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M-3S, a Three-Stage Solid Propellent Rocket for Launching Scientific Satellites

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M-3S, a Three-Stage Solid Propellent Rocket for Launching Scientific Satellites The Space Congress® Proceedings 1980 (17th) A New Era In Technology Apr 1st, 8:00 AM M-3S, A Three-Stage Solid Propellent Rocket for Launching Scientific Satellites Ryojiro Aklba Professor, Institute of Space and Aeronaut lea I Science, The University of Tokyo Tomonao Hayashi Professor, Institute of Space and Aeronaut lea I Science, The University of Tokyo Daikichiro Mori Professor, Institute of Space and Aeronaut lea I Science, The University of Tokyo Tamiya Nomura Professor, Institute of Space and Aeronaut lea I Science, The University of Tokyo Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Aklba, Ryojiro; Hayashi, Tomonao; Mori, Daikichiro; and Nomura, Tamiya, "M-3S, A Three-Stage Solid Propellent Rocket for Launching Scientific Satellites" (1980). The Space Congress® Proceedings. 3. https://commons.erau.edu/space-congress-proceedings/proceedings-1980-17th/session-5/3 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. M-3S, A THREE STAGE. SOLID PROPELLANT ROCKET FOR LAUNCHING SCIENTIFIC SATELLITES Dr. Ryojfro Akfba, Professor Dr.. Tomonao Hayashi, Professor Dr. Daikichlro Morf, Professor Dr. Tamlya Nomura, Professor Institute of Space and Aeronaut lea I Science The University of Tokyo ABSTRACT The Institute of Space and Aeronautical successf u I I y orb I tedl the th i rd sc \ ent i f i c Science, University of Tokyo has developed satellite "TAIYO" of 86 kilogram weight in the Mu series satellite' launchers. M-3S as February 1975. TAIYO 1 was designed for con­ the newest version of Mu family is a three ducting synthetic observations o^n aeronomy in stage solid propel I ant rocket in which TVC the magnetosphere, themnosphere and mesosphere systems are Introduced! first in the first- with a special reference to the solar- stage as well as the second stage. ' The terrestrial Interactions through radiation first flight test of M-3S has been success­ and particles. The launch of the third M-3C fully conducted on February 17th 1980. made in February 1976 was unsuccessful and Following to the historical remarks on the failed to orbit the fourth scientific deve1opment of Mu seni es , veh I c I e descrIp- satellite CORSA (Cosmic Radiation Satellite), tion, principles of the flight procedure which aimed at cosmic heavy primaries and X-­ including guidance and control and results ray astronomy observations. of.the flight test are reviewed. Further improvement of Mu is programmed concerning As the third generation of the Mu-rocket the to future sc i ent i f I c space observat i on, ISAS developed the M-3H vehicle, which was particularly to the interplanetary probe designed to have a more pay load weight capa- PLANET-A aiming at optical (UV) observation- bility than M-3C by the thrust augmentation of Halley f s Comet. furnished by extending the first stage motor. The first flight test of M-3H was made in HISTORICAL REMARKS February 1977, and a technological test satellite "TANSEI-3" was put Into a semi-polar The ISAS is responsible for the developments orbit. Following this test scientific satel­ of satellite launch vehicles and scientific lites "KYGKKG" and "JIK!KEN" were put Into satellites. The first generation of the orbit by M-3H f s In February and September 1978, satellite launch vehicle planned by the ISAS respectively. "KYOKKO 11 was designed for was M-4S. In February 1970 Lambda-45, that studies on aurora and related phenomena on a was designed as a simulation test vehicle semi-polar orbit, and "JIKIKEN" was designed for the development of M-4S, injected the for studies on wave-particle interaction in Japan's first satellite "OHSUMI" into an magnetosphere on a highly eccentric low orbit.. Following the launch of a technology inclination orbit. Both of them have partici­ test satellite "TANSEI" in February 1971, M- pated in the International Magnetosphere 4S vehicles successfully launched two full Study (1976-1979). fledged scientific satellites "SHINSEI" in September 1971 and "DENPA" in August 1972. in February 1979 CORSA-b was launched by M-3C- 4 Into a circular orbit to supplement the M-3C, the second generation of Mu series? is former failure of CORSA. This satellite named a three-stage solid propel I ant rocket designed "HAKUCHO" Is serving as a monitor for new to inject a scientific satellite around 90 kg, celestial X-ray sources and their burst Its another feature is the introduction of phenomena* the flight