Abstract: A hardware configuration and related control strategy is disclosed that accepts an electric power input typical of space flight systems and converts that energy into a spark pulse train with fixed/predetermined performance metrics for the following system parameters: time to first spark, peak breakdown voltage amplitude, spark repetition rate and energy delivered per spark, which have all been optimally chosen to reliably ignite certain fuel mixtures, which have been proven to be beneficial for use in aerospace applications.

Abstract: An exoatmospheric vehicle uses a control system that includes a thrust system to provide thrust to control flight of the vehicle. A regenerative heat system is used to preheat portions of the thrust system, prior to their use in control of the vehicle. The heat for preheating may be generated by consumption of a fuel of the vehicle, such as a monopropellant fuel. The fuel may be used to power a pump (among other possibilities), to pressurize the fuel for use by thrusters of the thrust system. The preheated portions of the thrust system may include one or more catalytic beds of the thrust system, which may be preheated using exhaust gasses from the pump. The preheating may reduce the response time of the thrusters that have their catalytic beds preheated. Other thrusters of the thrust system may not be preheated at all before operation.

Abstract: A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.

Abstract: A high-speed-launch ramjet boost (HSLRB) engine includes a combustion system for igniting fuel pumped by a fuel pump from a fuel tank, where the combustion system includes an igniter, fuel injectors and frame holders. An inlet provides a pathway for air to flow toward the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator is included for exhausting exhaust gas from combustion of the fuel by the combustion system. A processor is coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein the processor provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle.

Abstract: A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks.

Abstract: Systems and methods are described herein for a hybrid liquid propellant rocket engine. In an embodiment, the engine includes a first pump powered by a first turbine, a second pump powered by a second turbine, and a gas generator. An output of the gas generator is connected to the first turbine and the second turbine. The engine further includes a third pump powered by a third turbine, a fourth pump powered by a fourth turbine, and a nozzle having an expander cycle in a wall and a combustion chamber. An output of the third pump is connected to the expander cycle and an output of the wall is connected to the third turbine and the fourth turbine. An output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.

Abstract: A detonation thrust-producing device includes an explosive located in a recess in an external surface of a body. Detonation of the explosive expels material out of the recess, providing thrust to the body in an opposite direction. A mass, such as a metal disk, may be placed blocking or covering the external opening. The body may be a part of a vehicle, such as an airborne projectile. The thrust-producing device may include multiple detonation motors arrayed around the body, capable of being individually or multiply detonated. Such thrust-producing devices may be used for attitude adjustment, steering, or other control of the flight of the projectile or other air vehicle. The detonation thrust-producing devices have the advantage of a faster-response time than propellant-based devices, and do not need the nozzles that are used with many propellant-based devices.

Abstract: A dual fuel propulsion system comprising a gas turbine engine configured to generate a propulsive thrust using a cryogenic liquid fuel.

Abstract: A rocket engine system with a fuel conversion system in communication with a gas generator.

Abstract: A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.

Abstract: An apparatus for reducing heating effects of an exhaust plume of a jet engine on an impinged surface includes fluid injectors disposed adjacent and aimed into an exhaust plume zone that's to be occupied by an exhaust plume when the engine is running. A flow generator transmits fluid flow into such an exhaust plume through the injectors. Each injector emits fluid in at least two divergent directions to increase the cross-sectional area of the exhaust plume by forming fluidic lobes in the exhaust plume.

Abstract: The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.

Abstract: Methods and systems are provided for propelling a vehicle. In an embodiment, by way of example only, a method includes flowing a decomposed hydroxylammonium nitrite (HAN)-based propellant into a chamber, introducing an aspirated non-polar fuel into the chamber, and combusting the decomposed HAN-based propellant and the aspirated non-polar fuel to produce an exhaust gas.

Abstract: A gas generating composition of the present invention contains at least one fuel selected from carboxylic acids, salts of carboxylic acids, and polymers; at least one perchlorate salt; and/or at least one metal oxide or metal hydroxide. A gas generating system 200 containing a gas generant in accordance with the present invention is also contemplated.

