Full-object verification platform and working method of satellite magnetic detection and control system

A technology for verifying platforms and satellites, applied in testing/monitoring control systems, general control systems, control/regulation systems, etc., can solve the problems of not being suitable for micro-satellites, large technical difficulties, economic costs, high costs, etc., and achieve economical research and development Effects of cost, high simulation fidelity, and high simulation accuracy

Inactive Publication Date: 2011-02-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] At present, the full physical simulation test and verification of the satellite attitude determination and control system on the ground has great technical difficulty and economic cost; Physical verification in a large magnetic simulator, the high cost is not suitable for cheap tiny satellites

Method used

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  • Full-object verification platform and working method of satellite magnetic detection and control system
  • Full-object verification platform and working method of satellite magnetic detection and control system
  • Full-object verification platform and working method of satellite magnetic detection and control system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0081] Example 1: large pitching maneuver

[0082] From Figure 5 (a) It can be seen that there is an overshoot of about 5 degrees from -165 degrees to 0 degrees, and the maneuvering time is 30s. Steady-state curves such as Figure 5 (b) shown.

[0083] The above-mentioned maneuvering curve is partially enlarged at about 0 degrees, such as Figure 5 (b) shown. Depend on Figure 5 (b) It can be seen that the control overshoot is less than 5 degrees, and it takes 40 seconds to finally stabilize. In a stable state, the angle control error is less than 0.5 degrees, and the angular velocity is less than 0.01deg / sec.

Embodiment 2

[0084] Example 2: Big handstand maneuver

[0085] From Figure 6 (a) It can be seen that from +165° handstand maneuver to 0°, there is an overshoot of about 5°, and the maneuvering time is 30s. When approaching the steady state, the local amplification curve is as follows Figure 6 (a) shown.

[0086] The above-mentioned maneuvering curve is partially enlarged at about 0 degrees, such as Figure 6 (b) shown. Depend on Figure 6 (b) It can be seen that the control overshoot is less than 5 degrees, and it takes 40 seconds to finally stabilize. In a stable state, the angle control error is less than 0.5 degrees, and the angular velocity is less than 0.01deg / sec.

Embodiment 3

[0087] Embodiment 3: Steady state maintenance

[0088] The steady-state maintenance test curve is as follows Figure 7 shown. From Figure 7 It can be seen that the air bearing table can be kept at a certain point, and the angular error is <0.1 degree and the angular velocity is <0.01 degree in the steady state. The small wave on the right side of the figure is the change process of the comprehensive simulation platform under the condition of small human disturbance, which reflects the ability of the comprehensive simulation platform to resist disturbance.

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Abstract

The invention discloses a full-object verification platform and a working method of a satellite magnetic detection and control system. The platform comprises a mono-axial air floated platform, a platform computer system, an angle measuring system, a communication computer, a mini-type magnetic simulator, a satellite magnetometer, a satellite computer and an environment simulation computer. In the method, the mono-axial air floated platform is used for simulating a small satellite in space; the environment simulation computer and the mini-type magnetic simulator are used for generating an on-track magnetic field; the real satellite magnetometer and the real satellite computer sense the on-track magnetic field and complete attitude measurement and the generation of a control instruction; the platform computer computes a magnetic moment required to be output according to an control moment instruction forwarded by the communication computer and the local geomagnetic numerical value output by the magnetometer on the platform and then sends the control instruction to a magnetic moment machine; and the magnetic moment machine and the local geomagnetism act to form an actual control moment so as to control the air floated platform be stabled at a certain angle or to move at a large angle. The full-object verification platform and the working method are low in cost, high in the fidelity of emulation verification and precise in control.

Description

technical field [0001] The invention relates to an all-physical verification platform and working method of a satellite magnetic measurement and magnetic control system, and belongs to the technical field of the verification platform and working method of a pitch circuit of a micro-satellite magnetic measurement and magnetic control system. Background technique [0002] The microsatellite control system often adopts the configuration scheme of "magnetometer + magnetic torque device + bias momentum wheel", which has the characteristics of low cost and high reliability. A better control method using this configuration scheme is: the magnetometer is used as the attitude sensor, the bias momentum wheel is used as the passive stabilization device of the star, and the three-axis magnetic torque device is used to realize the small-angle stability and stability of the satellite pitch circuit. Large maneuver control and chapter precession control, this control method has the advantag...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/00B64G7/00
Inventor 郁丰程月华华冰熊智康国华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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