Free-falling body verification device for drag-free spacecraft
A free-falling body verification device for a drag-free spacecraft comprises a spacecraft simulation device ( 1 ), used for carrying out free-falling body motion on the ground; an inertial sensor or accelerometer ( 2 ), used for measuring the residual disturbance acceleration of the spacecraft simulation device ( 1 ); an attitude sensor ( 3 ), used for measuring attitude parameters of the spacecraft simulation device ( 1 ); a drag-free controller ( 4 ), used for processing the residual disturbance acceleration and the attitude parameters so as to obtain a feedback control signal; and a propeller ( 5 ), used for generating thrust action applied on the spacecraft simulation device ( 1 ) under the control of the feedback control signal, so as to enable the spacecraft simulation device ( 1 ) to overcome the residual disturbance of the external environment and maintain the attitude. The space operating environment is simulated by means of the free-falling body motion of the spacecraft on the ground within short time; the inertial sensor or accelerometer ( 2 ), the attitude sensor ( 3 ), the drag-free controller ( 4 ), and the propeller ( 5 ) are combined, so that the performance and function test verification for a space drag-free aerospace system is realized in the technical ground environment within short time.
1. A free-falling verification device for a drag-free spacecraft, the device comprising:
a) a spacecraft simulator ( 1 ) operating to simulate free-falling motion on ground;
b) a plurality of inertial sensors/accelerometers ( 2 ) each operating to measure residual acceleration and disturbance acceleration of said spacecraft simulator ( 1 );
c) an attitude sensor ( 3 ) operating to measure attitude of said spacecraft simulator ( 1 );
d) a drag-free controller ( 4 ) operating to process said residual acceleration and said disturbance acceleration measured by said inertial sensor/accelerometer ( 2 ), and said attitude measured by said attitude sensor ( 3 ) whereby obtaining a feedback control signal; and
e) one or more thrusters ( 5 ) each operating to generate force under control of said feedback control signal, and to apply said force on said spacecraft simulator ( 1 ) whereby enabling said spacecraft simulator ( 1 ) to resist residual disturbance from external environment and to maintain an attitude thereof.
2. The device of claim 1 , wherein as a number of said inertial sensors/accelerometers ( 2 ) is greater than 1, one of said inertial sensors/accelerometers ( 2 ) is disposed at a centroid of said spacecraft simulator ( 1 ), and the others are distributed at positions of said spacecraft simulator ( 1 ) other than said centroid.
3. The device of claim 1 , wherein said attitude sensor ( 3 ) is a gyroscope.