Abstract: An expander cycle rocket engine includes a primary nozzle with a heat exchanger formed therein to cool the nozzle and heat up a fluid used to drive a turbo-pump, and a secondary heat exchanger is located within the primary nozzle and includes passages to channel the fluid in order to add additional heat to the fluid used to drive the turbo-pump. The secondary heat exchanger can be a nozzle shaped heat exchanger located within the primary nozzle, and struts that secure the nozzle shaped heat exchanger within the primary nozzle and channel the fluid between nozzles. The concentric arrangement of first and second heat exchangers can transfer more heat from the combustion gases to the fluid that is used to drive the turbo-pump such that higher pressures can be obtained allowing for larger nozzles and much higher thrust than can be obtained with traditional nozzle engines, or provide significantly higher chamber pressures for engines in the prior art thrust class.

Abstract: The present invention provides a heretofore-unknown use for zirconium nitride as a hydrogen peroxide compatible protective coating that was discovered to be useful to protect components that catalyze the decomposition of hydrogen peroxide or corrode when exposed to hydrogen peroxide. A zirconium nitride coating of the invention may be applied to a variety of substrates (e.g., metals) using art-recognized techniques, such as plasma vapor deposition. The present invention further provides components and articles of manufacture having hydrogen peroxide compatibility, particularly components for use in aerospace and industrial manufacturing applications. The zirconium nitride barrier coating of the invention provides protection from corrosion by reaction with hydrogen peroxide, as well as prevention of hydrogen peroxide decomposition.

Abstract: A counter-rotating blade stage in lieu of a stator stage may compensate for relatively low rotational speed of a gas turbine engine spool. A first spool may have at least one compressor blade stage and at least one turbine blade stage. A combustor is located between the at least one compressor blade stage and the at least one turbine blade stage along a core flowpath. The at least one counter-rotating compressor blade stage is interspersed with the first spool at least one compressor blade stage. A transmission couples the at least one additional compressor blade stage to the first spool for counter-rotation about the engine axis.

Abstract: Hollow RX-08HD cylindrical charges were loaded with boron and PTFE, in the form of low-bulk density powders or powders dispersed in a rigid foam matrix. Each charge was initiated by a Comp B booster at one end, producing a detonation wave propagating down the length of the cylinder, crushing the foam or bulk powder and collapsing the void spaces. The PdV work done in crushing the material heated it to high temperatures, expelling it in a high velocity fluid jet. In the case of boron particles supported in foam, framing camera photos, temperature measurements, and aluminum witness plates suggest that the boron was completely vaporized by the crush wave and that the boron vapor turbulently mixed with and burned in the surrounding air.

Abstract: A method of evaluating a power plant having a design life based on operating the plant within an allowable chemical exposure range includes accumulating a history of a chemical exposure of a steam generating portion of the power plant. The method also includes determining a remaining life of the plant based on the history of the chemical exposure and assuming continued operation of the plant within the allowable chemical exposure range. The method may also include evaluating an economic value of operating the plant based on the remaining life of the plant.

Abstract: This invention involves the mixtures of oxides of nitrogen and oxygen (O2) as the oxidizing component in propulsion, gas generation and power generation applications. Advantages of the oxidizers of the inventions may be self pressurization, high density, density impulse, higher operational temperatures, and high Isp performance. The invention provides devices, methods and compositions related to the disclosed oxidizers.

Abstract: A non-polluting engine that produces mechanical, rotary motion, and produces oxygen as a principle gaseous byproduct. The engine employs a fuel mixture that includes two components that together produce oxygen. The fuel mixture is introduced to a combustion chamber where it is heated to facilitate the rapid production of oxygen. The expansion of the oxygen within the combustion chamber is translated to rotary mechanical energy. The oxygen produced during the reaction is expelled from the combustion chamber and released into the atmosphere.

Abstract: A plasmatron-catalyst system. The system generates hydrogen-rich gas and comprises a plasmatron and at least one catalyst for receiving an output from the plasmatron to produce hydrogen-rich gas. In a preferred embodiment, the plasmatron receives as an input air, fuel and water/steam for use in the reforming process. The system increases the hydrogen yield and decreases the amount of carbon monoxide.

