Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.

Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.

A robot multi-degree-of-freedom clamper has a short stroke biaxial cylinder installed on the clamping jaw supporting frame and an output end connected with a pneumatic clamping jaw A. In addition, a clamping jaw finger A is connected with an output end of the pneumatic clamping jaw A. A long stroke biaxial cylinder is connected with a pneumatic clamping jaw B. A clamping jaw finger B is connected with the output end of the pneumatic clamping jaw B. A pneumatic clamping jaw C is positioned between the pneumatic clamping jaw A and the pneumatic clamping jaw B. A clamping jaw finger C is connected with the output end of the pneumatic clamping jaw C. The clamping jaw finger A and the pneumatic clamping jaw A are driven by the short stroke biaxial cylinder to move back and forth on the clamping jaw supporting frame.

A pallet assembly is provided and includes one of a bushing, a utility panel assembly and tooling features. The bushing is securably insertable into bushing openings defined in bottom and top pallet assembly panels and pallet assembly sidewalls. The bushing is selected from a group including multiple bushings having bores of various sizes and one or more apertures of varying sizes that are communicative with the bores. The utility panel assembly is supportively disposable on the bottom pallet assembly panel and includes a utility panel having multiple connectors. The tooling features supportively connect the pallet assembly sidewalls to a transport cart.

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 projectile landing apparatus for retrieving a projectile includes a plurality of grippers disposed to be spaced apart. The plurality of grippers may include a support, a guide having one side connected to one end of the support, and a shock absorber having one end connected to the other end of the support and having the other end connected to the guide. The plurality of grippers may guide a projectile, buffer a load, and safely retrieve the projectile.

Pneumatically supported towers for low gravity applications are disclosed herein. In one aspect, an inflatable tower for use in vacuum environments can have a membrane configured to support a load when inflated with an inflation gas to a pressures less than 100,000 pascals and greater than 0.01 pascal. The inflation gas can be chosen to have a sufficiently low boiling temperature at the inflation pressure of the membrane that the gas will not condense to a liquid or solid within a defined range of temperatures in which the tower is designed to operate. The membrane can be configured to be packaged for transport in deflated condition and rolled onto cylinders from which the membrane can be later unfurled and inflated as part of the tower inflation process. The membrane can be further configured to progressively inflate beginning at a bottom or lowest level of the membrane during the tower inflation process. The membrane can be divided into a plurality of compartments by one or more diaphragms containing valves configured to regulate flow of the inflation gas between the compartments.

Systems and methods for bonding objects using energetic welding are disclosed. A representative system includes a launch vehicle portion, one or more landing support elements positioned to support the launch vehicle portion when the launch vehicle portion lands on a landing surface, and a bonding device carried by at least one of the landing support elements and configured to form a bond between the bonding device and the landing surface when the launch vehicle portion is on the landing surface. The bond may include a weld. A further representative system includes a bonding device with an energetic material and an anchor element, wherein activating the energetic material deforms the anchor element onto a landing surface to form a weld between the bonding device and the landing surface. A representative method includes automatically bonding a portion of a launch vehicle to a landing surface in response to landing.

A collet assembly, for an umbilical plate that connects a vehicle to a ground station prior to a launch of the vehicle, includes an active decoupler. The active decoupler includes a pin. A cuff has a central opening. The pin passes through the central opening. A plurality of fingers are pivotally coupled to the cuff. A plurality of levers are pivotally coupled to the plurality of fingers and the pin.