Air intake cover

Patent metadata

Field	Value
Publication number	US-11577851-B2
Application number	US-201816770688-A
Country	US
Kind code	B2
Filing date	Nov 27, 2018
Priority date	Dec 7, 2017
Publication date	Feb 14, 2023
Grant date	Feb 14, 2023

Abstract

A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile. In the first configuration, the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface. A missile provided with such a cover is also disclosed.

First claim

The invention claimed is:

1. A cover for an intake of an air-breathing engine in a missile, the cover comprising a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile; wherein in the first configuration the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface;
wherein the motive arrangement comprises a linkage mechanism, the linkage mechanism, in the first configuration, being extended in a first direction such that the cover, in use, is locked onto the missile, and wherein, in the second configuration, the linkage mechanism is contracted in the first direction such that the cover is removable from the missile.

2. A cover as claimed in claim 1 wherein the motive arrangement comprises an actuator operable to move the motive arrangement from the first configuration to the second configuration.

3. A cover as claimed in claim 1 wherein the motive arrangement is configured, when moving from the first configuration to the second configuration, to move through an intermediate configuration in which the cover is removable from the missile but is not pushed outwardly from the missile.

4. A cover as claimed in claim 1 further comprising a hook structure arranged such that, when fitted to the air intake, the hook structure co-operates with a lip of the air intake so as to form a pivot about which the cover rotates as it is pushed outwardly from the missile.

5. A cover as claimed in claim 1 wherein the motive arrangement further comprises a cam and follower mechanism arranged to push the cover outwardly from the missile when the motive arrangement is moved to the second configuration.

6. A cover as claimed in claim 2 wherein the actuator comprises a linear actuator that is operable to extend in a second direction, so as to move the motive arrangement from the first configuration to the second configuration.

7. A cover as claimed in claim 6 wherein the motive arrangement further a cam and follower mechanism arranged to push the cover outwardly from the missile when the motive arrangement is moved to the second configuration and the cam comprises a sliding cam provided on the linear push rod on which a linear actuator operates.

8. A cover as claimed in claim 1 wherein the first direction is generally perpendicular to the second direction.

9. A cover as claimed in claim 6 wherein the second direction is generally parallel to a missile body tube of the missile.

10. A cover as claimed in claim 1 , wherein the linkage mechanism comprises a locking arm arranged to retract in the first direction when the motive arrangement moves from the first configuration to the second configuration.

11. A cover as claimed in claim 1 , further comprising a sealing ring arranged such that, when the cover is in place on the missile, the sealing ring is located around the intake so as to seal the intake from the external environment.

12. A cover as claimed in claim 2 further comprising means to hold the motive arrangement in the first configuration.

13. A cover as claimed in claim 12 wherein the motive arrangement comprises an actuator operable to move the motive arrangement from the first configuration to the second configuration and the means comprise a frangible shear pin configured to break on operation of the actuator.

14. A cover as claimed in claim 2 wherein the actuator is a pyrotechnic actuator.

15. A cover as claimed in claim 2 comprising means to receive a signal from the missile so as to cause operation of the actuator.

16. A cover as claimed in claim 1 further comprising a ballast weight arranged such that the centre of gravity of the cover is located towards the front of the cover.

17. A missile having an air-breathing engine and an intake for the air-breathing engine, the missile comprising a cover as claimed in claim 1 covering the intake, the cover being in the first configuration such that the surface of the cover is flush with the surface of the missile and the motive arrangement is located within the intake, wherein the cover is in communication with the missile such that, on receipt of a signal from the missile, the cover moves to the second configuration and is ejected from the missile.

18. A missile as claimed in claim 17 wherein the air intake is provided with means arranged to co-operate with the cover such that the cover can be locked to the missile in the first configuration.

19. A missile as claimed in claim 17 , wherein the linkage mechanism comprises a locking arm arranged to retract in the first direction when the motive arrangement moves from the first configuration to the second configuration and the means comprise slots arranged to receive the locking arm.

Assignees

• Mbda Uk Ltd

Inventors

• Howarth Anthony James

Classifications

• F42B15/10

  Missiles having a trajectory only in the air · CPC title

• F02C7/042 Primary

  having variable geometry · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D2033/0253

  specially adapted for particular type of aircraft · CPC title

• F42B15/00

  Self-propelled projectiles or missiles, e.g. rockets; Guided missiles (F42B10/00, F42B12/00, F42B14/00 take precedence; for practice or training F42B8/12; rocket torpedoes F42B17/00; marine torpedoes F42B19/00; cosmonautic vehicles B64G; jet-propulsion plants F02K) · CPC title