Dynamic simulator used for spatial visual navigation sensor

A visual navigation and sensor technology, applied in the field of visual navigation of space vehicles, can solve the problems of complex error calibration process and high test cost, achieve automatic correction of installation errors, wide application prospects, and reduce the cost of dynamic test tests

Active Publication Date: 2016-08-31
HARBIN INST OF TECH
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Problems solved by technology

[0006] The purpose of the present invention is to provide a dynamic simulator for spatial visual navigation sensors in order to solve the problems of high test cost and complicated error calibration process in the existing dynamic testing methods of visual navigation sensors

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  • Dynamic simulator used for spatial visual navigation sensor
  • Dynamic simulator used for spatial visual navigation sensor
  • Dynamic simulator used for spatial visual navigation sensor

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specific Embodiment approach 1

[0042] Specific implementation mode one: the following combination Figure 1 to Figure 10 Describe this embodiment, the dynamic simulator for spatial visual navigation sensor described in this embodiment, it comprises high-frequency infrared laser 1, optical system 2, light source detector fiber support 3, light source detector fiber 4, image exporter 5. Linear displacement mechanism 6, optical platform 7, support 8, controller 10 and dynamics computer 11,

[0043] The linear displacement mechanism 6 and the support 8 are all arranged on the optical table 7, and the support 8 is used to fix the visual navigation sensor 9; the high-frequency infrared laser 1, the optical system 2, the light source detector fiber support 3, the light source detector fiber 4 and the image The output devices 5 are all arranged on the linear displacement mechanism 6; the light source detector fiber holder 3 is used to fix the light source detector fiber 4, the light source detector fiber holder 3 i...

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Abstract

The invention relates to a dynamic simulator used for a spatial visual navigation sensor and belongs to the technical field of visual navigation of spacecrafts, aiming at solving the problems of high experiment cost and complicated error calibration process of existing dynamic testing methods of visual navigation sensors. The dynamic simulator comprises a high-frequency infrared laser, an optical system, a light source detector optical fiber support, a light source detector optical fiber, an image output device, a linear displacement mechanism, an optical table, a support, a controller and a dynamics computer, wherein the dynamic simulator forms a closed-loop system with the dynamics computer and the visual navigation sensor in a manner of fast assembly to be used for verification of flight control semi-physical simulation experiment; the controller receives data of six degrees of freedom of the aircraft from the dynamics computer, the coordinate of a target on the visual navigation sensor is obtained by calculation with a data processing and control system, and the coordinate of the target on the image output device of the dynamic simulator is obtained by utilizing a mapping relation model. The dynamic simulator is used for visual navigation of spatial visual navigation sensors.

Description

technical field [0001] The invention relates to a dynamic simulator for a space visual navigation sensor, belonging to the technical field of visual navigation of space vehicles. Background technique [0002] The visual navigation sensor is a key device to realize complex space operations. In space missions such as space vehicle rendezvous and docking, vehicle capture, parking and maintenance, it is necessary to use visual navigation sensors to navigate and control the vehicle body or its actuators, such as robotic arms. [0003] Due to the difficulty in the development of the visual navigation sensor, high measurement accuracy requirements, high requirements on the space light environment, and long working hours, it is necessary to conduct sufficient ground tests and verifications before the visual navigation sensor officially performs its flight mission. [0004] The visual navigation sensor is the measurement unit of the relative position and attitude of the spacecraft a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 刘鹏于丹赵岩乔德治赵巍唐降龙
Owner HARBIN INST OF TECH
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