control system utilizing IfTVC (Liquid Inj ecti on Thrust Vector Cont roI) and N-3S Is the fourth generation of Mu series sidejets for the second stage. The first satellite launch vehicles. It is an improved . test of M-3C launch vehicle was successfully version of M-3H and Is provided with a flight made in February 1974 and a technology test control capability during the burning phase satellite "TANSEI-2" of 56 kilogram- weight of the first stage. The first test launch CM- was put into an orbit. The second M-3C 35- 1/MS-T4) has been conducted on Fab, 17*1980. §-43 VEHICLE DESCRIPTION command system, radar transponders, a timer and other instruments around its peripheral section. Configuration of M-3S is shown in Fig. I. A At the peripheral section of the instrumenta­ summary of the stage dimensions and engine tion bay 2 solid propellant spin motors are data of M-3S is given in Table I. The total installed. Each of them has two nozzles direct­ length is 23.8 m, maximum diameter is 1.4 m, ing to opposite sides, one for accelerating lift-off weight is 49.5 ton and the total spin, the other for decelerating it. The amount of lift-off thrust is 246 ton incilud- latter nozzle is closed until the spin rate ing thrust of 8 strap-on boosters. comes up to 2 rps which is detected by gyro system. LITVC and side jet modules are equip­ The first stage motor named M-13 is composed ped around the nozzle of M-22. LITVC for the of 4 segments loaded with polybutadiene base second stage is a similar to that of the first solid propellant. The motor case material of stage but injection valves are of on-off type M-13 is a maraging steel with nominal tensile instead of the proportional type. The side jet strength of 200 kg/mm2 . A couple of shaped is an H202 monopropellant rocket of 8 kgf charges are provided at both sides of the thrust. In each side jet module, 4 thrusters top segment to destroy the motor for f I ight are placed directing 2 by 2 to the opposite di­ safety. 8 strap-on boosters making 4 pairs rection. 4 modules installed evenly around the are attached to the first stage for the pur­ nozzle close to its exit produce thrust circum- pose of minimizing the dispersion caused by ferentially on both directions. Those 16 side disturbances in the early phase of launching jets are efficiently used in various modes, as well as enhancing performance. The exposed high thrust mode, low thrust mode (only 8 span of ta i I fin is taken as about 2/3 of the thrusters are operative In this mode), spin former Mu (M-3H)to reduce the aerodynamic mode and three axes mode, in accordance with stability margin so as to make TVC effective. the progress of flight phase. TVC injectant of FVC equipments are located around the nozzle 20 & and the side jet propellant of 20 Jl are and a solid motor for roll control (SMRC) is loaded for the second stage control. The M-22 attached to the tip of each fin. motor has also destruction device for safety at the center of its forward plate. The nose TVC employed in M-3S is so called LI TVC in fairing is made of FRP honeycomb sandwich which Freon II4B 2 is used for injectant. 8 shell covered by a thin cork layer for heat proportional type injection valves, actuated protection. by electro-hydraulic device are installed one to every octant surrounding the nozzle. A spherical third stage motor M-3A Is mated to Simple blowdown N 2 pressurization is adopted the second stage fastened with a marman clamp to both the hydraulic power and Freon feed. on an interstage structure of a truncated cone The Freon of 120 £ is loaded in 15 tanks. A which is opened Into 4 petals after the comple­ tank of the same configuration is used for the tion of separation. The case material of M-3A actuator oil accumulator. Is Ti alloy, and M-3A Is also loaded with polybutadiene base propellant. Electrical There are electronic instruments, rate gyros interface of M-3S is illustrated In Fig. 2. and telemetry systems for the first stage also Most of the events such as Ignition and separa­ inside the fin shroud. The interstage struc­ tion are conducted by the command from an ture between the first and the second stage electronic programming timer (EPT). is composed of 6 triangular trusses which are opened after separation by the coil springs FLIGHT SEQUENCE AND PRINCIPLE OF GUIDANCE AND set at the hinges of the trusses. CONTROL An SMRC is in principle a device tnat is a Fig. 3 sketches flight sequence of M-3S-I solid propellant gas generator equtpped with schematically, and Table 2 shows the main a hot gas valve which alternatively opens or sequence of events.
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