Traditionally, large missiles have been controlled in post boost flight by hydraulic control actuation systems. Hydraulic systems possess the advantages of high stiffness, high response and high torque capability. They have the disadvantages, however, of being expensive and bulky. This paper describes a pneumatic control system that has been developed for a large ballistic missile as part of the Simplified Inertial Guidance Demonstration (SIG-D) program at MIRADCOM. The design offers the potential for a significant cost reduction over a hydraulic system to meet the control and stabilization requirements for a missile of this type. The missile itself utilizes a strapdown inertial guidance system and digital processing for sensor signals and autopilot compensation. It is seen that the processing, autopilot design, and actuation system performance are intimately coupled, as characteristics unique to each subsystem drastically affect the performance of every other one. The basic control system design philosophy, mechanical design, modelling performance, and influence on the total missile system performance is discussed. Typical data on the pneumatic system is presented. (Wassmann)
A pneumatic actuation system for a large balistic missile
Ein pneumatisches Antriebssystem fuer einen grossen ballistischen Flugkoerper
FLUID POWER SYMP. 5TH INTERNAT. BHRA-SYMP. ; Sep ; C-20
1978
20 Seiten, 16 Bilder, 3 Tabellen, 5 Quellen
Aufsatz (Konferenz)
Englisch
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