A thermal control system may transfer energy (directly or after a delay) to a thrusting device that can be used to slow a reentry vehicle entering a gaseous atmosphere from orbit. The thermal control system may mitigate the heating of the vehicle by transferring heat generated by the viscous interaction between the vehicle and high-altitude portions of a planetary atmosphere to a working fluid. This working fluid may then be routed through and/or ejected through one or more nozzles aligned to produce thrust in a direction that opposes the forward motion of this vehicle. This counter thrust may help to slow the reentry vehicle and reduce the amount of kinetic energy that can be converted into thermal energy. The working fluid may also be stored to use for propulsion after the reentry vehicle slows below hypersonic velocities.

A space transportation system intended to be mounted on a space launcher comprising a re-ignitable propulsion device and steerable flaps located at a second end and a monitoring unit, each flap comprising an actuating means configured to modify the orientation of said flap, said monitoring unit being configured to control the activation of the propulsion device and individually control the orientation of the flaps in order to implement the following steps: a launch step during which the propulsion device is off and the flaps are in a retracted position; a return step during which the monitoring unit deploys the flaps and individually controls the orientation of the flaps to slow down the system, the propulsion device being off; a landing step during which the monitoring unit controls the propulsion device and the actuating means to orient the flaps to slow down.

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.

An embodiment of the present invention discloses a repair system for a planetary exploration parachute. The repair system includes a folding piece and a fuse, the fuse is provided in the folding piece, a sensing signal for reflecting an impact force of dust is received by the fuse, fusing is generated in the fuse when the sensing signal is greater than a preset threshold, and the folding piece is changed from a folded state to an unfolded state after the fusing is generated in the fuse, so as to automatically repair a damaged part of the parachute.

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.

The invention relates to a space wing, produced by means of a diaphragm forming a polygonal surface provided with an inflatable structure which includes ribs extending over the diaphragm along diagonals of the diaphragm and passing through a central point of the diaphragm. The inflatable structure includes at least one film strip, the perimeter of which adheres onto the diaphragm such as to form an inflatable space with the diaphragm.

A method, operable in the presence of ambient cosmic rays, is provided for braking a craft upon approach to a planet, moon or other space body, e.g. in preparation for landing. Deuterium-containing particle fuel material is projected in a specified direction outward of the craft, which interacts with both the cosmic rays and their principal decay product muons to generate energetic micro-fusion products that produce a braking thrust on the craft for a specified trajectory. The micro-fusion products may push directly against the craft, e.g. upon a pressure plate, or upon a sail or parachute connected to the craft, to decelerate the craft. A prepositioned automated landing system at a landing site may project the fuel material toward the craft based on telemetry tracking of an incoming craft and likewise directly disperse the material cloud to form a braking cushion at the landing site. The micro-fusion landing system may be part of a site-to-site transport, where the craft was launched using either conventional chemical rockets or micro-fusion for accelerating thrust.

An atmosphere reentry and landing device for a safe reentry of a rocket stage into the atmosphere and for a safe splashdown thereof. The device includes a ballute which is folded in a first state and unfolded in a second state, a shrouding mechanism which carries out a shrouding of the rocket stage with the ballute, a filling mechanism, and a control unit which controls the shrouding mechanism and the filling mechanism. The ballute is disposed on the rocket stage so that an aerodynamics thereof is not compromised in the first state. The ballute substantially shrouds the rocket stage in the second state. During reentry into the atmosphere, the filling mechanism fills the ballute in the second state with air or a gas from a boundary layer which is created between a plasma formed in front of a surface of the device and the surface of the device.

A recoverable rocket and an associated recovery method are disclosed. A recoverable rocket comprises a rocket body and at least two side wings. One end of each side wing is connected to the casing of the rocket body, and the other end is connected to a deceleration mechanism; the deceleration mechanism comprises a turbine engine and a propeller. The propeller is arranged below the turbine engine. The propeller is connected to the drive shaft of the turbine engine, and the turbine engine drives the propeller to rotate in the air to generate a thrust which decelerates the rocket during recovery. The rocket body comprises a structural system, a propulsion system, a control system and a set of landing legs. The advantage of this invention is that it realizes the recovery of rockets.

A method for the deployment of reconnaissance devices including buoy cameras and robotic devices in a target mission area of a remote location in space utilizing a maneuverable descent de-booster capsule and a buoyant vessel for the deployment is disclosed, including identifying the target area from an orbiting spacecraft; deploying the de-booster into orbit over the target area; initiating gradual descent of the de-booster in the atmosphere of the remote location in space; ejecting the buoyant vessel and its payload from the de-booster; filling the buoyant portion of the buoyant vessel with a lifting gas to cause the buoyant portion to become a large balloon; activating reconnaissance devices on the bay portion of the buoyant vessel, including video and other devices for monitoring and surveiling the target mission area; maneuvering the buoyant vessel to refine mission site selection; opening cargo bay doors at a predetermined altitude to deliver payloads including buoy cameras to the target mission area; causing the at least one buoyant vessel to rise in the atmosphere over the target mission area after payload delivery; and activating communication relay functions in the buoyant vessel while maintaining ongoing reconnaissance activities.