SPACECRAFT ATTITUDE CONTROL SYSTEM

PROBLEM TO BE SOLVED: To accomplish a high precision attitude control at the time of rendezvous docking upon accomplishing high precision attitude control during alone navigation. SOLUTION: When a first and a second spacecraft 10, 11 are in alone navigation, a first and a second actuator 18, 21 are...

Full description

Saved in:
Bibliographic Details
Main Author YOSHIZAWA TAKESHI
Format Patent
LanguageEnglish
Published 15.08.2000
Edition7
Subjects
AIRCRAFT
AVIATION
COSMONAUTICS
PERFORMING OPERATIONS
TRANSPORTING
VEHICLES OR EQUIPMENT THEREFOR
Online AccessGet full text

Cover

More Information
Summary:PROBLEM TO BE SOLVED: To accomplish a high precision attitude control at the time of rendezvous docking upon accomplishing high precision attitude control during alone navigation. SOLUTION: When a first and a second spacecraft 10, 11 are in alone navigation, a first and a second actuator 18, 21 are driven by a first and a second attitude control part 14, 15 so that independent attitude control is conducted, and at the time of rendezvous docking, the stored information in a first and a second memory part 16, 19 and the sensing information given by a first and a second attitude sensor 12, 13 are transmitted and received through a first and a second communication device 17, 20, and on the basis of these given pieces of information, a desirable sensor corresponding to the center of gravity in the docking condition is selected from the two attitude sensors 12 and 13, and the first and second actuators 18, 21 are driven on the basis of the sensing information of the selected sensor so that the attitude control is conducted.
Bibliography:Application Number: JP19990028691