Spacecraft thermal shock suppression system
AssigneeThe Boeing Company
InventorsGrant Wang, Richard Chiang
Life of this patent
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Abstract
A satellite system includes a solar wing moveably connected to a satellite central body. A sensor, also coupled to the satellite central body, detects the movement of the body and generates a rate signal based on that movement. Additionally, an actuator, which controls momentum, is coupled to the satellite central body with maximum torque along the thermal shock axis. Subsequently, a rate-dominated thermal shock suppression controller, which is coupled to the satellite central body, receives the rate signal from the sensor to control the actuator.
Claims28
A satellite system comprising:
- a satellite central body having a thermal shock axis, such that torque applied along said thermal shock axis suppresses thermal shock;
- a solar wing moveably connected to said satellite central body;
- a sensor, coupled to said satellite central body, for detecting movement rate of said satellite central body and generating a compensation signal based on said movement rate;
- an actuator, coupled to said satellite central body with torque substantially maximized along said thermal shock axis of said satellite central body, for adjusting momentum of said satellite central body;
- and
- a thermal shock suppression controller for receiving said compensation signal and controlling said actuator as a function of said compensation signal, said thermal shock suppression controller further maintaining attitude of said satellite central body.
A control method for a satellite maintaining a pointing attitude, said method comprising the steps of:
- sensing a change in movement of a satellite central body, said change in movement taking the satellite out of the pointing attitude;
- estimating a compensation signal to return the satellite to the pointing attitude;
- operating a situational-stable rate-dominated high-bandwidth controller in response to said compensation signal;
- and
- activating an actuator in response to said situational-stable rate-dominated high-bandwidth controller, thereby returning the satellite to the pointing attitude.
A satellite momentum system comprising:
- a satellite central body;
- an actuator coupled to said satellite central body with maximum control authority along a thermal shock axis;
- and
- a control system for controlling momentum acting on said satellite central body, whereby said control system controls said actuator.
Dependencies are inferred from the claim text.