A propulsion system including an extinguishable rocket motor and an incorporated maneuver control system. The rocket motor may be of the solid fuel type. One or more proportional axial thrust valves in communication with a pressure vessel or motor case containing a solid fuel propellant may be used to release combustion products for creating axial thrust. A plurality of proportional maneuver control valves in communication with the pressure vessel and having associated maneuver control thrusters may be selectively actuated in different modes of operation to provide control of pitch, yaw and roll. Fully opening all valves in communication with the pressure vessel may be used to cause rapid depressurization to extinguish the propellant. Reignition of the rocket motor may be effected upon repressurization of the pressure vessel through closing at least some of the valves. Ignition grains may be employed to shorten reignition time, and multiple propellant grains may be provided for multiple pulses.

Steerable, intermittently operable rocket propulsion system

A solid propellant dual pulse rocket motor has a pressure vessel containing two pulse grains separated by a barrier insulator. An igniter assembly disposed at a fore end of the pressure vessel selectively ignites a first pulse grain from a central channel within the grain. The igniter assembly also ignites a second pulse grain by ejecting hot combustion gases onto the fore end of the grain. Using such an ignition arrangement, a dual pulse rocket motor may be constructed using standard off-the-shelf ignition components.

Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture

A multi-pulse or multi-stage canister loaded solid propellant rocket motor. The canisters are prepared separately and loaded with solid propellant whereby the scrape rate may be reduced after which they are installed in a monolithic case which affords stiffness continuity over the length of the rocket motor to prevent guidance system upsetting free play. In order to reduce the complexity of installation of the membrane seal assembly for each pulse, the bulkhead therefor is manufactured integral with the case of the respective canister and becomes the forward closure thereof. For the multi-stage rocket motor, the monolithic case may be stepped and tapered, and the stages severable therefrom as they burn out by primer cord.

Solid propellant canister loaded multiple pulsed or staged rocket

A membrane seal assembly separating forward and aft combustion chambers of a rocket motor. The assembly covers the aft surface of a bulkhead having apertures therein to preclude flow communication between the combustion chambers during combustion of propellant within the aft combustion chamber. The assembly includes a membrane which has a plurality of sectors which open along hinge lines away from the bulkhead to allow flow communication between the combustion chambers when a higher pressure is present in the forward combustion chamber than in the aft combustion chamber, i.e., during subsequent combustion of the propellant in the forward combustion chamber. The sectors are provided by a plurality of radially extending slits in the membrane which are formed entirely through the thickness of the membrane so that complex scoring tooling and close tolerances of manufacturing membranes with score lines is not required while maintaining reliability of the burst membrane so that the cost of the membrane seal assembly may be reduced. The pattern and sizing of apertures in the bulkhead is such, for an erodible bulkhead, that each aperture erodes into the adjacent eroding apertures in such a manner as to minimize the size of debris breaking away from the bulkhead to reduce the possibility of debris becoming lodged in the nozzle throat.

Reduced cost membrane seal assembly for pulsed rocket motor

The invention discloses a dipulse engine with an integrated propellent twining structure and a preparation method. The dipulse engine comprises a combustion chamber shell, a soft interlayer, a first pulse grain assembly, a second pulse grain assembly, an ignition device and a jet pipe, wherein a front opening and a rear opening are formed in the two ends of the combustion chamber shell separately;the soft interlayer comprises a first section and a second section and divides the cavity of the combustion chamber shell into a first cavity, a third cavity and a second cavity; the first cavity isclose to the rear opening; the third cavity and the second cavity are close to the front opening and are formed internally and externally; the first pulse grain assembly comprises a first grain and afirst heat insulation layer; a central groove is formed in the first grain; the second pulse grain assembly comprises a second grain and a second heat insulation layer; the ignition device is arrangedat the front opening, and the top cover body of the ignition device is provided with a second extension part; the two wall surfaces of the second extension part are spliced with the combustion chamber shell and the second heat insulation layer separately; and the jet pipe is arranged at the rear opening. According to the dipulse engine, the second extension part is spliced with the combustion chamber shell and the second heat insulation layer, so that the negative weight is greatly reduced.

Dipulse engine with integrated propellent twining structure and preparation method

A thin membrane of high strength but ductile material is placed over a perforated structural support, thus allowing high pressure on the membrane side of the support to separate one chamber from another. Upon application of pressure through the perforated structural supporting structure, the membrane will collapse allowing communication between chambers. The arrangement has utility in rocket motors and gas generators where discrete impulse segments are desired to be available on command, and may be fabricated in concentric or tandem (series) volumes.

Membrane seal for application to pulsed rocket motors

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Membrane seal for application to pulsed rocket motors