Method and device for controlling attitude of a spacecraft
US10407186B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Mar 31, 2016 |
| Grant date | Sep 10, 2019 |
| Priority date | — |
| Expiry date | Nov 2, 2036 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/245
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method of controlling the attitude of a spacecraft in spinning around itself with a non-zero total angular momentum HTOT. The spacecraft includes a set of inertia flywheels configured to form an internal angular momentum HACT. The axis of the total angular momentum HTOT is aligned with a principal axis of inertia of the spacecraft, in the course of which the inertia flywheels are controlled to form an internal angular momentum HACT. The following expression, in which J is the inertia matrix of the spacecraft: Hact×J−1(Htot⊗J−1Htot) is negative if the principal axis of inertia targeted is the axis of maximum inertia of the spacecraft and is positive if the principal axis inertia targeted is the axis of minimum inertia of the spacecraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.