Aircraft canopy jettison

Patent metadata

Field	Value
Publication number	US-11220322-B2
Application number	US-202016869035-A
Country	US
Kind code	B2
Filing date	May 7, 2020
Priority date	May 7, 2020
Publication date	Jan 11, 2022
Grant date	Jan 11, 2022

Abstract

Aircraft canopy jettison systems, apparatus, and methods are described herein. An example aircraft includes a forward fuselage defining a cockpit, a seat in the cockpit, a pivot pin coupled to the forward fuselage, and a canopy removably coupled to the forward fuselage over the cockpit. The canopy includes a frame having a hinge portion. The hinge portion includes a cam. The cam is dimensioned such that when the canopy is jettisoned while the aircraft is at zero altitude and zero airspeed, a travel path of the hinge portion does not intersect a travel path of the seat when the seat is ejected while the aircraft is at zero altitude and zero airspeed.

First claim

What is claimed is:

1. An aircraft comprising:
a forward fuselage defining a cockpit;
a seat in the cockpit;
a pivot pin coupled to the forward fuselage;
a canopy removably coupled to the forward fuselage over the cockpit, the canopy including a frame having a hinge portion engaged with the pivot pin, the hinge portion including a cam; and
a canopy jettison rocket motor to, when activated, move the canopy away from the forward fuselage, such that the canopy (1) rotates about the pivot pin until reaching a release angle and then (2) releases from the pivot pin and moves away from the forward fuselage, the cam to restrict the canopy from releasing from the pivot pin until the canopy reaches the release angle, the cam dimensioned such that when the canopy is jettisoned while the aircraft is at zero altitude and zero airspeed, a travel path of the hinge portion does not intersect a travel path of the seat when the seat is ejected while the aircraft is at zero altitude and zero airspeed.

2. The aircraft of claim 1 , further including a roller coupled to the forward fuselage, the cam to slide and/or roll along the roller when the canopy is rotated about the pivot pin.

3. The aircraft of claim 2 , wherein the frame defines a roller slot above the cam.

4. The aircraft of claim 3 , wherein the canopy is slidable on the forward fuselage from a first position in which the roller is disposed in the roller slot to a second position in which the roller is not disposed in the roller slot.

5. The aircraft of claim 4 , further including a canopy unlatch thruster to, when activated, move the canopy from the first position to the second position.

6. The aircraft of claim 5 , wherein the canopy unlatch thruster is to activate the canopy jettison rocket motor once the canopy is in the second position.

7. The aircraft of claim 6 , further including an ejection handle, wherein the ejection handle is to, when triggered, activate the canopy unlatch thruster.

8. The aircraft of claim 1 , wherein the hinge portion of the frame includes a hinge fork defining a slot, the pivot pin disposed in the slot.

9. The aircraft of claim 1 , further including an ejection seat rocket-catapult to, when activated, eject the seat from the cockpit.

10. The aircraft of claim 9 , further including:
a pyrotechnic device coupled to the forward fuselage; and
a lanyard coupled between the canopy and a pin of the pyrotechnic device.

11. The aircraft of claim 10 , wherein, when the pin is pulled from the pyrotechnic device, the pyrotechnic device is to activate the ejection seat rocket-catapult without a delay time.

12. A method comprising:
activating a canopy jettison rocket motor on an aircraft, wherein the activating of the canopy jettison rocket motor causes a canopy to (1) rotate about a pivot pin until reaching a release angle and then (2) release from the pivot pin and move away from a forward fuselage of the aircraft, the canopy including a frame having a hinge portion, the hinge portion including a cam to restrict the canopy from releasing from the pivot pin until the canopy reaches the release angle, the cam dimensioned such that when the canopy is jettisoned while the aircraft is at zero altitude and zero airspeed, a travel path of the hinge portion does not intersect a travel path of a seat when the seat is ejected while the aircraft is at zero altitude and zero airspeed.

13. The method of claim 12 , further including activating an ejection seat rocket-catapult to eject the seat when the canopy reaches a lanyard initiation angle.

14. The method of claim 13 , wherein the activating of the ejection seat rocket-catapult does not include a time delay.

15. The method of claim 12 , further including, prior to activating the canopy jettison rocket motor, activating an unlatch thruster to slide the canopy aft on the forward fuselage from a first position to a second position.

16. The method of claim 15 , wherein the frame defines a roller slot above the cam, wherein the aircraft includes a roller, and wherein, in the first position, the roller is disposed in the roller slot, and in the second position, the roller is not disposed in the roller slot.

17. The method of claim 16 , wherein the cam slides and/or rolls along the roller when the canopy is rotated about the pivot pin.

18. An aircraft comprising:
a forward fuselage defining a cockpit;
a seat in the cockpit;
a bell crank pivotably coupled to the forward fuselage;
a pivot pin coupled to the bell crank;
a canopy removably coupled to the forward fuselage over the cockpit, the canopy including a frame having a hinge portion engaged with the pivot pin, the hinge portion including a cam; and
a canopy remover to, when activated, move the canopy away from the forward fuselage, such that the canopy (1) rotates about the pivot pin until reaching a release angle and then (2) releases from the pivot pin and moves away from the forward fuselage, the cam to restrict the canopy from releasing from the pivot pin until the canopy reaches the release angle, the cam dimensioned such that when the canopy is jettisoned while the aircraft is at zero altitude and zero airspeed, a travel path of the hinge portion does not intersect a travel path of the seat when the seat is ejected while the aircraft is at zero altitude and zero airspeed.

19. The aircraft of claim 18 , wherein the canopy remover is to, when activated, slide the canopy aft on the forward fuselage from a first position to second position.

20. The aircraft of claim 19 , wherein the bell crank is rotated when the canopy is slid between the first position and the second position.

Assignees

• Boeing Co

Inventors

• Walter Matthew W

Classifications

• B64D25/10

  Ejector seats · CPC title

• B64C1/1476

  Canopies; Windscreens or similar transparent elements · CPC title

• B64C1/32 Primary

  Severable or jettisonable parts of fuselage facilitating emergency escape · CPC title