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
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  • 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 c

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  • 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

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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...

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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

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Application Information

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IPC IPC(8): B64G1/24B64G1/62
CPCB64G1/242B64G1/62B64G1/24B64G1/36G01C23/00B64G1/26G05D1/04B64G1/247
Inventor J·P·伊利B·A·费尔D·波拉迪安
Owner THE BOEING CO
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