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Replacement and extrapolation combined navigation method

A navigation method and thrust technology, applied in the field of replacement and extrapolation of landing navigation, can solve problems such as poor accuracy and lack of working conditions, and achieve the effect of ensuring effective updates

Active Publication Date: 2014-12-17
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0005]The first method is less accurate at the end of the landing, while the second method does not work well at the beginning of the landing
Generally speaking, the weighted compromise between the navigation values ​​determined by the two navigation methods during the landing process is the usual navigation method for landing detectors. The determinism and inertial navigation cumulative error have a greater impact, so it is not suitable for detectors with higher requirements for landing altitude and speed control

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  • Replacement and extrapolation combined navigation method
  • Replacement and extrapolation combined navigation method
  • Replacement and extrapolation combined navigation method

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Embodiment Construction

[0026] Such as Figure 5 Shown is the method flow chart of the present invention, and this method is explained in detail below:

[0027] 1) Obtain the initial t of the detector in the inertial system by measuring the orbit on the ground 0 time position and speed

[0028] 2) Any t can be measured by the accelerometer installed on the detector i The magnitude and direction of the acceleration generated by the thrust of the engine in the coordinate system of the detector body at each moment is denoted as (The subscript i indicates from t 0 Starting from time, taking time T (the sampling period of the navigation computer) as the interval, the data obtained from the i-th sampling or the derived data obtained from the sampling data, the same below. i=0,1,2...n, the subscript n indicates the current moment);

[0029] 3) Obtain any t through the star sensor and gyroscope installed on the detector i The attitude matrix of the time detector body in the inertial system For de...

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Abstract

The invention discloses a replacement and extrapolation combined landing navigation method which is suitable for height and speed navigation in the landing process of an extraterrestrial celestial body of a space detector. The method comprises the following steps of: determining the landing altitude and speed of the detector in a landing preliminary stage by adopting a method in which the inertial navigation and a measuring sensor are in a weighting eclectic manner; and directly determining the landing altitude and speed of the detector by adopting measuring information of the measuring sensor below the specific height of a landing terminal stage, and determining the height and speed in an updating interval of the measuring information by adopting the inertial navigation extrapolation. The method is used, the navigation accuracy of the landing altitude and speed is obviously improved, and the replacement rate and the data smoothing property of navigation data of the detector are guaranteed.

Description

technical field [0001] The invention relates to a landing navigation method with replacement and extrapolation, which is suitable for navigation calculation with uncertain initial attitude in the landing process of space probe extraterrestrial celestial bodies. Background technique [0002] During the landing process of the extraterrestrial celestial body, the probe needs to obtain the distance and speed information of itself relative to the target celestial body (the target celestial body is assumed to be the moon in the following). There are two main methods for the detector to independently obtain translational motion information. The first is to use inertial attitude measurement sensors (star sensors, gyroscopes, and accelerometers) to obtain the inertial attitude of the probe and the acceleration information received, and combine the orbit initial value information provided by the ground measurement and control system to perform calculation and extrapolation to obtain i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/24
Inventor 张洪华于萍李骥何健黄翔宇关轶峰赵宇梁俊程铭王鹏基王大轶
Owner BEIJING INST OF CONTROL ENG
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