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Mars probe autonomous orbit determination method by considering sun vector

A Mars rover and solar vector technology, applied to instruments, measuring devices, etc., can solve problems such as poor autonomy, long distance between equipment and ground, and large information delay

Active Publication Date: 2020-06-05
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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  • Mars probe autonomous orbit determination method by considering sun vector
  • Mars probe autonomous orbit determination method by considering sun vector
  • Mars probe autonomous orbit determination method by considering sun vector

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Embodiment Construction

[0126] Such as figure 1 As shown, a kind of Mars rover autonomous orbit determination method considering the sun vector proposed by the present invention comprises the following steps:

[0127] (1) Let the orbiter perform rate damping after the arrow is separated; complete the rate damping, so that the position of the orbiter relative to the inertial space remains unchanged;

[0128] (2) Send a fixed speed command to the three-axis flywheels of the orbiter, so that the orbiter has the initial conditions for capturing the sun; send a fixed speed command of 2 rpm to the three-axis flywheels.

[0129] (3) After the rate damping is over, the orbiter can independently judge whether it is in the shadow area, if it is in the shadow area, keep the body stable, and continue to move after waiting for the shadow;

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

[0131] (4) After the orbiter captures th...

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Abstract

The invention discloses a Mars probe autonomous orbit determination method by considering a sun vector, and the method enables a Mars probe to complete the orbit determination just through a sun sensor and a Mars sensor carried by the Mars probe in a sun-around flight process of a ground fire transfer section without depending on the ground support. The Mars detector performs orbit extrapolation according to the orbit recursion model; while the Mars sensor is used for measuring the position of the Mars probe relative to the Mars, solar vector measurement is introduced to further restrain the orbit extrapolation error. Compared with the prior art, the orbit determination method has the beneficial effects that the Mars detector can obtain stable observed quantity under the condition that a tracking Mars target is lost or a Mars sensor breaks down, and the reliability of orbit autonomous determination is improved.

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 the determination of the autonomous orbit of the Mars probe during the ground fire transfer and flight around the sun, especially when the tracking Mars target is lost or the Mars sensor failure mode, Only rely on the measurement of the sun vector to complete the short-term orbit calculation. Background technique [0002] During the Mars rover's flight around the sun, it needs to calculate the position and speed of the orbiter in real time to ensure the attitude calculation of the whole device and the success of the mission. [0003] There is no experience in Mars exploration in China. Earth satellite orbit calculations generally provide initial orbit values ​​based on ground-measured orbits, and perform orbit recursion online or use on-board GNSS equipment to solve high-precision orbit data. However, for the Mars probe,...

Claims

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Application Information

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Patent Type & Authority Applications(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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