Abstract: A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus or hole is defined by a tube extending through the face plate. The tube extends through the face plate in a portion of a through bore which also is used to define the second annulus. The second annulus is formed using a throughbore through which the tube extends. This allows the second annulus to always be formed inherently and precisely substantially coaxial with the first annulus. Moreover, the second annulus can be formed with a much greater tolerance than if other independent components needed to be added.

Abstract: A pressure-actuated rocket system comprises a bottom base, a detonator and a rocket body. A top base is placed on a top surface of the bottom base. At least one through hole is located on a side of the top base and extended to an opening of the top surface. The hollow detonator has a closed and an opened ends. The rocket body is a bottle with fins. After soda powder is placed inside the detonator and vinegar is filled into the rocket body, the bottom base, the detonator and the rocket body are held inclined. The openings are aimed at the inclined bottom base in turn, the pressure-actuated rocket system is then turned upside down. Soda powder subsequently falls and reacts with vinegar, and gas is generated. A pressure accumulates inside the rocket body until it is high enough to shoot the rocket body up.

Abstract: In a supersonic nozzle incorporating injectors and a combustion chamber as part of an expander cycle rocket engine, the oxidizer is injected in two streams. One of the streams, preferably a small fraction of the total, is injected into an upstream or preburner section of the combustion chamber and the other to a downstream or main section of the chamber. The preburner combustion gas is cooled in a substantially uniform manner to a moderate temperature by cooling the bulk of the gas rather than cooling only the gas in a boundary layer adjacent to the chamber wall. The combustion gas produced in the downstream section is hotter, and heat from that gas is drawn through the chamber wall into a jacket. The limited combustion in the preburner permits the use of a cooling element with highly intimate heat exchange construction, extracting a high level of energy from the preburner gas without damage to the cooling element and an overall improvement in the regenerative cooling.

Abstract: In a supersonic nozzle incorporating injectors and a combustion chamber as part of an expander cycle rocket engine, the oxidizer is injected in two streams. One of the streams, preferably a small fraction of the total, is injected into an upstream or preburner section of the combustion chamber and the other to a downstream or main section of the chamber. The preburner combustion gas is cooled in a substantially uniform manner to a moderate temperature by cooling the bulk of the gas rather than cooling only the gas in a boundary layer adjacent to the chamber wall. The combustion gas produced in the downstream section is hotter, and heat from that gas is drawn through the chamber wall into a jacket. The limited combustion in the preburner permits the use of a cooling element with highly intimate heat exchange construction, extracting a high level of energy from the preburner gas without damage to the cooling element and an overall improvement in the regenerative cooling.

Abstract: An apparatus is provided for burning a fuel and nitrous oxide. The apparatus has a combustor, a catalyst, a nitrous oxide supply passage for directing the nitrous oxide to a contact position with the catalyst, and a fuel supply passage for supplying the fuel to the combustor. The catalyst is for facilitating decomposition of the nitrous oxide, and the combustor is for burning the fuel, the decomposed nitrous oxide and/or further nitrous oxide decomposed in the reaction.

Abstract: A method and device for producing a controlled combustion by placing a combustion chamber in communication with a feed chamber that contains a solid propellant/body, introducing at least a portion of the body into the combustion chamber, isolating the combustion chamber from the feed chamber, and igniting the solid propellant in the combustion chamber while the combustion chamber is isolated from the feed chamber.

Abstract: Methods and arrangements for tailoring rocket exhaust plume signatures of rocket exhaust systems are disclosed. The tailoring of the rocket exhaust plume signature is accomplished by providing and locating at least one structure having materials and/or additives that modify the radiant intensity pattern of the rocket exhaust plume upon ablation or melting into the rocket exhaust plume. The materials and/or additives can be manufactured or incorporated into preexisting ablative materials of the rocket exhaust system or be provided as stand-alone structures.

