A stabiliser system 500 for an ejection seat 14 comprising a collapsible support structure (502,fig5A) coupled to a seat back 102 or seat bucket 104. An aerofoil (504,fig5A) coupled to the collapsible support structure and a deployment system (506,fig5A) operatively coupled to the collapsible support structure to expand the collapsible support structure. A method of actuating an ejection system comprising; receiving an eject command (602,fig6) by a controller (202,fig6), actuating (604,fig6) the ejection seat 14 via the controller and actuating a deployment system (606,fig6) of a stabiliser system via the controller. A controller is designed to expand the collapsible support structure by expanding part (608,fig 6). The deployment system may include a spring, a linear actuator or a gas piston. The deployment system may communicate with a controller or receive power from the ejection seat or can be operatively coupled to an ordnance system. The collapsible support structure may include a frangible retention element (510,fig5A) or a retractable retention element (510,fig5A).
Vertical stabilizer for ejection systems
2024-01-31
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |