Orbit attitude control device, and method of controlling orbit attitude

Patent metadata

Field	Value
Publication number	US-9696726-B2
Application number	US-201615054505-A
Country	US
Kind code	B2
Filing date	Feb 26, 2016
Priority date	Nov 28, 2012
Publication date	Jul 4, 2017
Grant date	Jul 4, 2017

Abstract

An orbit attitude control device includes a plurality of nozzles for injecting combustion gas supplied from a combustion chamber, and a control section configured to calculate nozzle opening degree correction values so that a deviation between a detection value of the pressure of the combustion chamber and a command value becomes smaller. The control section is configured to calculate a total correction value so that the deviation between the detection value and the command values becomes smaller. A total value T1 for first group nozzles and a total value T2 for second group nozzles are calculated. The total correction value is distributed to the opening degree correction values for the first group nozzles with a ratio of T2/(T1+T2) and to the opening degree correction values for the second group nozzles with a ratio of T1/(T1+T2).

First claim

What is claimed is:

1. A method of controlling an orbit attitude, comprising:
inputting opening degree command values for opening degrees of a plurality of nozzles which inject combustion gas supplied from a combustion chamber;
calculating nozzle opening degree correction values that are correction values for opening degree command values of the plurality of nozzles so that a deviation between a detection value of a pressure of the combustion chamber and a command value of the pressure becomes smaller; and
calculating the nozzle opening degree correction values for the plurality of nozzles based on the opening degree command values to correct the opening degree command values by the calculated nozzle opening degree correction values,
wherein a first group nozzles which belong to a first group of the plurality of nozzles are configured to inject combustion gas in opposite directions along a first axis, and a second group nozzles which belong to a second group of the plurality of nozzles are configured to inject combustion gas in opposite directions along a second axis,
wherein the calculating nozzle opening degree correction values comprises;
calculating a total correction value that is a correction value for a total of the opening degree command values of the plurality of nozzles so that the deviation between the detection value of the pressure and the command value of the pressure becomes smaller;
calculating a total first group value T1 that is a total value of the opening degree command values for the first group nozzles and a total second group value T2 that is a total value of the opening degree command values for the second group nozzles;
distributing the total correction value into a first group correction value and a second group correction value based on a ratio of the total first group value and the total second group value; and
calculating the nozzle opening degree correction values for the first group nozzles so that a total value becomes the first group correction value and calculating the nozzle opening degree correction values for the second group nozzles so that a total value becomes the second group correction value.

2. The method according to claim 1 , wherein said calculating nozzle opening degree correction values comprises:
calculating the nozzle opening degree correction values for the first group nozzles, by distributing the first group correction value to the each of the first group nozzles in proportion to each of the opening degree command values; and
calculating the nozzle opening degree correction values for the second group nozzles, by distributing the second group correction value to the each of the second group nozzles in proportion to each of the opening degree command values.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Fujita Toshiharu
• Hayakawa Nobuaki

Classifications

• B64G1/26 Primary

  using jets · CPC title

• G05D1/0883 Primary

  Physics · mapped topic

• B64G1/242

  Orbits and trajectories · CPC title

• B64G1/244

  Spacecraft control systems · CPC title