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Midway correction strategy making and implementing method suitable for Mars detection

An implementation method and technology of Mars, which is applied to space navigation equipment, space navigation aircraft, space navigation vehicle guidance devices, etc., and can solve the problem of limited ground measurement and control and orbit determination, unable to reach Mars, unable to generate strategies independently, etc. problems, to achieve the effect of reducing the pressure of long-term monitoring

Active Publication Date: 2020-06-23
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Traditional halfway corrections are based on ground orbit determination data, and a large number of simulation iterative calculations are performed on the ground to finally formulate a halfway correction capture strategy. This method is limited by ground measurement and control and orbit measurement; The strategy cannot be generated independently on the Internet, resulting in the failure to reach Mars in the end

Method used

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  • Midway correction strategy making and implementing method suitable for Mars detection
  • Midway correction strategy making and implementing method suitable for Mars detection
  • Midway correction strategy making and implementing method suitable for Mars detection

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Embodiment approach

[0034] A method for formulating and implementing a midway correction strategy applicable to Mars exploration, comprising the following steps:

[0035] S1. According to the restricted three-body gravitational orbital dynamics model, establish an error transfer model from any moment to when the probe enters the influence sphere of Mars; according to the error transfer model, calculate the orbital deviation of the probe arriving at Mars at the current moment (so The orbital deviation includes orbital semi-major axis deviation and orbital eccentricity deviation), when the orbital semi-major axis deviation of the probe arriving at Mars at the current moment exceeds the preset value of the orbital semi-major axis deviation, and the orbital eccentricity of the probe arriving at Mars at the current moment When the deviation exceeds the preset value of the track eccentricity deviation, go to S2.

[0036] The error propagation model described is:

[0037] x tof =Φ(X 0 ,t tof )X 0 ...

Embodiment

[0050] An on-line formulating and self-implementation method for a mid-course correction strategy suitable for Mars exploration. During the Mars probe's in-orbit flight, based on the position and speed information obtained from optical autonomous navigation, the selection of the mid-course correction time base is completed autonomously. On the computer) to generate the midway correction control strategy autonomously, and in the process, the computer resources are minimally occupied. The self-formulation and implementation method of midway correction strategy includes the following steps:

[0051] S1. Based on the limited three-body gravitational orbital dynamics model, establish an error transmission model from the time of correction to the time of entering the Mars influence sphere; calculate the time to Mars based on the position and velocity deviation between the probe's orbit and the nominal orbit independently calculated on the current device Track deviation position and ...

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Abstract

The invention relates to a midway correction strategy making and implementing method suitable for Mars detection. The method comprises the following steps that: S1, an error transfer model of a detector from any moment to the moment when the detector enters a Mars influence ball is established according to a limited three-body gravity orbit kinetic model, the orbit deviation of the detector arriving at the Mars at the current moment is calculated according to the error transfer model, and when the orbit deviation exceeds a deviation preset value, the method shifts to S2; S2, the speed error ofthe detector is corrected at the current moment by adopting a differential correction method with the parameter of entering the B-plane of the orbit of the Mars taken as a target, and iterative computation is performed with the error transfer model in the S1 to obtain pulse speed increment at the current moment; and S3, according to the pulse speed increment in the step S2, an orbit control duration and an orbit control ignition direction are obtained. With the method adopted, the autonomous formulation and implementation of a midway correction strategy under limited computing resources are realized. The method is simple and feasible, and Mars detection reliability under the condition of the absence of ground support is improved.

Description

technical field [0001] The invention relates to a formulating and implementing method for a midway correction strategy suitable for Mars exploration, in particular to an online formulating and autonomous implementation method for a midway correction strategy suitable for Mars exploration, and belongs to the technical field of Mars exploration orbit control. Background technique [0002] Our country will launch a Mars probe in 2020, and realize the conventional three-step process of "circling", "falling" and "patrolling" at one time. After the Mars probe is put into orbit, due to the orbital errors of the rocket, navigation errors, maneuver execution errors, and various perturbation forces that the probe receives during its flight, the actual flight track of the probe will deviate from the nominal track. In order to reach the planned To capture the aiming point, multiple mid-course track corrections (TCM) must be completed on the detector during the ground fire cruise. [00...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 王卫华秦捷于常利许贤峰王献忠王超
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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