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On-board autonomous orbit extrapolation method suitable for circular-orbit satellite

A technology of autonomous orbit and push method, applied in the direction of complex mathematical operations, etc., can solve problems such as consuming more hardware resources, high calculation accuracy, and complex calculation models

Active Publication Date: 2014-08-20
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the satellite's high-precision orbit determination and orbit extrapolation technology are all carried out through a special orbit determination system on the ground and a high-speed numerical computer. The calculation model is complex and the calculation accuracy is high.
After the satellite is launched into the sky, its orbit data is either obtained by the GPS receiver, or simply extrapolated from the root number on the ground. The former is likely to cause the navigation star to be invisible in the case of complex pointing of the satellite, resulting in discontinuous orbit data. The latter However, because the extrapolation model is too simple, the accuracy of the orbital data deteriorates
[0003] However, the orbit on the star serves the attitude control system, and the requirements for accuracy vary with tasks. The high-precision on-board autonomous numerical method extrapolation technology consumes more hardware resources for on-board autonomous processing. It can be seen that there is a need for a reasonably simplified autonomous extrapolation scheme that not only meets the accuracy requirements of the attitude control system, but also satisfies the computing power constraints of the star mission system, and reduces the amount of up-note data

Method used

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  • On-board autonomous orbit extrapolation method suitable for circular-orbit satellite
  • On-board autonomous orbit extrapolation method suitable for circular-orbit satellite
  • On-board autonomous orbit extrapolation method suitable for circular-orbit satellite

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1-L

[0090] Example 1 - LEO (Low Orbit) Satellite

[0091] 1. Simulation input

[0092] (1) In this simulation example, the simulation standard data is the simulation data of STK software. For the simulation mechanical model, see figure 2 The mechanical model selected for the simulation shown is the numerical extrapolation method of the "HPOP" model.

[0093] (2) The Jacchia–Roberts model is selected as the atmospheric perturbation model in this simulation example, and the geomagnetic flow index and atmospheric perturbation related parameters provided by the US NASA website are selected by reading files.

[0094] (3) The initial orbital elements of the simulation in this simulation example are as follows image 3 The initial instantaneous radicals of the extrapolation shown.

[0095] (4) For the error of the number of 6 tracks in this simulation example, see Figure 4 Errors of the square roots shown.

[0096] 2. Simulation output

[0097] Simulation results such as Figure...

Embodiment 2-M

[0100] Example 2 - MEO (Medium Orbit) Satellite

[0101] 1. Simulation input

[0102] In this simulation example, the orbit data generated by the HPOP model of the STK software is used as the standard value, and the orbit extrapolation method of this program is used to generate the orbit data, and the difference between the standard value generated by the STK software is used, and the result is the extrapolation accuracy of this method .

[0103] Among them, the simulation input conditions such as Figure 10 The initial orbital elements of the MEO orbital simulation shown and Figure 11 Mechanics model for MEO simulation shown.

[0104] 2. Simulation output

[0105] The simulation results of this simulation example are as follows Figure 12 5-day position-velocity error from single-point extrapolation of the MEO orbit shown.

[0106] 3. Simulation conclusion

[0107] according to Figure 16 The statistical results of the position and velocity errors of MEO orbit and IG...

Embodiment 3-I

[0108] Example 3 - IGSO (Incline Geosynchronous Orbit) Satellite

[0109] 1. Simulation input

[0110] In this simulation example, the simulation input conditions are as follows Figure 13 The IGSO orbital simulation initial orbital radicals and Figure 14 The simulation mechanics model of IGSO is shown.

[0111] 2. Simulation output

[0112] The results of this simulation example are Figure 15 The IGSO orbit shown is a single-point extrapolation of the 5-day position and velocity errors.

[0113] 3. Simulation conclusion

[0114] according to Figure 16 The statistical results of the position and velocity errors of MEO orbit and IGSO orbit extrapolated for 5 days shown above show that in this simulation example, the position accuracy of IGSO orbit extrapolated for 5 days can reach 25.3km, and the velocity accuracy can reach 1.7m / s; If the point is extrapolated for 2.5 days before and after the current time, the position accuracy of IGSO orbit extrapolation for 2.5 day...

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Abstract

The invention discloses an on-board autonomous orbit extrapolation method suitable for a circular-orbit satellite. A mean element input from the ground is used, a simplified extrapolation model is adopted, and an on-board computer orbit processing module carries out autonomous extrapolation according to the simplified extrapolation model, and in the autonomous extrapolation process, only a J2 item perturbation of all earth gravitational field perturbations is taken into account while all items containing the eccentricity rate e are ignored. The method can deal with the condition of discontinuous output of GPS orbit data caused by attitude maneuver of the satellite, continuous use of an on-board orbit is achieved through autonomous extrapolation of software of the on-board computer orbit processing module, and meanwhile the method needs to adapt to the constraint of the processing capacity of an on-board computer.

Description

technical field [0001] The invention relates to the technical field of satellite orbit prediction in celestial mechanics, in particular to the processing of man-made satellite orbits and the extrapolation of analysis methods in orbit mechanics. Background technique [0002] At present, the satellite's high-precision orbit determination and orbit extrapolation technology are all carried out through a special orbit determination system on the ground and a high-speed numerical computer. The calculation model is complex and the calculation accuracy is high. After the satellite is launched into the sky, its orbit data is either obtained by the GPS receiver, or simply extrapolated from the root number on the ground. The former is likely to cause the navigation star to be invisible in the case of complex pointing of the satellite, resulting in discontinuous orbit data. The latter However, because the extrapolation model is too simple, the accuracy of the orbit data deteriorates. ...

Claims

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Application Information

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IPC IPC(8): G06F17/17
Inventor 吴会英张永合尹增山
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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