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Initial value synchronization method for improving landing navigation accuracy

A technology of initial value synchronization and navigation accuracy, which is applied in the field of navigation task requirements, can solve problems such as navigation errors, and achieve the effect of avoiding navigation errors and being easy to implement

Active Publication Date: 2014-02-19
BEIJING INST OF CONTROL ENG
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide an initial value synchronization method for improving landing navigation accuracy, and to solve the navigation error problem caused by the asynchronous time between the initial value of navigation and the starting time of the landing and descent program

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  • Initial value synchronization method for improving landing navigation accuracy
  • Initial value synchronization method for improving landing navigation accuracy
  • Initial value synchronization method for improving landing navigation accuracy

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Embodiment Construction

[0021] Such as image 3 The concrete steps of shown method of the present invention are:

[0022] 1) Before the detector starts the landing and descent procedure, the ground measurement and control station injects the start time t of the landing and descent procedure into the detector 0 and t 0 The location information of the time detector r 0 and velocity information v 0 ;

[0023] 2) Start time t according to the landing descent procedure injected on the ground 0 , and the current control cycle start time t, calculate the new landing and descent program start time t 0new , the specific method is: (t 0new -t)=n×T, and t 0new >t 0 , (t 0new -T)0 ; where n is a positive integer, and T is the control cycle of the onboard computer

[0024] 3) The onboard computer on the probe uses the position information r obtained in step 1) 0 and velocity information v 0 as the initial value, with t 0new -t 0 is the orbital integration time, using orbital extrapolation method to ...

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Abstract

The invention discloses an initial value synchronization method for improving the landing navigation accuracy. According to the method, a starting moment of a landing and declining program is adjusted to be consistent with an initial moment of a control period of a satellite-borne computer, a navigation initial value is updated according to the initial moment of the control period of the satellite-borne computer, the synchronization among the navigation initial value, the starting moment of the landing and declining program and the initial moment of the control period is ensured, and the navigation accuracy in the landing and declining process is improved. A moment alignment algorithm of the method is simple, reliable and easy to realize, a large amount of operation of timing, calculation and the like is not required to be performed on the ground, and only the track extrapolation calculation is required to be autonomously performed on a satellite.

Description

technical field [0001] The invention relates to an initial value synchronization method for improving the accuracy of landing navigation, which is suitable for the navigation task requirements of the extraterrestrial celestial body landing process of space probes. Background technique [0002] Landing navigation accuracy is crucial to ensure landing safety. The accuracy of navigation initial value is the prerequisite to ensure the accuracy of landing navigation. [0003] Since space probes are equipped with inertial attitude sensors such as star sensors and gyroscopes, the attitude information can be acquired by the probe independently, while the translational information of the probe relative to a specific celestial body, such as position and velocity, etc., the probe does not have the ability to actively acquire The capability of these translational information (position and velocity) needs to be measured and determined by the ground measurement and control system, and in...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/00G01C25/00
CPCG01C21/00G01C25/00
Inventor 张洪华于萍关轶峰赵宇梁俊程铭何健王大轶王鹏基黄翔宇李骥杨巍于洁
Owner BEIJING INST OF CONTROL ENG
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