A method of supplying a receiving tank of a receiving spacecraft with a supply gas. The method includes coupling a second end of a transfer line in flow communication with the receiving tank. The transfer line extends from a first end to the second end. The first end is coupled to a transfer tank disposed on a supply spacecraft. The transfer tank holds a transfer quantity of the supply gas. The supply spacecraft includes a heating system coupled in thermal communication with the transfer tank and a transfer valve operatively coupled to the transfer line. The method also includes activating the heating system while the transfer valve is closed such that a pressure of the transfer quantity of the supply gas is increased. The method further includes opening the transfer valve, wherein a difference between the increased pressure of the supply gas in the transfer tank and a pressure in the receiving tank causes a portion of the transfer quantity of the supply gas to flow through the transfer line to the receiving tank.

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 system for producing an object is disclosed including a build device having a build area and a material bonding component to receive portions of a material that are used to produce the object, at least one gripper within the build area to contact the object to provide support and to provide for at least one of a heat sink for the object, a cold sink for the object, and electrical dissipation path from the object, and a movement mechanism to move the build device relative to the object to position the build device at a position to further produce the object. Another system and methods are also disclosed.

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.

Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft. The servicing device may include a communication device configured to receive data relating to the target spacecraft from a location remote from the spacecraft servicing device. The servicing device may include a coupling mechanism comprising at least one movable coupling configured to rotate the body relative to the target spacecraft when the spacecraft servicing pod is coupled to the target spacecraft. The at least one spacecraft servicing component may include at least one propulsion device positioned on a boom arm extending away from the body.

Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

The invention relates to a locking coupling including a first coupling unit and a second coupling unit, which in each case extend along a longitudinal axis and are designed to be identical. Each coupling unit includes a valve unit and a locking unit. The first and the second valve unit are designed to form a fluid connection between the first and the second coupling unit, and the first and the second locking unit are designed to connect the first coupling unit and the second coupling unit mechanically to one another. The first coupling unit includes an actuating element, by actuation of which the first and the second coupling unit can be mechanically connected to one another via the first and the second locking unit and can be fluidically connected to one another via the first and the second valve unit.

Systems and methods are provided for scheduling objects having pair-wise and cumulative constraints. The systems and methods presented can utilize a directed acyclic graph to increase or maximize a utilization function. The objects can comprise satellites in a constellation of satellites. In some implementations, the satellites are imaging satellites, and the systems and methods for scheduling can use human collaboration to determine events of interest for acquisition of images. In some implementations, dominant edges are removed from the directed acyclic graph. In some implementations, dynamic weights are assigned to nodes associated with downlink events in the directed acyclic graph.

Disclosed is a berthing system to receive a client module, including a plurality of berthing posts, a plurality of clamping mechanisms each mounted to a respective berthing post, the plurality of clamping mechanisms movable along a berthing post to clamp a received module, wherein the plurality of clamping mechanisms are configured to assert a radial force upon the received module, wherein the plurality of clamping mechanisms each include a rotary clamping jaw that includes drawdown portion and a radial contact portion.

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.