Orbit attitude control device, and method of controlling orbit attitude

Patent metadata

Field	Value
Publication number	US-9469419-B2
Application number	US-201314018698-A
Country	US
Kind code	B2
Filing date	Sep 5, 2013
Priority date	Nov 27, 2012
Publication date	Oct 18, 2016
Grant date	Oct 18, 2016

Abstract

An orbit attitude control device includes a plurality of nozzles and a control section. The nozzles inject a combustion gas supplied from a combustion chamber, opening degrees being controlled in accordance with opening degree command values. The control section calculates nozzle opening degree correction values for the opening degree command values in response to a detection value of a pressure of the combustion chamber and a command value for the pressure, and correct the opening degree command values by the nozzle opening degree correction values. Each nozzle opening degree correction value is determined based on each opening degree command value.

First claim

What is claimed is:

1. An orbit attitude control device comprising:
a plurality of nozzles configured to inject a combustion gas supplied from a combustion chamber; and
a control section configured to receive opening degree command values for the plurality of nozzles, calculate a pressure difference between a detection value of a pressure inside the combustion chamber and a command value for the pressure, determine a total control value based on the pressure difference, calculate nozzle opening degree correction values by distributing the total control value to the opening degree command values to be proportional to the opening degree command values, correct the opening degree command values by the nozzle opening degree correction values, and control the plurality of nozzles based on the corrected opening degree command values such that the plurality of nozzles inject the combustion gas supplied from the combustion chamber based on the corrected opening degree command values.

2. The orbit attitude control device according to claim 1 , wherein each of the nozzle opening degree correction values is determined based on a monotonically increasing function of a corresponding one of the opening degree command values.

3. The orbit attitude control device according to claim 2 , wherein each of the nozzle opening degree correction values is determined to be proportional to the corresponding one of the opening degree command values.

4. A method of controlling an orbit attitude, the method comprising:
receiving opening degree command values for a plurality of nozzles;
calculating a pressure difference between a detection value of a pressure inside a combustion chamber and a command value for the pressure;
determining a total control value based on the pressure difference;
calculating nozzle opening degree correction values by distributing the total control value to the opening degree command values to be proportional to the opening degree command values;
correcting the opening degree command values by the nozzle opening degree correction values; and
controlling the plurality of nozzles based on the corrected opening degree command values such that the plurality of nozzles inject the combustion gas supplied from the combustion chamber based on the corrected opening degree command values.

5. The method according to claim 4 , wherein each of the nozzle opening degree correction values is determined based on a monotonically increasing function of a corresponding one of the opening degree command values.

6. The method according to claim 5 , wherein each of the nozzle opening degree correction values is determined to be proportional to the corresponding one 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

  Physics · mapped topic

• B64G1/244

  Spacecraft control systems · CPC title