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
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[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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