Spacecraft magnetic test sensor layout method and system based on near-field analysis method
By rationally arranging multiple magnetic acquisition and monitoring sensors on the equatorial plane of the spacecraft and adopting a sensor layout method based on near-field analysis, the problem of low accuracy in spacecraft magnetic moment testing was solved, achieving high-precision magnetic measurement and error reduction.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHANGHAI INST OF SATELLITE EQUIP
- Filing Date
- 2022-12-19
- Publication Date
- 2026-06-12
AI Technical Summary
In existing technologies, the sensor layout for spacecraft magnetic moment testing leads to reduced testing accuracy. In particular, the reduced sensor spacing in near-field layouts results in a lower signal-to-noise ratio and increased testing error, making it difficult to meet the requirements for high-precision magnetic measurements.
Several special sensor layout methods based on near-field analysis were employed, including a spacecraft permanent magnet moment, a stray magnetic moment testing line layout, and a three-component magnetic sensor layout. By rationally arranging multiple magnetic acquisition sensors and magnetic monitoring sensors on the spacecraft's equatorial plane, the distance ratio between the sensors and the spacecraft was ensured to meet 0.4.
It improves the accuracy of magnetic testing of spacecraft and reduces testing errors, especially for large cylindrical shells and combined spacecraft, avoiding eccentricity errors and improving the accuracy of magnetic control.
Smart Images
Figure CN116224177B_ABST
Abstract
Claims
1. A spacecraft magnetic test sensor layout method based on near-field analysis, characterized in that, Includes the following steps: Layout selection steps: Select a magnetic sensor layout method based on near-field analysis according to actual needs; Magnetic sensor layout steps: Lay out the magnetic sensors according to the selected magnetic sensor layout method; In the layout selection step, the spacecraft permanent magnet moment and stray magnetic moment test one-line three-component magnetic sensor layout is selected from the magnetic sensor layout. The spacecraft is placed upright on a non-magnetic turntable, and the support frame for carrying the sensor is placed at the east end of the spacecraft equatorial plane along the geomagnetic east-west direction through the center of the spacecraft equatorial plane. In the layout selection step, the spacecraft magnetic moment test cross-shaped three-component magnetic sensor layout is selected from the magnetic sensor layout. The spacecraft is placed upright on a non-magnetic turntable, and support frames for carrying the sensors are placed at the east end of the geomagnetic east-west direction and the south end of the geomagnetic north-south direction on the spacecraft equatorial plane, passing through the center of the spacecraft equatorial plane. In the layout selection step, the three-component magnetic sensor layout for ferromagnetic fixture calibration used in spacecraft magnetic testing is selected from the magnetic sensor layout. The ferromagnetic fixture is fixed on the non-magnetic turntable according to its installation position on the spacecraft. The support frame for carrying the sensor is placed on the equatorial plane of the virtual spacecraft along the east-west direction of the geomagnetic direction, passing the east end of the center of the equatorial plane of the spacecraft. In the layout selection step, the three-component magnetic sensor layout for stray magnetic moment testing in the spacecraft antenna array working mode of the magnetic sensor layout is selected. The spacecraft is placed upright on the air-floating platform, and the antenna arrays on both wings of the spacecraft are deployed on the air-floating platform. Support frames for carrying the sensors are placed at both ends along the east-west direction of the geomagnetic direction and at both ends along the north-south direction of the geomagnetic direction, passing through the center of the spacecraft's equatorial plane. In the layout selection step, the three-component magnetic sensor layout is selected in the spacecraft scanning radiometer working mode of the magnetic sensor layout. The spacecraft is placed upright on the non-magnetic turntable, and the ground water cooling system of the scanning radiometer operation support equipment is placed in the predetermined area of the test area turntable. Support frames for carrying the sensors are placed at both ends along the east-west direction and the north-south direction of the geomagnetic direction, passing through the center of the spacecraft's equatorial plane. In the layout selection step, the three-component magnetic sensor layout for magnetic moment load kinetic energy spacecraft magnetic testing is selected from the magnetic sensor layout. Multiple sets of support frames for carrying sensors are placed on the equatorial plane of the spacecraft magnetic moment load, the equatorial plane of the spacecraft, the equatorial plane of the spacecraft magnetic torque device installation position, and the equatorial plane of the spacecraft magnetic compensation block installation position along the east-west direction of the geomagnetic direction, passing through the east end of the center of the equatorial plane. In the layout selection step, the three-component magnetic sensor layout for the magnetic test of the rocket final stage platform assembly is selected. The support frame for carrying the sensor is placed on the equatorial plane of the payload compartment of the rocket final stage platform assembly along the east-west geomagnetic direction through the center of the equatorial plane.
