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.

Tether-based reaction control systems for spacecraft undergoing atmospheric entry or reducing orbital energy, including systems that use atmospheric drag on one or more tethers to alter the angle of attack of the spacecraft during its atmospheric transit to reduce the thermal and mechanical loads on the spacecraft during the reentry process. Systems may include tethers that together generate a force that functionally acts on the spacecraft at a point that is offset from the spacecraft's center of mass. Such systems may be either actively or passively controlled.

Systems and methods for a parachute or parachute system are described. The parachute or parachute system includes two or more panels and includes at least one band which may be in a lateral direction relative to the two or more panels. The at least one band may be secured at different points which are lateral mid-points in individual contiguous ones of the two or more panels. Further, a first distance between an individual set of points of the different points may be shorter than twice a second distance. The second distance is a lateral distance from at least one point of the individual set of points to a seam of one panel of the two or more panels having the at least one point.

Tether-based reaction control systems for spacecraft undergoing atmospheric entry or reducing orbital energy, including systems that use atmospheric drag on one or more tethers to alter the angle of attack of the spacecraft during its atmospheric transit to reduce the thermal and mechanical loads on the spacecraft during the reentry process. Systems may include tethers that together generate a force that functionally acts on the spacecraft at a point that is offset from the spacecraft's center of mass. Such systems may be either actively or passively controlled.

Tether-based reaction control systems for spacecraft undergoing atmospheric entry or reducing orbital energy, including systems that use atmospheric drag on one or more tethers to alter the angle of attack of the spacecraft during its atmospheric transit to reduce the thermal and mechanical loads on the spacecraft during the reentry process. Systems may include tethers that together generate a force that functionally acts on the spacecraft at a point that is offset from the spacecraft's center of mass. Such systems may be either actively or passively controlled.

A metal encapsulated ceramic tile thermal insulation system for rockets and associated methods is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end and includes a heat shield positioned at the second end. The heat shield includes a plurality of thermal protection apparatuses, where individual of the thermal protection apparatuses include ceramic tiles encapsulated by inner and outer metal layers, which are positioned on opposing top and bottom surfaces of the ceramic tiles. The plurality of thermal protection apparatuses includes a plurality of pins positioned within corresponding holes drilled through the ceramic tiles and are secured to the metal layers. The outer metal layer can protect the ceramic tile from tool strikes and debris and can also prevent water from reaching and being absorbed by the ceramic tile.

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.

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 device for automatically releasing cremated ashes, including a chamber for containing cremated ashes; and a release mechanism configured to selectively release cremated ashes contained in the chamber to the external environment. The release mechanism includes an annular outer member, and an inner member at least partially radially inward of the outer member. The outer member includes an outlet from the chamber. The release mechanism is configured to translate the inner member and the outer member relative to each other along a common longitudinal axis from a first relative position, in which release of cremated ashes in the chamber through the outlet is inhibited, to a second relative position, in which release of cremated ashes in the chamber through the outlet is enabled. In the first relative position, the inner member is in contact with the outer member so as to cover the outlet. In the second relative position, the inner member is spaced from the outer member.

Systems and methods for a parachute or parachute system are described. The parachute or parachute system includes two or more panels and includes at least one band which may be in a lateral direction relative to the two or more panels. The at least one band may be secured at different points which are lateral mid-points in individual contiguous ones of the two or more panels. Further, a first distance between an individual set of points of the different points may be shorter than twice a second distance. The second distance is a lateral distance from at least one point of the individual set of points to a seam of one panel of the two or more panels having the at least one point.