An adaptive load relief control system for a SATURN type vehicle which significantly reduces aerodynamically induced structural loads without incurring excessive velocity dispersions has been studied. This control system utilizes pendulous accelerometers to measure the angle between the total vehicle acceleration vector and the vehicle body. This measurement is used to fly the vehicle along the nominal trajectory to minimize velocity dispersions. However, if unusually high values of wind velocity are encountered, the system will cause the vehicle to turn into the wind to reduce the lateral structural loads. Results of an anal6g computer study show that the adaptive system can reduce aerodynam3cally induced peak structural loads as much as 50 percent under those encountered using conventional control techniques. relief is used only when required, velocity dispersions are held to a minimum.
An Adaptive System for Load Relief and Accurate Control of Launch Vehicles
1st AIAA Annual Meeting ; 1964 ; Washington, D.C., United States
1964-01-01
Miscellaneous
No indication
English
A MODERN LOAD RELIEF GUIDANCE SCHEME FOR SPACE LAUNCH VEHICLES
Springer Verlag | 2024
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