2. The spacecraft magnetic test sensor layout method based on near-field analysis according to claim 1, characterized in that, In the magnetic sensor layout step, multiple three-component magnetic acquisition sensors for collecting magnetic field signals from the equatorial plane of the spacecraft are sequentially placed on the support frame. The distance ratio parameter between the sensor and the spacecraft must conform to the near-field distance ratio rule. A three-component magnetic monitoring sensor was placed at a predetermined distance away from the center of the spacecraft to monitor the fluctuations of the environmental magnetic field in the magnetic test center area of the spacecraft. Based on the estimated value of the redundant magnetic moment of the spacecraft and the resolution value of the magnetic monitoring sensor, the preset distance value must meet the preset conditions. Determine the consistency status of the magnetic axis of the magnetic acquisition sensor, the magnetic axis of the magnetic monitoring sensor, the magnetic axis of the geomagnetic field, the magnetic coordinate axis of the spacecraft, and the zero-position axis of the non-magnetic turntable.
3. The spacecraft magnetic test sensor layout method based on near-field analysis according to claim 1, characterized in that, In the magnetic sensor layout step, multiple three-component magnetic acquisition sensors for collecting magnetic field signals from the equatorial plane of the spacecraft are sequentially placed on the support frames at the east and south ends. The distance ratio parameter between the sensor and the spacecraft must conform to the near-field distance ratio rule. A three-component magnetic monitoring sensor was placed at a predetermined distance away from the center of the spacecraft to monitor the fluctuations of the environmental magnetic field in the magnetic test center area of the spacecraft. Based on the estimated value of the redundant magnetic moment of the spacecraft and the resolution value of the magnetic monitoring sensor, the preset distance value must meet the preset conditions. Determine the consistency status of the magnetic axis of the magnetic acquisition sensor, the magnetic axis of the magnetic monitoring sensor, the magnetic axis of the geomagnetic field, the magnetic coordinate axis of the spacecraft, and the zero-position axis of the non-magnetic turntable.
4. The spacecraft magnetic test sensor layout method based on near-field analysis according to claim 1, characterized in that, In the magnetic sensor layout step, multiple three-component magnetic acquisition sensors for collecting magnetic field signals from the equatorial plane of the spacecraft are sequentially placed on the support frame. The distance ratio parameter between the sensor and the spacecraft must conform to the near-field distance ratio rule. A three-component magnetic monitoring sensor is placed at a predetermined distance from the center of the virtual spacecraft to monitor the fluctuations of the magnetic field in the magnetic test center area of the ferromagnetic tooling. Based on the estimated value of redundant magnetic moment from the ferromagnetic tooling and the resolution of the magnetic monitoring sensor, the preset distance value must meet the preset conditions. Determine the consistency status of the magnetic axis of the magnetic acquisition sensor, the magnetic axis of the magnetic monitoring sensor, the magnetic axis of the geomagnetic field, the magnetic coordinate axis of the virtual spacecraft, and the zero-position axis of the non-magnetic turntable.
5. The spacecraft magnetic test sensor layout method based on near-field analysis according to claim 1, characterized in that, In the magnetic sensor layout step, multiple three-component magnetic acquisition sensors for collecting spacecraft equatorial magnetic field signals are symmetrically placed on the support frames at the east and west ends and the north and south ends. The distance ratio parameter between the sensor and the spacecraft must conform to the near-field distance ratio rule. A three-component magnetic monitoring sensor is placed at a predetermined distance away from the center of the spacecraft to monitor the fluctuations of the environmental magnetic field in the central area of the spacecraft. Based on the magnitude of the redundant magnetic moment estimated by the spacecraft's permanent magnet moment and the stray magnetic moment generated by the antenna being energized, and the resolution value of the magnetic monitoring sensor, the preset distance value must meet the preset conditions. Determine the consistency status of the magnetic axis of the magnetic acquisition sensor, the magnetic axis of the magnetic monitoring sensor, the magnetic axis of the geomagnetic field, the magnetic coordinate axis of the spacecraft, and the zero-position axis of the air-bearing turntable.
6. The spacecraft magnetic test sensor layout method based on near-field analysis according to claim 1, characterized in that, In the magnetic sensor layout step, multiple three-component magnetic acquisition sensors for collecting spacecraft equatorial magnetic field signals are symmetrically placed on the support frames at the east and west ends and the north and south ends. The distance ratio parameter between the sensor and the spacecraft must conform to the near-field distance ratio rule. A three-component magnetic monitoring sensor was placed at a predetermined distance away from the center of the spacecraft to monitor the fluctuations of the environmental magnetic field in the magnetic test center area of the spacecraft. Based on the magnitude of the redundant magnetic moment estimated by the spacecraft's magnetic moment and the resolution value of the magnetic monitoring sensor, the preset distance value must meet the preset conditions. Determine the consistency status of the magnetic axis of the magnetic acquisition sensor, the magnetic axis of the magnetic monitoring sensor, the magnetic axis of the geomagnetic field, the magnetic coordinate axis of the spacecraft, and the zero-position axis of the non-magnetic turntable.
7. The spacecraft magnetic test sensor layout method based on near-field analysis according to claim 1, characterized in that, In the magnetic sensor layout step, multiple three-component magnetic acquisition sensors for acquiring magnetic field signals from each equatorial plane are placed sequentially on each support frame. The distance ratio between the magnetic acquisition sensors deployed on each equatorial plane and the center of each equatorial plane must conform to the near-field distance ratio rule. A three-component magnetic monitoring sensor was placed at a predetermined distance away from the center of the spacecraft to monitor the fluctuations of the environmental magnetic field in the magnetic test center area of the spacecraft. Based on the estimated value of the redundant magnetic moment of the spacecraft and the resolution value of the magnetic monitoring sensor, the preset distance value must meet the preset conditions. Determine the consistency status of the magnetic axis of the magnetic acquisition sensor, the magnetic axis of the magnetic monitoring sensor, the magnetic axis of the geomagnetic field, the magnetic coordinate axis of the spacecraft, and the zero-position axis of the non-magnetic turntable.
