Abstract: Embodiments of the invention relates to an injection element having an inner element with a first outlet opening and an outer element. The outer element includes at least one second outlet opening structured and arranged for receiving and injecting fuel in a combustion space, and arranged coaxially to the first outlet opening. The outer element further includes third outlet openings composed of bores structured and arranged for forming a cooling liquid film layer, wherein the bores are arranged coaxially to the first outlet opening and the at least one second outlet opening.

Abstract: A bi-propellant rocket motor having controlled thermal management is disclosed. The rocket motor produces thrust using a solid or gel-phase primary propellant that can be either fuel- or oxidizer-rich, with a complementary self-pressurizing secondary propellant selected to balance the primary propellant in terms of the equivalence ratio. The motor houses multiple propellant grains arranged in such a configuration that each chamber containing a primary grain serves as both propellant storage and the main combustion chamber for that propellant grain as it burns with the secondary propellant. The secondary propellant is stored separately, and the flow routed past the primary propellant chamber to provide cooling for adjacent primary propellant chambers limiting the temperature rise in the motor structure.

Abstract: Liquid monopropellants for passive vehicle restraint systems (e.g., air bags) include an aqueous solution of a water-soluble oxidizer and a water-soluble organic fuel miscible with the oxidizer. The oxidizer is most preferably ammonium nitrate, hydrogen peroxide or nitric acid, while the fuel is a lower alcohol such as methanol, ethanol, propanol or glycerol. The liquid monopropellants will advantageously have an oxidation ratio (OR) of greater than about 0.90.

Abstract: Tungsten is added to fuel gels to increase the density specific impulse. l gels contain monomethylhydrazine or other hypergolic liquids well known in the art. The quantity of tungsten employed can vary from 10%-98% weight percent depending on the specific application. The important parameters to consider during formulation are particle size, concentration, combustion efficiency, physical properties, and plume signature. Tungsten particle sizes ranging from 10 microns to 0.5 micron were compared with carbon of 0.24 when burned in air. It is shown that tungsten burns as well as or better than carbon; however, the increased density specific impulse achieved with tungsten as compared with carbon verifies that tungsten as a high energy additive to hypergolic fuel gels is superior.

Abstract: A compound having the following formula: ##STR1## wherein R.sup.1 is --N.sup.+ H.sub.3 as found in claim 1 and R.sup.2 is either the same as F.sup.1 or hydrogen. "A" is an oxidizing anion, and X is selected to provide a neutral charge balance for the compound. A method of making a compound of the indicated structure from a compound of similar structure by an anion exchange process is also disclosed. Finally, propellant formulations incorporating the novel compounds of the present invention as fuels and oxidizers are disclosed.

Abstract: Disclosed is a method of converting non-hypergolic, liquid, rocket propellants into hypergolic propellants. The method to accomplish the conversion relates to the use of ammonium metavanadate as an additive to the liquid oxidant, such as, red fuming nitric acid (RFNA). The RFNA with additive is hypergolic with the usual fuels with which RFNA has been employed where a separate ignition system is normally required. RFNA with additive is also hypergolic with fuels which have been non-hypergolic and which have not been so used in the past with RFNA. These additional fuel blends include a fuel material selected from turpentine, aniline, triethylamine, furfuryl alcohol or blends of these fuel materials.

Abstract: Norbornadiene [bicyclo (2.2.1) heptadiene-2,5] is dimerized to a mixture of mainly the exo-endo stereoisomer of the hexacylic dimer of norbornadiene at both an excellent selectivity and conversion using an effective amount of a two component catalytic system of rhodium acetylacetonate and diethylaluminum chloride or ethylaluminum dichloride or aluminum ethylsesquichloride. The mixture also contains the endo-endo stereoisomer and some trimer. After hydrogenation a suitable mixture of the exo-endo and endo-endo dimers can be used as a component of high energy fuel.

Abstract: Norbornadiene [bicyclo(2.2.1)heptadiene-2,5] is dimerized to the exo-exo stereoisomer of the hexacyclic dimer of norbornadiene at both an excellent selectivity and conversion using an effective amount of a three component catalytic system of diethylaluminum chloride, ferric or ferrous or cobaltic or cobaltous acetylacetonate and bis(1,2-diphenylphosphino)ethane. The reaction rate is rapid. After hydrogenation the exo-exo hexacyclic dimer can be used as a component of high energy fuel for either jet or rocket propulsion.