A turbine pump system includes a turbine pump assembly including a housing, a pump located in the housing, a turbine located in the housing and operably connected to the pump, and a heat exchanger located between the pump and a hydraulic fluid load. The heat exchanger is configured to reduce a temperature of a hydraulic fluid flow output by the pump and directed to the hydraulic fluid load. The heat exchanger is operably connected to a turbine gas flow and utilizes the turbine gas flow to cool the hydraulic fluid flow at the heat exchanger.

The invention is a jet propulsor using gas or liquid of the environment as an operating medium (OM). The propulsor comprises eight nozzles arranged centrally symmetrically and a channel system (CS). The CS comprises eight active channels (AC) with pressure units therein to control a flow head of the OM, four intermediate channels (IC) and a central channel (CC). Each of the AC is connected by one end to one of the nozzles. All AC are pairwise connected to each other by other ends, forming four connecting nodes of the AC (ACCN). Connected to each of the ACCN by one end is one of the IC pairwise interconnected by other ends and forming two connecting nodes of the IC (ICCN). The CC is connected to the ICCN. The technical result is the reduction of unproductive energy loss in the flows of the OM in the CS and increasing its efficacy.

A turbine pump system includes a turbine pump assembly including a housing, a pump located in the housing, a turbine located in the housing and operably connected to the pump, and a heat exchanger located between the pump and a hydraulic fluid load. The heat exchanger is configured to reduce a temperature of a hydraulic fluid flow output by the pump and directed to the hydraulic fluid load. The heat exchanger is operably connected to a turbine gas flow and utilizes the turbine gas flow to cool the hydraulic fluid flow at the heat exchanger.

A turbine pump system includes a turbine pump assembly including a housing, a pump located in the housing, a turbine located in the housing and operably connected to the pump, and a heat exchanger located between the pump and a hydraulic fluid load. The heat exchanger is configured to reduce a temperature of a hydraulic fluid flow output by the pump and directed to the hydraulic fluid load. The heat exchanger is operably connected to a turbine gas flow and utilizes the turbine gas flow to cool the hydraulic fluid flow at the heat exchanger.

A rocket-powered space launch system comprises both a vehicle segment with an integrally designed propulsion subsystem and a supporting ground facility segment. Elements of a propulsion unit as easily accessed for removal and replacement of individual components. Said launch system is highly reusable, operable, and facilitates governmental agency regulatory compliant safety of occupants and public without passenger escape function and/or commanded vehicle destruction.

A rocket-powered space launch system comprises both a vehicle segment with an integrally designed propulsion subsystem and a supporting ground facility segment. Elements of a propulsion unit as easily accessed for removal and replacement of individual components. Said launch system is highly reusable, operable, and facilitates governmental agency regulatory compliant safety of occupants and public without passenger escape function and/or commanded vehicle destruction.

A motor cap assembly for an ejection seat may comprise a servo valve assembly, a reservoir a cylinder, a motor cap manifold housing comprising a monolithic body having an internal manifold structure integral to the body configured to communicate a gas between a pressure source and a gas block, and configured to communicate a hydraulic fluid between, the reservoir, the servo valve assembly, and the cylinder, a rack piston disposed within the cylinder and configured to translate axially therein between a base end and a head end of the cylinder, and a motor cap outer housing coupled circumferentially about the motor cap manifold housing, wherein the motor cap outer housing is configured to rotate circumferentially about the motor cap manifold housing in response to an axial translation of the rack piston.

A motor cap assembly for an ejection seat may comprise a servo valve assembly, a reservoir a cylinder, a motor cap manifold housing comprising a monolithic body having an internal manifold structure integral to the body configured to communicate a gas between a pressure source and a gas block, and configured to communicate a hydraulic fluid between, the reservoir, the servo valve assembly, and the cylinder, a rack piston disposed within the cylinder and configured to translate axially therein between a base end and a head end of the cylinder, and a motor cap outer housing coupled circumferentially about the motor cap manifold housing, wherein the motor cap outer housing is configured to rotate circumferentially about the motor cap manifold housing in response to an axial translation of the rack piston.

A method of forming a flexible structure for a rocket motor assembly comprises forming a polysiloxane composition comprising at least two different silicone materials. A preliminary structure is formed from the polysiloxane composition. The preliminary structure is cured to crosslink at least a portion of different polysiloxane chains of the preliminary structure. A flexible structure for a rocket motor assembly, a flexible assembly for a rocket motor assembly, a moveable thrust nozzle assembly for a rocket motor assembly, and a rocket motor assembly are also described.

A method of forming a flexible structure for a rocket motor assembly comprises forming a polysiloxane composition comprising at least two different silicone materials. A preliminary structure is formed from the polysiloxane composition. The preliminary structure is cured to crosslink at least a portion of different polysiloxane chains of the preliminary structure. A flexible structure for a rocket motor assembly, a flexible assembly for a rocket motor assembly, a moveable thrust nozzle assembly for a rocket motor assembly, and a rocket motor assembly are also described.