The present application generally relates to hypergolic hydrocarbon fuel compositions comprising a convenient fuel and a cycloheptatriene and/or its analogs, and methods of making and using the hypergolic hydrocarbon fuel compositions.

A rocket propellant includes a hydrocarbon blend having a total aromatic compounds content less than 0.5 mass percent, a specific energy of at least 18.4 KBtu/lb, and a mass density of at least 0.8150 grams per cubic centimeter. The propellant, which can be prepared by blending a refined kerosene with an isoparaffin and/or a cycloparaffin, exhibits a high volumetric heat of combustion and excellent thermal stability. This combination of properties is especially useful for fueling reusable launch vehicles employing regenerative cooling of engine components.

A rocket propellant includes a hydrocarbon blend having a total aromatic compounds content less than 0.5 mass percent, a specific energy of at least 18.4 KBtu/lb, and a mass density of at least 0.8150 grams per cubic centimeter. The propellant, which can be prepared by blending a refined kerosene with an isoparaffin and/or a cycloparaffin, exhibits a high volumetric heat of combustion and excellent thermal stability. This combination of properties is especially useful for fueling reusable launch vehicles employing regenerative cooling of engine components.

A method for the degassing of hypergolic propellants includes introducing hypergolic propellant into a vacuum-tight vessel, cooling the vacuum-tight vessel containing the hypergolic propellant, and applying a pressure that is reduced as compared to the atmospheric pressure to the hypergolic propellant.

A method for the degassing of hypergolic propellants includes introducing hypergolic propellant into a vacuum-tight vessel, cooling the vacuum-tight vessel containing the hypergolic propellant, and applying a pressure that is reduced as compared to the atmospheric pressure to the hypergolic propellant.

A monopropellant includes 30-70% by weight of an oxidizer including hydroxylammonium nitrate, 5-50% by weight of a fuel, and a burn rate modifier in a non-zero amount of up to 3% by weight. The burn rate modifier can be selected from vanadium salts, iron salts, and combinations thereof. The monopropellant is a stable liquid between 20 C and 100 C at ambient pressure.

Airbag cushion assemblies for aspirating ambient air to enhance inflation. Some embodiments may comprise an inflation module comprising an inflator and a plurality of high-velocity nozzles fluidly coupled with the inflator and configured to deliver inflation gas from the inflator into an airbag cushion. A housing coupled to the airbag cushion, may comprise an aspiration inlet configured to allow for receipt of ambient air into the airbag cushion during inflation of the airbag cushion. The plurality of high-velocity nozzles may be configured to, upon actuation of the inflator, draw ambient air into the airbag cushion along with the inflation gas from the inflator. In some embodiments, a valve assembly may be provided that is configured to open upon actuation of the inflator and to close following inflation of the airbag cushion to prevent air and inflation gas from exiting through the aspiration inlet.

A rocket propellant includes a hydrocarbon blend having a total aromatic compounds content less than 0.5 mass percent, a specific energy of at least 18.4 KBtu/lb, and a mass density of at least 0.8150 grams per cubic centimeter. The propellant, which can be prepared by blending a refined kerosene with an isoparaffin and/or a cycloparaffin, exhibits a high volumetric heat of combustion and excellent thermal stability. This combination of properties is especially useful for fueling reusable launch vehicles employing regenerative cooling of engine components.

A monopropellant includes 30-70% by weight of an oxidizer including hydroxylammonium nitrate, 5-50% by weight of a fuel, and a burn rate modifier in a non-zero amount of up to 3% by weight. The burn rate modifier can be selected from vanadium salts, iron salts, and combinations thereof. The monopropellant is a stable liquid between 20 C and 100 C at ambient pressure.

An inflator (10), especially for a vehicle safely system, includes a combustion chamber (16) in which a solid propellant (18) combustible under the generation of gas is accommodated, and a compressed gas chamber (24) containing compressed gas (26), wherein even in the non-activated state of the inflator (10) a fluid communication exists between the combustion chamber (16) and the compressed gas chamber (24). The compressed gas (26) contains at least one inert gas as well as oxygen and at least one combustible gas, wherein the combustible gas is provided at a concentration at which no self-supporting conversion of the combustible gas with oxygen takes place.