More compact side force steering and attitude control system, and a vehicle including such a system

Patent metadata

Field	Value
Publication number	US-10895443-B2
Application number	US-201615771715-A
Country	US
Kind code	B2
Filing date	Oct 27, 2016
Priority date	Oct 28, 2015
Publication date	Jan 19, 2021
Grant date	Jan 19, 2021

Abstract

An in-flight side force steering and attitude control system for a vehicle includes a thruster body and a plurality of valves distributed in first and second valve sets. The system further includes a first tank defined by a first cylindrical enclosure present at the center of the thruster body, the first tank containing a first solid propellant charge having at least one combustion face exposed at one end of the first tank, the first tank being in communication with the first valve set; and a second tank defined between the first cylindrical enclosure and a second cylindrical enclosure present around the first enclosure, the second tank containing a second solid propellant charge having at least one combustion face exposed at one end of the second tank, the second tank being in communication with the second valve set.

First claim

The invention claimed is:

1. An in-flight side force steering and attitude control system for a vehicle, the system comprising a thruster body and a plurality of valves distributed in first and second valve sets, and comprising:
a first tank defined by a first substantially cylindrical enclosure present at a center of the thruster body and extending along a longitudinal axis of said thruster body, the first tank being closed at a first end and open at a second end, the first tank containing a first solid propellant charge having at least one combustion face exposed at the second end of said first tank, the first tank being in communication with the first valve set; and
a second tank defined between the first substantially cylindrical enclosure and a second substantially cylindrical enclosure present around said first substantially cylindrical enclosure and extending along the longitudinal axis of the thruster body, the second tank being closed at a first end and open at a second end, the second tank containing a second solid propellant charge having at least one combustion face exposed at the second end of said second tank, the second tank being in communication with the second valve set.

2. A system according to claim 1 , wherein the first and second valve sets are arranged at a distance apart respectively towards the front and towards the rear of the thruster body in substantially symmetrical manner relative to the center of gravity of the vehicle situated on the longitudinal axis of the thruster body.

3. A system according to claim 1 , wherein the second end of the first tank through which the combustion face of the first propellant charge is exposed, and the second end of the second tank through which the combustion face of the second propellant charge is exposed, are arranged at a distance apart from each other, respectively towards the rear and towards the front of the thruster body, in a manner that is substantially symmetrical relative to the center of gravity of the vehicle situated on the longitudinal axis of the thruster body.

4. A system according to claim 1 , wherein the first solid propellant charge presents a combustion speed different from the combustion speed of the second solid propellant charge.

5. A system according to claim 1 , wherein surfaces of the first and second solid propellant charges other than their surfaces corresponding to the combustion faces are covered in a layer of inhibitor material.

6. A system according claim 1 , wherein the first solid propellant charge comprises a plurality of solid propellant segments, the solid propellant segments being separated from one another by layers of inhibitor material.

7. A system according to claim 1 , wherein the second solid propellant charge comprises a plurality of solid propellant segments, the solid propellant segments being separated from one another by layers of inhibitor material.

8. A system according to claim 1 , wherein the first tank is in communication with the first valve set via an extender.

9. An air or space vehicle including a system according to claim 1 .

10. A missile having a terminal portion fitted with a system according to claim 1 .

Assignees

• Arianegroup Sas

Inventors

• Caubet Pascal
• Clermont Matthieu

Classifications

• B64G1/26 Primary

  using jets · CPC title

• B64G1/62

  Systems for re-entry into the earth's atmosphere; Retarding or landing devices · CPC title

• F42B10/663 Primary

  using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves · CPC title

• B64G1/403

  Solid propellant rocket engines · CPC title