Method for Mars acquisition by using SINS/image matching combination navigation

A technology of Mars capture and integrated navigation, applied in the direction of integrated navigators, etc., can solve the problems of import restrictions and high prices, and achieve the effects of eliminating deviations, improving orbital accuracy, and promoting the development of autonomy

Inactive Publication Date: 2012-12-12
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

At present, deep space probes mainly rely on star sensors to obtain self-controlled reference points, which requires very high-precision star sensors. In addition to being expensive, they are also subject to import restrictions.

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  • Method for Mars acquisition by using SINS/image matching combination navigation
  • Method for Mars acquisition by using SINS/image matching combination navigation
  • Method for Mars acquisition by using SINS/image matching combination navigation

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Embodiment Construction

[0019] This implementation is a method for capturing Mars using SINS / image matching combined navigation, including the following steps:

[0020] Step 1: The Mars exploration mission can use direct brake capture, that is, use the orbital control engine brake of the probe to achieve orbit capture. During the actual flight near Mars, the probe descends under counter-control. During the descent, it needs to cut into the orbit of Mars, that is, under the gravitational pull of Mars, making the probe its satellite. The speed of the probe is relatively fast during the interstellar flight, and it needs to decelerate continuously so that the speed of the probe at the cut-in height is greater than the first cosmic speed of Mars, 5.0km / s, and its height corresponds to figure 1 shown , otherwise it may crash into the Martian atmosphere; at the same time, the speed of the probe must be lower than the second cosmic speed of Mars, 34.1km / s, and its height corresponds to figure 1 shown ,...

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Abstract

The present invention discloses a method for Mars acquisition by using SINS/image matching combination navigation. According to the method, SINS is adopted to provide a current position and an attitude of a detector; a SINS/image matching combination navigation model is established, an image matching algorithm is adopted to carry out auxiliary correction on an output result of SINS, and a current exact position and a current exact attitude of the detector are provided; position change and attitude change of the detector can be determined by extracting and tracking an outline edge of a target Mars; an optimal combination filtering algorithm is adopted to provide state information formed by fusion of multiple information of the detector, wherein navigation positioning is performed on the detector; and finally an entering-orbit state of the detector is determined to form a control command so as to achieve independent and accurate acquisition of the detector. With the method of the present invention, development trends of miniaturization, high integration, and multi-function of the detector are met, the method of the present invention provides more excellent real time performance than remote control and remote sensing on the ground, signal blind areas on the back surface of the Mars are avoided, and independent and intelligent target acquisition and determination can be achieved.

Description

technical field [0001] The invention relates to a method that can be used for deep space probes to carry out autonomous Mars capture, in particular to a method for deep space probes to use SINS / image matching combined navigation technology to carry out autonomous Mars capture. Background technique [0002] The process of the deep space probe from decelerating and braking to being captured by the gravity of Mars until entering the ring of Mars - Mars capture is the most difficult and most important key link in the entire Mars exploration activities. After breaking away from the earth's influence sphere, the deep space probe uses inertia to fly towards Mars within the gravitational range of the sun. Before reaching the orbit of Mars, it must perform "braking" to slow down so that it can be captured by the gravitational force of Mars. If the braking is not enough at this time, the probe will fly out of the Mars influence ball; if the braking is excessive, the probe will hit Mar...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
Inventor 冷雪飞赵华姜燕王碧辉
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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