Eureka AIR delivers breakthrough ideas for toughest innovation challenges, trusted by R&D personnel around the world.

Coorbital satellite autonomous relative position keeping method based on laser loads

A technology of relative position and satellite position, which is used in space navigation equipment, space navigation aircraft, space navigation vehicle guidance devices, etc., and can solve problems such as high ground dependence, poor long-term system in-orbit capability, and insufficient system robustness.

Active Publication Date: 2017-10-27
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
View PDF5 Cites 17 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the propeller-based active control mode, the satellite uses the propeller to change orbit to maintain the relative position of the constellation. The position is determined by using the ground measurement and control network, the navigation constellation and the inter-satellite communication, and the data is processed by the ground. Due to the non-renewable nature of the propellant , The system has poor long-term on-orbit capability and poor autonomous operation capability, and the system is not robust enough
Passive constellation maintenance uses changes in satellite configuration to achieve orbit changes. The satellites in the constellation are relatively independent, which is the same as the active control mode. The satellites in the constellation are connected through ground stations, and there is still a high degree of dependence on the ground.

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Coorbital satellite autonomous relative position keeping method based on laser loads
  • Coorbital satellite autonomous relative position keeping method based on laser loads
  • Coorbital satellite autonomous relative position keeping method based on laser loads

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0022] To cite a specific embodiment, the constellation adopts a navigation constellation to realize autonomous orbit determination on the satellite and obtain the initial position reference. After that, the navigation constellation fails, and the constellation autonomously maintains the relative position. The laser communication ranging integrated load is used to realize the determination of the relative position of the satellite and the unification of the time on the satellite. The position of each star in the constellation is used to determine the relative position holding requirements of each star, and the target constellation solution is determined after the relative position holding operation is determined. Determine the perturbation adjustment plan through the target constellation, and adjust the perturbation influence through the change and adjustment of the solar wing, so as to achieve the relative position maintenance of multiple stars on the same orbit.

[0023] After ...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The invention relates to a coorbital satellite autonomous relative position keeping method based on laser loads. On-satellite autonomous orbit determination is achieved through a navigation constellation or orbit determination is measured through a ground station, the satellite position initial reference is obtained, determination of the relative positions between two space satellites and time unification of systems are achieved by combining inter-satellite laser ranging and communication integrated loads with rotary table pointing information, a target constellation is resolved through the current position of each star of the constellation, the existing position information and the target position information are compared, the relative position keeping requirement of each star is determined, the enveloping and pose deformation requirements of each star are resolved, the change rate of a satellite orbit is changed by solar wing position adjustment and deformation and adjustment of the perturbation influence, and accordingly relative position keeping of coorbital satellites is achieved, all the stars in the constellation can run in a relative good form after the orbit is affected by perturbation, and the orbit decay influence is reduced.

Description

Technical field [0001] The invention relates to the technical field of satellite operation trajectory and attitude control, in particular to a method for maintaining the autonomous relative position of a co-orbit satellite based on a laser load. Background technique [0002] Aerospace technology is one of the most promising high-tech technologies in the world today. Space applications have evolved from traditional high-orbit and single-satellite applications to high- and low-orbit satellites, constellation group applications and single-satellite independent applications. . At the same time, with the fierce competition for high orbit positions in space, low-orbit constellation applications have become an important form of space applications. The low-orbit communication system represented by the Iridium satellite system and the orbital communication system, the composite constellation navigation system represented by Beidou and GPS, and the low-orbit ground remote sensing system r...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 王星又闫海平池贤彬项斌刘萧磊梁纪秋
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Eureka Blog
Learn More
PatSnap group products