Abstract: Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Abstract: Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Abstract: Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Abstract: Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Abstract: Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Abstract: Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Abstract: Inflatable rings for supporting friction welding workpieces, and associated systems and methods. A support assembly for joining multiple workpieces in a representative embodiment includes a carriage and a generally ring-shaped support member that in turn includes a body and at least one inflatable member carried by the body and positioned to expand from a first configuration to a second configuration.

Abstract: Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The first cross-sectional area is less than the second cross-sectional area. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle.

Abstract: Inflatable rings for supporting friction welding workpieces, and associated systems and methods. A support assembly for joining multiple workpieces in a representative embodiment includes a carriage and a generally ring-shaped support member that in turn includes a body and at least one inflatable member carried by the body and positioned to expand from a first configuration to a second configuration.

Abstract: Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a launch vehicle that has a first end and a second end generally opposite the first end, and is elongated along a vehicle axis extending between the first and second ends. The vehicle carries an exposed outwardly facing surface having a first region positioned or positionable to have a first cross-sectional area generally normal to the vehicle axis toward the first end of the vehicle, and a second region positioned or positionable to have a second cross-sectional area generally normal to the vehicle axis toward the second end of the vehicle. The first cross-sectional area is less than the second cross-sectional area. The system can further include a propulsion system carried by the launch vehicle and having at least one nozzle positioned toward the first end of the vehicle to launch the launch vehicle.

Abstract: A female fuse housing is provided for housing a fuse and includes a sidewall, a fuse insertion end, a terminal entry end, and a pliant partition. The sidewall has an inner surface and an exterior surface. The inner surface defines a fuse insertion area. The terminal entry end has first and second terminal sockets. The pliant partition is located within the fuse insertion area between the first terminal socket and the second terminal socket and substantially parallel to the longitudinal axis to define a first female receptor chamber and a second female receptor chamber.