Distributed spacecraft ground artificial system and implementing method thereof

A ground simulation and spacecraft technology, applied in the aerospace field, can solve the problems of fixed configuration and poor scalability of the distributed spacecraft simulation platform, and achieve the effect of good configurability and scalability.

Inactive Publication Date: 2009-08-12
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the configuration of the existing distributed spacecraft simulation pla

Method used

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  • Distributed spacecraft ground artificial system and implementing method thereof
  • Distributed spacecraft ground artificial system and implementing method thereof
  • Distributed spacecraft ground artificial system and implementing method thereof

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specific Embodiment approach 1

[0019] Specific implementation mode one: the following combination figure 1 , figure 2 Describe this embodiment, this embodiment is made up of the following several parts:

[0020] The basic platform unit includes a polished cast iron platform 1 and n air-floated spacecraft simulation platforms 2. After receiving the control instructions from the ground control unit, the n air-floated spacecraft simulation platforms 2 independently carry out control strategy planning, and plan the control strategy on the polished cast iron platform 1. Complete two-dimensional translation and single-axis rotation perpendicular to the platform, and n air-floating spacecraft simulation platforms 2 perform information interaction between spacecraft, cooperative attitude control between spacecraft, space configuration maintenance control of distributed spacecraft systems, and autonomous collision Verification of circumvention control, n≥2;

[0021] The local GPS positioning system includes two l...

specific Embodiment approach 2

[0028] Specific implementation mode two: the following combination figure 2 Describe this embodiment, the difference between this embodiment and Embodiment 1 is that the air bearing spacecraft simulation platform 2 includes sensors: X-axis accelerometer 2-1, Y-axis accelerometer 2-2 and fiber optic gyroscope 2-8 ; Executing agency: air-conditioning thruster 2-3 and reaction flywheel 2-7; Controller: PC104 simulation computer 2-10; And n bluetooth modules 2-11,

[0029] X-axis accelerometer 2-1, Y-axis accelerometer 2-2, air-conditioning thruster 2-3, reaction flywheel 2-7, fiber optic gyroscope 2-8 and PC104 simulation computer 2-10 are all connected to the CAN bus, through the CAN bus Realize data acquisition and transmission of control commands, n bluetooth modules 2-11 are respectively connected with PC104 simulation computer 2-10, and n bluetooth modules 2-11 are respectively realized with other n-1 airborne spacecraft simulation platforms 2 and the ground For the inform...

specific Embodiment approach 3

[0033] Specific embodiment three: the difference between this embodiment and embodiment two is that the air-floating spacecraft simulation platform 2 also includes a laser range finder 2-4, a visual camera 2-5 and a visual processing computer 2-6, and the laser range finder 2-4. The distance meter 2-4 and the visual processing computer 2-6 are respectively connected to the CAN bus, the visual camera 2-5 is connected to the visual processing computer 2-6, and other components and connection methods are the same as those in the second embodiment.

[0034] The visual camera 2-5 and the laser rangefinder 2-4 can also be configured to determine the relative position of the air-floating spacecraft, and to perform ground simulation verification of space rendezvous and docking technology, etc. Such an arrangement allows for increased accuracy in determining the relative position.

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Abstract

The invention discloses a distributed spacecraft ground simulation system and a method for realizing same, belonging to the technical field of space flight and aviation. The invention aims at solving the problems that the configuration of the simulation platform of a prior distributed spacecraft is solidified and the expandability is bad. The invention adopts a one-dimensional rotational base air floated platform which is based on a plane two-dimensional parallel motion and is perpendicular to a parallel motion plane. By configuring a cooling air thrustor and a counteractive flywheel as an executing mechanism and configuring a high-precision optical fibre gyro, an x-axle accelerometer and a Y-axle accelerometer as a sensing component, the definition of a high-precision relative position and the standardization of an initiate posture can be realized by a high-precision local GPS positioning system, and other hardware systems can be configured according to different tasks, thereby forming a multi-spacecraft ground simulation system. The invention can realize the ground simulation multi-spacecraft system by configuring different practical hardwares or simulators according to the task of the spacecraft, thereby having strong expansion capability and applicability.

Description

technical field [0001] The invention relates to distributed spacecraft system simulation technology, in particular to a multi-spacecraft application, which can realize ground simulation multi-spacecraft system and its implementation method by configuring different physical hardware or simulators according to spacecraft tasks, and belongs to aerospace Aviation sector. Background technique [0002] From the perspective of the development of distributed spacecraft systems in various countries, many distributed spacecraft systems that have entered the stage of on-orbit test verification or research have attached great importance to the ground verification of key technologies, especially the development of the system's ground physics simulation system. Full-physical / semi-physical simulation systems with different forms and different simulation purposes have been established, which are widely used in relative orbit and relative attitude control strategies and algorithms of distrib...

Claims

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Application Information

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IPC IPC(8): B64G7/00G06F17/50
Inventor 曹喜滨张锦绣兰盛昌王继河杨正贤董晓光王峰叶东
Owner HARBIN INST OF TECH
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