A nozzle assembly for an ejection seat may comprise a servo valve assembly, a reservoir a cylinder, a nozzle manifold housing comprising a monolithic body having internal manifold structures integral to the body configured to communicate a gas between a pressure source and the reservoir, and configured to communicate a hydraulic fluid between, the reservoir, the servo valve assembly, and the cylinder, a rack piston disposed within the cylinder and configured to translate axially therein between a base end and a head end of the cylinder, and a linear nozzle coupled to the rack piston and configured to rotate in response to an axial translation of the rack piston.


    Access

    Download


    Export, share and cite



    Title :

    HYDRAULIC THRUST VECTOR PITCH CONTROL NOZZLE FOR ROCKET CATAPULT


    Contributors:

    Publication date :

    2021-01-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Hydraulic thrust vector pitch control nozzle for rocket catapult

    MASTROLIA BRADLEY | European Patent Office | 2022

    Free access

    HYDRAULIC THRUST VECTOR YAW CONTROL FOR ROCKET CATAPULT MOTOR ASSEMBLY

    MASTROLIA BRADLEY | European Patent Office | 2021

    Free access

    Hydraulic thrust vector yaw control for rocket catapult motor assembly

    MASTROLIA BRADLEY | European Patent Office | 2022

    Free access

    VARIABLE THRUST CATAPULT

    WHELAN PATRICK / SALOIS MATTHEW D / BENJAMIN JEFF et al. | European Patent Office | 2021

    Free access

    VARIABLE THRUST CATAPULT

    BENJAMIN JEFF / SALOIS MATTHEW D | European Patent Office | 2021

    Free access