Abstract: A system for providing ignition and pressurization of hypersonic vehicles is disclosed. The system combines the pressurization, barbotage and ignition functions into a single system saving mass and volume and simplifying the hypersonic vehicle plumbing. A monopropellant fuel such as Tridyne is used to pressurize a fuel tank, warm the fuel as it enters fuel injectors, and provide barbotage of the fuel just prior to its injection into a combustion chamber.

Abstract: A fuze for a submunition is miniaturized in size by forming the fuze of a micro-electromechanical systems (“MEMS”) velocity sensor (38, 32, 34 and 36), a MEMs shock detector (31), a DC power supply (30) and one of the MEMs arm-fire device (2, FIG. 1) or MEMs safe and arm device (2, FIG. 5). Multiple fuzes may be incorporated in a fuze to ensure detonation of the explosive charge, should one fuze fail. A millimeter-microwave (“MMW”) receiver-decoder may be included to permit remote detonation on command from a remote transmitter (52) and/or a microprocessor (54) may be included to time the detonation to the physical characteristics of the target.

Abstract: A fuze for a submunition is miniaturized in size by forming the fuze of a micro-electromechanical systems (“MEMS”) velocity sensor (38, 32, 34 and 36), a MEMs shock detector (31), a DC power supply (30) and one of the MEMs arm-fire device (2, FIG. 1) or MEMs safe and arm device (2, FIG. 5). Multiple fuzes may be incorporated in a fuze to ensure detonation of the explosive charge, should one fuze fail. A MMW receiver-decoder may be included to permit remote detonation on command from a remote transmitter (52) and/or a microprocessor (54) may be included to time the detonation to the physical characteristics of the target.

Abstract: Miniature arm fire and safe and arm devices include an electrically operated pyrotechnic initiation device (5) to generate a detonation wave upon command and a movable pressure barrier (9) that blocks propagation of the detonation wave if the device is not intended to be fired and opens a window (12) to transfer the detonation wave externally of the device. The detonation wave may in alternate embodiments be a subsonic flame front and pressure wave or a supersonic shock wave, respectively. An electromagnet (7) may serve to move the pressure barrier. Detonation waves output from the device have application in igniting an explosive train, either directly or indirectly, the latter by operating an electrical switch. In the arm fire device, the barrier automatically prevents a detonation output when electrical power is removed from the device. In the safe and arm device, the barrier, once moved out of the way, remains out of the way, even when electrical power is removed.

Abstract: The invention is an airframe which includes a vehicle (12) having a solid propellant rocket engine (14) and a ramjet or scramjet engine (16); a thrust plug (18) extending from an end (20) of the vehicle which directs combustion gases (23 and 64) produced by the solid propellant rocket engine or ramjet/scramjet engine to produce forward thrust; a longitudinal passage (38) extending from the end of the vehicle to an opening (30) forward of the end which receives external air directed by forward movement of the vehicle and in which solid propellant (32) of the solid propellant rocket engine is located, and wherein during rocket operation solid propellant is combusted to produce the combustion gases in the longitudinal passage which are conveyed by the longitudinal passage into contact with the thrust plug and during ramjet/scramjet operation the longitudinal passage is open to flow of external air after operation of the solid propellant rocket engine is completed and which supports mixing and combustion of the a