A system for launching aerospace payloads includes an unmanned modified lifting body spacecraft (100), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft (200) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.

A system for launching aerospace payloads includes an unmanned modified lifting body spacecraft (100), with a payload compartment in the forward section of the spacecraft. The spacecraft is propelled by hybrid rockets clustered in the aft section of the spacecraft. Reaction control system (RCS) modules control the flight path and its associated avionics hardware and software. This system also includes a carrier aircraft (200) configured to air-launch the spacecraft. The carrier aircraft includes a flight operations control system, which monitors the spacecraft's payload and monitors and controls launch and flight operations of the spacecraft. A ground-based mission control system monitors and controls the spacecraft's payload and monitors and controls the launch and flight operations of the spacecraft.

Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.

Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.

Various systems and methods of a layered tile insulation system of a space vehicle, configured to withstand vibration, high temperatures, and extreme thermal gradients, are disclosed. The layered tile insulation system can include at least one layered tile, each of the at least one layered tile including an outer layer having a first interlocking surface with a first set of interlocking features and an inner layer having a second interlocking surface with a second set of interlocking features, such that the outer layer is configured to be couple to the inner layer thereby forming a mechanical joint via the interlocking of the first interlocking surface with the second interlocking surface.

Repositioning the wing provides a methodology in reducing drag on multiple types of vehicles and objects. When the wing's root chord trailing edge is positioned further towards the back of the fuselage, it produces less drag. Therefore, aerospace vehicles or objects may benefit from this in reducing fuel consumption.

Repositioning the wing provides a methodology in reducing drag on multiple types of vehicles and objects. When the wing's root chord trailing edge is positioned further towards the back of the fuselage, it produces less drag. Therefore, aerospace vehicles or objects may benefit from this in reducing fuel consumption.

An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.

An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.

A process for manufacturing a cross-linked product has improved charring and thermal stability properties in which there is cross-linking of a benzoxazine monomer.