Actuation device for ejecting at least one removable part of a missile, particularly a nose

Patent metadata

Field	Value
Publication number	US-10942015-B2
Application number	US-201816500486-A
Country	US
Kind code	B2
Filing date	Apr 10, 2018
Priority date	Apr 28, 2017
Publication date	Mar 9, 2021
Grant date	Mar 9, 2021

Abstract

An actuation device for ejecting a removable part of a missile includes a pyrotechnic actuator having a pyrotechnic charge configured to generate an overpressure and a piston configured to act on the removable part of the missile, at least one retaining rod, and at least one thermal insulation element configured to thermally insulate at least the pyrotechnic charge. The pyrotechnic actuator is configured to break the retaining rod.

First claim

The invention claimed is:

1. An actuation device configured to eject at least one removable part of a missile, the actuation device comprising:
a pyrotechnic actuator comprising an activatable pyrotechnic charge configured to generate an overpressure, and a piston configured to be moved in a longitudinal direction of the missile by the overpressure generated on a head of said piston by the activatable pyrotechnic charge, such that a free end of the piston opposite said head is configured to act on said removable part of the missile;
at least one retaining rod comprising at least one part secured to said pyrotechnic actuator by a mechanical covering; and
at least one thermal insulation element configured to thermally insulate at least the pyrotechnic actuator,
wherein said pyrotechnic actuator is configured to break said at least one retaining rod, wherein a first end of said at least one retaining rod and an end of said pyrotechnic actuator are configured to be secured to a first shell securing element of the missile,
wherein a second end of the at least one retaining rod, opposite said first end of said at least one retaining rod, is configured to be secured to a second shell securing element of the missile.

2. The actuation device according to claim 1 , wherein the at least one retaining rod comprises two retaining rods substantially parallel to one another and with an axis along which the piston is configured to move, the two retaining rods being arranged on either side of said piston in a same plane.

3. The actuation device according to claim 1 , wherein said at least one retaining rod has at least one weakening zone.

4. The actuation device according to claim 3 , wherein said weakening zone is located in a proximity of the free end of the piston.

5. The actuation device according to claim 1 , wherein the at least one retaining rod comprises at least one retaining element with respect to the pyrotechnic actuator.

6. The actuation device according to claim 5 , wherein the at least one retaining element is arranged at a level of the mechanical covering.

7. The actuation device according to claim 1 , wherein the at least one retaining rod is provided with at least one thermal insulation sleeve.

8. The actuation device according to claim 7 , wherein said thermal insulation sleeve is arranged at a level of the mechanical covering.

9. The actuation device according to claim 1 , wherein said second end of the at least one retaining rod is provided with a threading configured to secure said at least one retaining rod to the second shell securing element of the missile by way of a nut.

10. The actuation device according to claim 1 , wherein said thermal insulation element comprises at least one of the following materials: mica, mullite, or muscovite.

11. A missile comprising the actuation device of claim 1 , said actuation device being secured by the first end to the first shell securing element of the missile and by the second end, opposite said first end, to the second shell securing element of the missile.

12. The missile according to claim 11 , wherein said first shell securing element secures the actuation device to a first shell of a nose of the missile and said second shell securing element secures the actuation device to a second shell of the nose.

13. The missile according to claim 12 , wherein the actuation device is configured to separate and spread out simultaneously the first shell and the second shell of the nose.

14. The missile according to claim 11 , wherein the at least one thermal insulation element is arranged facing the free end of said piston, and secured to the second shell securing element of the missile.

15. The actuation device according to claim 1 , wherein the at least one retaining rod comprises at least one retaining element configured to prevent translation of said at least one retaining rod with respect to the pyrotechnic actuator.

Assignees

• Mbda France

Inventors

• Quertelet Clément
• LAHEYNE Clyde

Classifications

• F42B15/36 Primary

  Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means · CPC title

• F42B15/34 Primary

  Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)} · CPC title