Abstract: A pulsed detonation engine having improved efficiency has a detonation chamber for receiving a detonable mixture, an igniter for igniting the detonable mixture, and an outlet for discharging detonation products. A diverging-converging nozzle is provided at the outlet of the detonation chamber. The geometry of the diverging-converging nozzle is selected to enable a relatively short nozzle to significantly improve efficiency of the pulsed detonation engine.

Abstract: Systems and methods are disclosed for tailoring rocket exhaust plume signatures of fuel-propelled vehicles. An uncombusted fuel is injected or sprayed into the exhaust plume of an ignited rocket. The injected or sprayed fuel modifies the rocket exhaust plume to simulate an exhaust plume of a different vehicle. One or more parameters associated with the injected or sprayed fuel can be modified, so that appropriate tailoring can be achieved.

Abstract: A turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to be matched to varying flow conditions, allowing a greater mass of air to be ingested by the compressor section and results in a lower compressor outlet temperature. Increased mass flow, combined with more fuel results in higher exhaust gas temperatures and greater thrust. The addition of oxygen to the inlet air flow allows the engine to operate at higher altitudes by preventing flameout due to rarefied air.

Abstract: A process for the production of a transverse thrust in a flying object in which a defined quantity of a monergol propellent substance is introduced into a propulsion unit, which is arranged transversely relative to a longitudinal axis of the flying object to produce a thrust transverse to the longitudinal axis of the flying object. The propulsion unit has a combustion chamber, a supersonic nozzle connected to the combustion chamber and a source of heat to combust the propellant substance and produce the desired thrust for a prescribed time.

Abstract: The present invention pertains to the field of rocketry and more precisely to liquid-propellant rocket engines and to rocket power units. This invention essentially relates to a method for increasing the specific impulse in a liquid-propellant rocket engine by using oxygen as well as a hydrocarbon fuel consisting of dicyclobutyl (C8H14). The dicyclobutyl provides for a substantial increase in the specific impulse of the liquid-propellant rocket engine when compared with kerosene. This invention also relates to a power unit for a rocket that has tanks for liquid oxygen and for the hydrocarbon fuel. Since the fuel tank is filled with dicyclobutyl (C8H14), it is thus possible to increase the thrust, the specific impulse, as well as the in-flight operation duration of the engine, and to reduce the weight of the tanks without any substantial change in the circuits of the liquid-propellant rocket engine and of the rocket power unit.

Abstract: A hybrid rocket engine and a method for propelling a rocket utilizing a vortex flow field. The flow field includes an outer fluid vortex spiraling toward a closed end of the flow field generating apparatus and an inner fluid vortex substantially concentric with the outer vortex spiraling away from the closed end and toward an outlet opening in which the inner vortex spirals in the same direction as the outer vortex, but in the opposite axial direction. The invention also relates to a rocket propulsion system utilizing the flow field in which the propulsion system includes a combustion chamber with a fuel source and an oxidizer source that deliver the said fuel and said oxidizer to the said outer and inner vortexes in a manner to support a combustion process while flowing along the flow field.

Abstract: A rocket propulsion system for spacecraft achieves greater economy, reliability and efficiency rocket by incorporating monopropellant RCS thrusters (1a-1f) for attitude control and bipropellant SCAT thrusters (5a-5c) for velocity control. Both sets of thrusters are designed to use the same liquid fuel, supplied by a pressurized non-pressure regulated tank, and operate in the blow down mode. In the propulsion system such station keeping and attitude control thrusters may function in conjunction with a large thrust apogee kick engine, which may also be of the SCAT thruster construction, that uses the same propellent fuel. Hydrazine and Binitrogen tetroxide are preferred as the fuel and oxidizer, respectively. The new system offers a simple conversion of existing monopropellant systems to a high performance bipropellant dual mode system without the extreme complexity and cost attendant to a binitrogen tetroxide--hydrazine bipropellant system.

Abstract: An expansion device for doing work comprised of a housing including first and second selectively expandable sections defining an internal chamber which contains a chemical motor. Upon activation of the chemical motor, the first and second chamber are driven apart with sufficient force to allow the device to do work. The chemical motor is generally an irreversible reaction which causes the expansion device to be maintained in an expanded position.

