Stud-propelling mechanisms for securing a launch vehicle to a landing platform, and associated systems and methods, are disclosed. A representative system includes a fastening mechanism carried by a landing support element of a portion of a launch vehicle, the mechanism configured to fasten the landing support element to the landing surface when the launch vehicle portion is on the landing surface. The fastening mechanism can include a barrel structure for propelling a stud and an interference portion positioned to receive the stud upon activation of an energetic material that propels the stud. The stud can bind in the interference portion and in the landing surface to fasten the landing support element to the landing surface. A representative method includes automatically fastening a portion of a launch vehicle to a landing surface using a stud carried by the portion of the launch vehicle.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.

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.

The present invention presents an adjustable speed reusable rocket with attachable wings system which is optimized for multiple purpose, such as space travel, high-speed long-distance travel between different addresses on earth, etc. The rocket system comprises an adjustable speed rocket propulsion system (rocket booster), an attachable wings system, a payload or space shuttle and may include slider wings system, etc. Firstly, the rocket system flies at a lift force caused by the attachable wings system at a low speed (e.g., Mach 0.5˜3). While the rocket system reaches relatively high altitude (e.g., 25,000 meters), at this altitude, the air density is extremely low comparing with the surface of earth at zero sea level, and then the attachable wings system may detach from the rocket system and fly to a designated location as a glider or by its engine on a runway, and the rocket system begins to fully initiate propulsion system and exert the payload to forward at a super high speed. Comparing with rocket fully initiate propulsion system from earth surface, the aerodynamic friction and the aerodynamic heat caused by air is extremely small and low.

Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to enable ignition of squibs of a squib array based on the satellite exiting the launch vehicle, and a squib controller to control the ignition of the squibs based on a firing sequence of the squibs, where the squib controller is to vary the firing sequence to autonomously deploy the solar array.

Devices and techniques including possibly mass-produced manufacture of fungible launch vehicles, suitable for customization to payload specification, and programming to achieve specified delivery. Speed of assembly is adjustable to demand for deliveries. Customization occurs after manufacture and delivery and in response to payload specification. Payload specification includes weight and balance, volume, packaging, and release mechanism and order. No individual launch vehicle is manufactured to meet any particular specification. Launch vehicles are delivered from assembly to a launch site or nearby storage. Launch vehicles can be allocated and customized upon demand, at the time of launch. Customization includes adjustment of weight and balance, attitude control, or air launch parameters. Software receives specifications of individual payloads and delivery parameters and determines customizations to achieve those specifications and parameters. Models of operation of launch vehicles and payload delivery can be updated in response to results of a launch.

A structure, system, and method directed to building dwellings, shopping areas, government offices, towns, factories, hospitals and the like on the moon. The structure, system, and method utilize horizontal hole cavities on the moon such that dwellings, shopping areas, factories, government offices, towns, unmanned robot devices, and the like are placed in the horizontal hole cavities where cosmic rays and ultraviolet are not directly incident. Additionally, vertical hole cavities are utilized for building elevators and stairs. In addition, pipes supplying oxygen produced by photosynthesis devices on the moon's surface and carbon dioxide produced by humans in the cavity are used as conduits.

The present technology is directed to thrusting rails for launch vehicles, and associated systems and methods. Certain embodiments of the thrusting rails can include a first rail housing portion having a cavity and a second rail housing portion having a projection positioned at least partially within the cavity. The rails can include a bellows positioned within the cavity and an elongated tube positioned within the bellows. The elongated tube can include a vent opening in a lateral wall of the elongated tube. A shield can be positioned between the vent opening at the bellows and a sleeve can be positioned within the elongated tube. The sleeve can be constructed from a fibrous material and positioned to retain an ordnance within the elongated tube.

A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle.