 1948, a third test sea-going antiaircraft guided missile no major problem in propulsion be­ having these same objectives pro­ in world history. The Laboratory had, cause enough was known of rocket duced good roll data. Confirmatory prior to that time, pursued an explor­ propellants to afford confidence that results were also obtained in another atory research and development pro­ it could attain the speed, altitude, flight test a month later. Shortly gram that resulted in, among other and range demanded. However, there thereafter flights of two modified things, a supersonic-missile, test­ were other problems. Even though STV-3's, which were intended to be vehicle configuration. The Navy de­ roll stabilization- a prerequisite of roll-stabilized, proved unsuccessful cided to adapt it to tactical use as good beam-riding - had been because of an apparent electrical a rocket-propelled surface-to-air mis­ achieved earlier by both subsonic power failure in one case and, in sile for the Fleet. This decision was and supersonic test models, and satis­ the other, the occurrence of large communicated to the Guided Missiles factory beam-riding had already been acceleration forces at end of boost, Committee of the Department of demonstrated, unexpected difficulties which were shown III post-flight Defense Research and Development were encountered in the first two analysis to have been present also in Board on June 11, 1948. Dr. R. B. STV*-3 flight tests (April and July, two previous STV-3 tests. Such Kershner of APL proposed the name 1948 ) . These tests had among their forces had not been encountered in "Terrier" for the new missile, after principal objectives the measurement tests of the STV-2's. After careful of roll moment and determination of study of the differences between the the damping coefficient, information two vehicles, the booster-missile at­ These historical notes are adapted from a chapter on the Terrier missile prepared by that was urgently needed before a tachment was redesigned to mini­ Rear Admiral M. R. Kelley, U.S. 'avy mize the possibility of a collision (Ret. ) for inclusion in a history of the Applied Physics Laboratory. * Supersonic test vehicle. between it and the missile's tail 18 APL Technical Digest compartment and nozzle extension poration for the manufacture and at the time of booster separation. tube during separation. But the first delivery of 50 prototype units spread This insured that the missile would flight test of this attachment (April over Lots 1 through 4. Pending be in a position to receive guidance 1949) showed that it had not re­ delivery of the first Lot 0 missiles, signals from the radar. It was obvi­ solved the difficulty ; the missile did tests of various models of the STV-3 ous that such an accommodation not roll-stabilize, and a violent were continued, these tests varying would only accidentally, if ever, disturbance occurred at separation, in their objectives as determined by occur in a tactical situation at sea. knocking out half the telemetering the problems under investigation. In another respect, also, these channels. Further investigation iden­ tests were not representative of tified three acceleration forces oper­ Guidance Problems Investigated guidance conditions in actual serv­ ating during the boost and separa­ With completion of successful ice afloat. There the radar pulses tion stage: ( 1) acceleration at boost, tests of the zero-length launcher and directed at a high-speed aircraft which forced the 250-pound sus­ the achievement of roll stabilization would be refl ected randomly from tainer charge rearward against the in the STV-3, emphasis was more different surfaces or features of the after face of the case; ( 2 ) decelera­ and more centered on solution of target and, in combination with tion at end of boost, which thrust the guidance problem. This was at random refl ections from the sea, the charge hard against the forward first a matter of beam-riding p er­ would ca use the beam to jitter. No face of the case ; and (3) igniter formance. The very modest effort on beam-riding guidance system could pressure at ignition, which drove the an interferometer homing system be considered acceptable until a de­ charge solidly against the after face that had been started in 1948 was termina tion had been made that this of the case, producing the damaging viewed only as a possible alternative jitter did not adversely affect the shock. Accordingly it was decided to in case satisfactory beam-riding guid­ missile's accuracy in guided flight. immobilize sustainer charges in all ance should prove unattainable. The opportunity was taken, there­ subsequent STV-3's, a "fix" that There had been early tests, begin­ fore, in the STV- 2 test in April, proved highly effective in later tests. ning with two flights of subsonic 1949, marking the first successful control test vehicles in 1947 and use of a capture beam, to test also Meanwhile, during the above tests followed by two successful STY the missile's ability to ride a jitter­ extending over a period of 18 flights in 1948, which inspired con­ ing beam. Jitter was in iected into months, progress was made in two fidence that beam-riding guidance the beam at the radar source so as other areas. A so-called "zero­ could be made effective for tactical to simulate that expected in a tacti­ length" launcher was checked out employment afloat. In these tests, cal situation. Another "first" was satisfactorily in four of the above­ however, the radar guidance beam achieved when the missile demon­ cited tests, and capture of the mis­ had been fixed in space and the strated in this test that it could ride sile into the guidance beam at end­ test missile was so launched as to a jittering beam with acceptable of-boost was successfully accom­ be in, or close to, the beam axis accuracy. plished in the flight of an STV-2. Prototype Testing Begins Following the Navy's decision III the spring of 1948 to make a tactical missile of the STV-3, plans were formulated to reach the final design of the new missile through tests of a succession of prototype missiles designated Lots 1, 2, 3, 4, 5, and 7. Lots 6 and 8 were earmarked for development of a higher perform­ ance missile at a later date, to bene­ fit from the experience with the earlier lots and from advances in the state of the art. Confident that a tactical version of the S TV-3 could be achieved, the Navy early contracted with the Consolidated Vultee Aircraft Corporation for pro­ duction of a pre-prototype Lot 0 consisting of fifteen missiles. Late in 1949, the Bureau of Ordnance (BuOrd) declared the Terrier to be in the production prototype stage and contracted with the above cor- Terrier missiles (BT-3) bein!! fired from the deck of the USS Norton SOllnd. .lui), -August 1965 19 Meanwhile research and develop­ ment in beam-riding guidance had been actively carried on with a view to improving the sensitivity of the missile response to control correc­ tions for guidance errors, both near the surface and at altitude. Obvi­ ously, the aerodynamic control sur­ faces would have to be moved through greater angles in the rari­ fied atmosphere at high altitude than in the denser atmosphere near the earth's surface in order to cor­ rect promptly any off-beam error. A red esign of the control system for Test firing of the Terrier missile at China Lake. California. the STV-3 had been completed near the end of 1948, the effective­ ness of which was impressively system for installa tion in the ship, cil In emergency seSSIOn- In the demonstrated in a flight test about plus the elements of an approxi­ absence of Russian representatives­ a year later when guidance sensi­ mately identical system for use at adopted a resolution before the day tivity was changed in flight for the NOTS. The latter system, obviously, was out condemning this unprovoked first time, being increased by a fac­ did not need to have the capabilities aggression, and three days later tor of six. The missile responded in the weapon-direction, fire-control, adopted a second resolution recom­ promptly by closing to within 2 mils a nd la unching subsystems that would mending that members of the of beam center, where it remained be required in the face of the un­ United N ations furnish such assist­ more than twice as long as any predictable motions of the ship at a nce to the R epublic of South Korea previous Bumblebee beam rider. sea. as might be necessary to restore the This signaled an important advance By this time progress made toward status quo in Korea. In compliance in beam-riding accuracy. Other less a rocket-propelled tactical missile, President Truman a t once directed obvious factors also had to be taken plus the general advance on all the U .S.
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