8. The spacecraft magnetic test sensor layout method based on near-field analysis according to claim 1, characterized in that, In the magnetic sensor layout step, multiple three-component magnetic acquisition sensors for collecting magnetic field signals from the equatorial plane of the spacecraft are sequentially placed on the support frame. The distance ratio between the acquisition sensor and the center of the equatorial plane of the payload compartment of the rocket's final stage platform assembly must conform to the near-field distance ratio rules: A three-component magnetic monitoring sensor for monitoring the fluctuations of the environmental magnetic field in the central area of the rocket's final stage platform assembly is placed at a predetermined distance away from the center of the rocket's final stage platform assembly. Based on the estimated value of redundant magnetic moment and the resolution value of magnetic sensors in the payload compartment of the rocket's final stage platform assembly, the preset distance value must meet preset conditions. Determine the consistency status of the magnetic axes of the magnetic acquisition sensor, the magnetic monitoring sensor, the geomagnetic field, and the magnetic coordinate axes of the rocket's final stage platform assembly.
9. The spacecraft magnetic test sensor layout method based on near-field analysis according to any one of claims 2-8, characterized in that, Range ratio parameter Sp : 0.4 Sp <1.4; Preset distance R The value satisfies the following preset conditions: R >(200 M / dB ) 1 / 3 in, M This indicates the estimated value of the redundant magnetic moment; dB This indicates the resolution value of the magnetic sensor.
10. A spacecraft magnetic test sensor layout system based on near-field analysis, characterized in that, Includes the following modules: Layout selection module: Select the magnetic sensor layout method based on near-field analysis according to actual needs; Magnetic sensor layout module: Layouts the magnetic sensors according to the selected magnetic sensor layout method; In the layout selection step, the spacecraft permanent magnet moment and stray magnetic moment test one-line three-component magnetic sensor layout is selected from the magnetic sensor layout. The spacecraft is placed upright on a non-magnetic turntable, and the support frame for carrying the sensor is placed at the east end of the spacecraft equatorial plane along the geomagnetic east-west direction through the center of the spacecraft equatorial plane. In the layout selection step, the spacecraft magnetic moment test cross-shaped three-component magnetic sensor layout is selected from the magnetic sensor layout. The spacecraft is placed upright on a non-magnetic turntable, and support frames for carrying the sensors are placed at the east end of the geomagnetic east-west direction and the south end of the geomagnetic north-south direction on the spacecraft equatorial plane, passing through the center of the spacecraft equatorial plane. In the layout selection step, the three-component magnetic sensor layout for ferromagnetic fixture calibration used in spacecraft magnetic testing is selected from the magnetic sensor layout. The ferromagnetic fixture is fixed on the non-magnetic turntable according to its installation position on the spacecraft. The support frame for carrying the sensor is placed on the equatorial plane of the virtual spacecraft along the east-west direction of the geomagnetic direction, passing the east end of the center of the equatorial plane of the spacecraft. In the layout selection step, the three-component magnetic sensor layout for stray magnetic moment testing in the spacecraft antenna array working mode of the magnetic sensor layout is selected. The spacecraft is placed upright on the air-floating platform, and the antenna arrays on both wings of the spacecraft are deployed on the air-floating platform. Support frames for carrying the sensors are placed at both ends along the east-west direction of the geomagnetic direction and at both ends along the north-south direction of the geomagnetic direction, passing through the center of the spacecraft's equatorial plane. In the layout selection step, the three-component magnetic sensor layout is selected in the spacecraft scanning radiometer working mode of the magnetic sensor layout. The spacecraft is placed upright on the non-magnetic turntable, and the ground water cooling system of the scanning radiometer operation support equipment is placed in the predetermined area of the test area turntable. Support frames for carrying the sensors are placed at both ends along the east-west direction and the north-south direction of the geomagnetic direction, passing through the center of the spacecraft's equatorial plane. In the layout selection step, the three-component magnetic sensor layout for magnetic moment load kinetic energy spacecraft magnetic testing is selected from the magnetic sensor layout. Multiple sets of support frames for carrying sensors are placed on the equatorial plane of the spacecraft magnetic moment load, the equatorial plane of the spacecraft, the equatorial plane of the spacecraft magnetic torque device installation position, and the equatorial plane of the spacecraft magnetic compensation block installation position along the east-west direction of the geomagnetic direction, passing through the east end of the center of the equatorial plane. In the layout selection step, the three-component magnetic sensor layout for the magnetic test of the rocket final stage platform assembly is selected. The support frame for carrying the sensor is placed on the equatorial plane of the payload compartment of the rocket final stage platform assembly along the east-west geomagnetic direction through the center of the equatorial plane.