Abstract: The present invention relates to a combined cycle system of enhanced efficiency. The system comprises a top stage, such as a fuel cell, a partial oxidation reactor or a heat engine, and an oxygen-enriching device, such as a temperature swing adsorption device or a chemical reactor bed device, as its bottom stage. The bottom stage uses waste heat produced by the top stage to enrich the oxygen content of air that is inputted to the bottom stage, thereby producing an oxygen-enriched gas mixture as the bottom stage output. This output mixture constitutes a superior oxidant which is fed back as an input for the top stage, thus enhancing the energy conversion efficiency, cheapness, and compactness of the combined cycle system as compared to that of ordinary fuel cells, partial oxidation reactors and heat engines that use unenriched air as their oxidant input.

Abstract: A high pressure pulsed gas source for accelerating a projectile along a gun barrel comprises a structure including a high voltage electrode for establishing axial electrical discharges in corresponding axial gaps behind an outlet where the projectile is located. Plasma flows at right angles to the discharges into a propellant mass that is converted into a high pressure component of the gas pulse. The gaps are arranged so that after the projectile moves away from its initial position and is in the barrel, power applied to the plasma via gaps close to the outlet is greater than power applied to the plasma via gaps farther from the outlet. To avoid damage to the gun, the gaps are arranged so power applied to the plasma is substantially the same in the discharges when plasma is initially produced. The gaps include walls that are eroded differently by the discharges so gap walls close to the outlet erode faster than gap walls farther from the outlet.

Abstract: An essentially particulate-free, non-toxic, odorless and colorless gas is generated in a pyrotechnic inflator device by using a eutectic solution of ammonium nitrate, guanidine nitrate and/or aminoguanidine nitrate, and minor amounts of polyvinyl alcohol and either potassium nitrate or potassium perchlorate. Ballistic modifiers such as triaminoguanidine nitrate (TAGN) or nitroguanidine (NQ) may be used as needed.

Abstract: Gas generating compositions and methods for their use are provided. Metal complexes are used as gas generating compositions. These complexes are comprised of a cationic metal template, sufficient oxidizing anion to balance the charge of the complex, and a neutral ligand containing hydrogen and nitrogen. The complexes are formulated such that when the complex combusts nitrogen gas and water vapor is produced. Specific examples of such complexes include metal nitrite ammine, metal nitrate ammine, and metal perchlorate ammine complexes, as well as hydrazine complexes. Such complexes are adaptable for use in gas generating devices such as automobile air bags.

Abstract: Solid rocket motor propellant formulations are provided which are capable of burning at at least two selected burn rates. The burn rate is controlled by controlling the pressure at which the propellant burns. For example, it is possible to mechanically modify the container, such as a rocket motor casing, in which the propellant is held in order to modify the pressure under which the propellant burns. Alternatively, the propellant may be configured or molded such that the pressure changes at a chosen time due to the process of burning the propellant. The propellant is capable of burning at a relatively constant burn rate at a chosen pressure. Once the pressure changes which chosen limits, the burn rate of the propellant is rapidly modified to another relatively constant burn rate. The solid rocket motor propellant is formulated with the addition of from about 0.5% to about 4.0% TiO.sub.2. The specific operating pressures and burn rates can be selected by modifying the amount of TiO.sub.

Abstract: The amount of particulate matter that is forced into the passenger compartment of an automobile by the deployment of an air bag as it protects the lives of occupants is reduced by improving the filterability of the combustion products of a composition for generating gas to inflate the bag. The filterability is improved by adding a nucleating agent for alkali metal halide vapors formed during said combustion. Silica, alumina, and graphite are representative of the nucleating agents.

Abstract: A hydrodynamic propulsion device possessing an expansion chamber located downstream of a cross-sectional widening for the inflow of a medium which is to be expelled through a discharge nozzle. The propulsion device is constructed as a static propulsion mechanism without movable components, in that the gaseous operating medium is produced in the propulsion device through the reaction of a hydrofuel, such as NaK with water.

