A method for determining the autonomous orbit of the Mars rover considering the sun vector

A technology of Mars probes and solar vectors, applied to instruments, measuring devices, etc., can solve the problems of large information delay, narrow measurable window, and long distance between instruments and ground, and achieve the goal of improving accuracy, stability, and reliability Effect

Active Publication Date: 2022-05-24
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

However, for the Mars probe, it has the characteristics of long distance from the ground and no GNSS available. The orbit calculation method simply borrowing from the earth satellite has the problems of narrow measurable window, no GNSS available, large information delay, and poor autonomy. The reliability of the orbit calculation of the detector needs to reduce the dependence on the ground and realize autonomous navigation

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  • A method for determining the autonomous orbit of the Mars rover considering the sun vector
  • A method for determining the autonomous orbit of the Mars rover considering the sun vector
  • A method for determining the autonomous orbit of the Mars rover considering the sun vector

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Embodiment Construction

[0126] like figure 1 As shown, a method for determining the autonomous orbit of a Mars probe considering the sun vector proposed by the present invention includes the following steps:

[0127] (1) Make the Mars rover perform rate damping after the rocket is separated; complete the rate damping, so that the position of the Mars rover relative to the inertial space remains unchanged;

[0128] (2) Send a fixed speed command to the three-axis flywheel of the Mars rover, so that the Mars rover has the initial conditions to capture the sun; send a fixed speed command of 2 rpm to the three-axis flywheel.

[0129] (3) After the rate damping is over, the Mars rover will independently judge whether it is in the shadow area. If it is in the shadow area, keep the body stable and continue to operate after the shadow appears;

[0130] If it is in a sunny area, use the solar sensor system equipped on the Mars rover to capture the sun and obtain the sun vector;

[0131] (4) After the Mars r...

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Abstract

The invention discloses a method for determining the autonomous orbit of a Mars probe considering the sun vector, so that the Mars probe does not rely on ground support but only relies on the sun sensor and Mars sensor carried by itself during the flight around the sun in the ground-fire transfer section. The device completes the orbit determination. The Mars rover performs orbit extrapolation based on the orbit recursion model; while using the Mars sensor to measure the position of the Mars rover relative to Mars, the measurement of the sun vector is introduced to further constrain the orbit extrapolation error. Compared with the prior art, the beneficial effect is that the orbit determination method of the present invention enables the Mars probe to obtain stable observations when the Mars target is lost or the Mars sensor fails, and the reliability of the orbit determination is increased.

Description

technical field [0001] The invention relates to a method for determining the autonomous orbit of a Mars probe considering the sun vector, which is used for determining the autonomous orbit of the Mars probe during the ground-fire transfer orbiting the sun, especially when the tracking Mars target is lost or the Mars sensor fails in the failure mode. The short-term orbit calculation is completed only by the measurement of the solar vector. Background technique [0002] During the flight of the Mars rover around the sun with the transfer of ground fire, it is necessary to calculate the position and velocity of the Mars rover in real time to ensure the calculation of the attitude reference of the whole vehicle and the success of the mission. [0003] There is no experience in Mars exploration in China. The earth satellite orbit calculation generally provides the initial orbit value based on the ground measurement orbit, and performs orbit recursion online or uses on-board GNSS ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 肖东东顾玥李立斌印兴峰刘付成刘宇
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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