An apparatus includes a structure configured to receive and transport thermal energy. The structure includes one or more materials configured to undergo a solid-solid phase transformation at a specified temperature or in a specified temperature range. The one or more materials form a heat input region configured to receive the thermal energy and a cold sink interface region configured to reject the thermal energy. The structure also includes one or more thermal energy transfer devices embedded in at least part of the one or more materials. The one or more thermal energy transfer devices are configured to transfer the thermal energy throughout the one or more materials and at least partially between the heat input region and the cold sink interface region. The one or more materials are also configured to absorb and store excess thermal energy in response to a temperature excursion associated with a thermal transient event and to release the stored thermal energy after the thermal transient event.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

An optical mining apparatus comprising: a light weight solar reflector; optics for controlling the delivery of concentrated sun light onto the surface of a target; and a temperature controlled gas enclosure that contains the target; wherein said solar reflector is oriented to reflect sun light onto said optics.

The present disclosure relates to a coupling assembly for fluidly connecting first and second spacecraft. The first space-craft comprises a drive mechanism and the second spacecraft comprising a valve for filling and/or draining the second spacecraft. The coupling assembly comprises first and second connectors and a lock. The first connector comprises an actuating member configured to engage and open the valve and a coupling member configured to couple to the drive mechanism such that the drive mechanism is operable to exert a torque on the coupling member to rotate the coupling member. The second connector comprises a stop portion and a bore for transferring fluid, the second connector configured to screw on to the valve until the stop portion engages the valve. In use, the lock is initially in a locked state wherein the coupling member is rotationally fixed relative to the second connector such that operation of the drive mechanism rotates the coupling member and the second connector together such that the second connector is screwed on to the valve until the stop portion engages the valve, the actuating member being prevented from moving relative to the second connector to engage and open the valve whilst the lock is in the locked state. The lock is configured such that, once the stop portion engages the valve, operation of the drive mechanism to exert a torque on the coupling member that is greater than a predetermined torque level moves the lock to an unlocked state wherein the actuating member is moveable relative to the second connector to engage and open the valve. The present disclosure also relates to a kit of parts for a coupling and to a method of fluidly connecting first and second spacecraft using a coupling.

An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.

A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

A propulsion strengthening member attached to a surface of an object existing in outer space, the propulsion strengthening member includes: a transparent member that transmits an emitted laser; and an opaque member that is provided between the transparent member and the object and absorbs the laser such that at least a part thereof is evaporated by energy of the laser.

A single-person spacecraft includes a pressurized crew enclosure, an external equipment bay, and an overhead crown assembly.

A controller controls a spacecraft to rendezvous a non-center-of-mass point of the controlled spacecraft with a non-center-of-mass point of an uncontrolled celestial body. The controlled spacecraft and the uncontrolled celestial body form a multi-object celestial system, and the controller produces control commands to thrusters of the controlled spacecraft using a non-linear model predictive control (NMPC) optimizing a cost function over a receding horizon that minimizes an error between coordinates of the non-center-of-mass point of the spacecraft and the non-center-of-mass point of the celestial body subject to joint dynamics of the multi-object celestial system coupled with joint kinematics of the multi-object celestial system.