Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Systems and methods for autonomous deorbit of spacecraft

A spacecraft and propulsion system technology, applied in the field of spacecraft de-orbiting, can solve problems such as increasing time and reducing the confidence of combustion instructions

Pending Publication Date: 2021-03-05
THE BOEING CO
View PDF0 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

delays, transmission errors, and other factors in these communications can increase the time required to calculate the deorbit of a spacecraft's burn target and reduce the confidence in the resulting burn command

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
  • Systems and methods for autonomous deorbit of spacecraft
  • Systems and methods for autonomous deorbit of spacecraft
  • Systems and methods for autonomous deorbit of spacecraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0034] The disclosed examples will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all disclosed examples are shown. In fact, several different examples could be described, and this should not be construed as limited to the examples set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0035] Within an example, systems and methods for deorbiting a spacecraft are described. Specifically, systems and methods for autonomously deorbiting a spacecraft utilizing onboard sensors and systems.

[0036]Example systems and methods involve autonomously selecting a land location for targeting while deorbiting a spacecraft. Selecting a land location may involve receiving user input including an indication of a time window for deorbiting the spacecraft. During this window of time, the spacecraft...

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 system and a method for autonomous deorbital of a spacecraft. In an example, a method for deorbiting a spacecraft is described. The method includes selecting a target landing site for deorbiting the spacecraft. The method includes determining a range target and a velocity target for reaching a predicted atmospheric entry location. The method includes determining a back-propagated orbit state estimate of the spacecraft. The method includes comparing the back-propagated orbit state estimate to a known orbit state of the spacecraft to determine that the back-propagatedorbit state estimate has converged with the known orbit state. The method includes calculating based on determining that the back-propagated orbit state estimate has converged with the known orbit state, (a) an estimated time of ignition for a propulsion system of the spacecraft and (b) an estimated burn velocity vector of the propulsion system using the range target and the velocity target. The method includes performing a burn pulse by the propulsion system.

Description

technical field [0001] The present disclosure generally relates to deorbiting a spacecraft. Specifically, the present disclosure relates to deorbiting spacecraft using onboard sensors and computing systems. Background technique [0002] Ideally, a spacecraft orbiting a celestial body such as a planet could be de-orbited within a specific window of time. The time window may be associated with the end of the mission, the operational status of the spacecraft, or a desired landing site. Selecting a landing site for a spacecraft and calculating an efficient and feasible deorbiting path requires consideration of several factors. Therefore, performing these functions within the time window may pose difficulties. [0003] Existing systems and methods for deorbiting spacecraft involve ground-side systems and two-way communications between the spacecraft and a ground-based system to provide on-board sensor information to and receive commands from the ground-based system. Latency, ...

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): B64G1/24B64G1/62
CPCB64G1/62B64G1/26B64G1/244B64G1/24B64G1/36G01C23/00G05D1/04B64G1/242B64G1/247
Inventor J·P·伊利B·A·费尔D·波拉迪安
Owner THE BOEING CO
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com