Abstract: A novel class of energy-generating chemical processes or reactions uses cryogenically Prepared and stored materials exhibiting volcanic ground states having lifetimes exceeding several seconds. Energy generation is provided through activation of cryogenically prepared and stored material characterized by a volcanic ground potential surface in which its lowest rotation-vibration level has a lifetime sufficiently long to permit practical storage and subsequent energy release. Cryogenic preparation and storage provides that the material is kept in these lowest rotation-vibration levels, thereby avoiding thermodynamic population of the higher levels which are short-lived and therefore not suitable for practical use. In one embodiment, the He .sub.2.sup.++ v=0, J=0 level has been found to have a lifetime of 220 minutes making He.sub.2.sup.++ an ideal candidate for a fuel in which laser-induced fragmentation of He.sub.2.sup.++ into He.sup.+ +He.sup.

Abstract: A propellant composition and method for limiting the corrosive properties of by-products from initiated crash bag propellant compositions comprising a 1(a) or 2(a) group metal azide salt, an oxidizer in the form of an oxide of a non-toxic transition metal element, and an effective amount of a modifier component of the formulaMe.sub.x (An).sub.owhereinMe is a metal cation selected from iron, copper, cobalt, nickel, and molybdenum;An is an anion group which is chemically compatible with and capable of reacting with the metal of the azide salt to form nitrogen gas and non-toxic by-products less corrosive than the corresponding hydroxide of the azide metal would be; andx and o are individually defined as positive numbers appropriate to indicate the correct chemical formula.

Abstract: This invention relates to a method for the production of unsaturated carboxylic acid esters. More particularly, this invention relates to a method for efficient production of a corresponding ester from an acrylic acid or methacrylic acid (hereinafter referred to collectively as "(meth)acrylic acid") by the reaction of the (meth)acrylic acid with an aliphatic alcohol of 1 to 12 carbon atoms in the presence of a strongly acidic cation-exchange resin catalyst.

Abstract: The specification discloses a method and apparatus for generating electricity which substantially eliminates the problem of acid rain as well as the problems associated with nuclear and hydroelectric power. Scrap aluminum and ferric oxide are reacted in a combustion chamber. The heat of the reaction as well as the heat of molten iron flowing from the combustion chamber heats boilers, the generated gas of which is used to drive electric generators. The iron is reoxidized, with the heat of reoxidation also being used to heat boilers which drive generators. The reoxidized iron is then recycled into the combustion chamber.

Abstract: Improved igniter compositions for rocket motors are provided which, when cured, are non-volatile and are capable of igniting under vacuum conditions and burning steadily at reduced pressures. Said igniter compositions comprise:(a) about 11% to about 13% hydroxyl terminated polybutadiene binder prepolymer;(b) about 0.7% to about 2.0% polyfunctional isocyanate curing agent for said binder prepolymer;(c) about 2.0% to about 20% metallic powder fuel;(d) about 20% to about 40% large particle size ammonium perchlorate;(e) about 30% to about 50% small particle size ammonium perchlorate;(f) about 0.05% to about 5.0% non-volatile burning rate catalyst;(g) about 0.05% to about 0.50% bonding agent capable of wetting the solids in the composition by said binder prepolymer and of chemically coupling with said ammonium perchlorate; and(h) about 0.01% to about 0.20% ammonia scavenger wherein all percentages are by weight based on the total weight of the compositions.

Abstract: Polynorbornene has been found to be an excellent binder for the preparation of solid fuel materials and solid propellants. Mixtures of polynorbornene with liquid fuel materials such as kerosene, gasoline, or the advanced missile and aircraft liquid fuels such as JP-4, JP-5, JP-9, JP-10, RJ-4, and RJ-5, for example, can contain 80% or more of the liquid fuel material and still exist in the form of a tough rubbery polymer which has excellent burning characteristics as a solid fuel for a ramjet. Many of these materials can be tailored to have heats of combustion higher than the state-of-the-art solid ramjet fuel formulations.