Material transfer interfaces for space vehicles, and associated systems and methods are disclosed. A representative system includes a first coupler configured to be carried by a first space vehicle, and a first valve device carried by the first coupler. The system further includes a second coupler configured to be carried by a second space vehicle and a second valve device carried by the second coupler. The first coupler includes rotatable and translatable latch arms positioned to engage with and connect to the second coupler. The first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler to transfer fluid between the first and second valve devices.

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual “cells”, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or “rolling” along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

A satellite rescue system (SRS) (1) for rescue and recertification of dormant satellites, said SRS having a thruster end (13) with a primary propulsion nozzle (11) and maneuvering thrusters (12) and a satellite connection end (8) with a body (15) between both ends. The satellite connection end of the SRS has an interface ring (14) with clinch clamps (4) that securely attach to a ring (3) on the rescued satellite. An umbilical connector (7) on the satellite connecting end of the SRS provides power and data to the rescued satellite.

A release mechanism for separating two components including: (i) a first plate-shaped member (1) with a first midplane (21) that is connectable to a first component and having two opposite first surfaces (3; 3′) arranged parallel to the first midplane and a first coupling portion (5); (ii) a second plate-shaped member (2) with a second midplane (22) that is connectable to a second component and having two opposite second surfaces (4; 4′) arranged parallel to the second midplane and a second coupling portion (6); (iii) an explosive (9) arranged in the first coupling portion and/or the second coupling portion or between them; and (iv) a plurality of protrusions (10) provided on and firmly connected to at least one of the first surfaces and/or the second surfaces. The first member and the second member are coupled to each other in a mutual midplane comprising the first midplane and the second midplane.

Embodiments of the disclosure are directed to a vibration control system and a vibration control device for structurally isolating a load from a vibration source. In various embodiments a vibration isolation device includes a first and support structure and a sidewall extending between and defining a body of the vibration isolation component. In embodiments the sidewall is configured to structurally support the load. In embodiments the sidewall includes one or more lattice portions occupying at least part of a total area of the sidewall, the lattice portions configured to attenuate a transfer of vibrations through the sidewall between the first and second support structures for reducing vibration transfer from the spacecraft vibration source and the load. In embodiments the body of the vibration isolation device is approximately the same as a component without one or more lattice portions such that the payload interface cone is a drop-in replacement.

A spacecraft refueling and storage system comprising a first tank and a second tank for storing propellant, a rotatable shaft to which the first and second tanks are mounted for rotating the first and second tanks about an axis of the shaft, and a drive motor for rotating the shaft so that upon rotation of the first and second tanks, liquid propellant is separated from gas in the propellant and settled to an outer portion of the first and second tanks.

Methods, devices, and systems are described for a mounting flange and bracket for a space habitat. The bracket system couples a bladder of a space habitat to a cylindrical core. The bracket system includes a soft goods layer configured to cover the bladder of the space habitat. The bracket system includes a mounting flange configured to couple at an end of the cylindrical core. The mounting flange includes a lip extending around the mounting flange. The bracket system includes a bracket configured to connect the soft goods layer to the mounting flange. The bracket has a first end and a second end. The first end includes a pin configured to couple to the soft goods layer. The second end includes a protrusion configured to latch to the lip of the mounting flange. In some variations, a cap is configured to be coupled to the outer side of the mounting flange.

An on-orbit servicing spacecraft includes an engagement system to engage a space vehicle or object to be serviced or tugged, so as to form a space system, and an electronic reaction control system to cause the spacecraft to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft to carry out given maneuvers. The electronic reaction control system includes (i) a sensory system to directly sense physical quantities or allow physical quantities to be indirectly computed based on sensed physical quantities, including one or more of position, attitude, angular rates, available fuel, geometrical features, and on-board systems state, (ii) attitude control thrusters mounted so as to allow their positions and orientations to be adjustable, and (iii) an attitude control computer in communication with the sensory system and the attitude control thrusters and programmed to receive data from the sensory system and to control, based on the received data, positions, orientations, and operating states of the attitude control thrusters so as to control attitude and position of the spacecraft. The attitude control computer is programmed to cause the spacecraft to carry out a given mission including an engagement step, in which the engagement system and the attitude control thrusters are controlled by the attitude control computer to engage a space vehicle or object to be serviced or tugged, and one or more operating steps, in each of which the attitude control thrusters are controlled by the attitude control computer to meet one or more requirements established for the operating step.

An electromagnetic pulse additive device for a connection ring of a heavy-lift carrier rocket is provided. The device includes brackets, a gear disk rotatably matched with the annular ground rail through a plurality of rolls arranged in a circumferential direction of the gear disk, a first drive motor, an annular ground rail, and a guide rail in a semicircular shape arranged at top ends of the brackets. An output shaft of a first drive motor is fixedly provided with a first drive gear engaged with the gear disk. The guide rail is slidably provided with three lifting modules which respectively drive a bending module, an electromagnetic head arranged electromagnetic coil electrically connected with a capacitor and a discharge circuit, and a rotational friction and extrusion module including a second drive motor and a friction bar fixedly connected to an output shaft of the second drive motor to rise and fall.

A reprovisionable spacecraft and reprovisioning subassemblies for mating with a reprovisionable spacecraft are both described. The reprovisionable spacecraft has one or more mechanical, thermal, data, and or electrical mating interfaces for attaching, powering, and communicating with a reprovisioning subassembly, which for one embodiment is a self-contained thruster unit. The self-contained thruster unit preferably comprises a fuel tank, control electronics, and a thruster assembly. Alternately, a reprovisioning subassembly can comprise a fuel tank and control electronics, a fuel tank, or a thruster. Also, a reprovisionable spacecraft may be carried into orbit without reprovisioning subassemblies attached, and then deployed after reprovisioning subassemblies have been attached to their respective mating interfaces. Reprovisioning utilizing a self-contained thruster unit or tank eliminates the large risk associated with refueling satellites in space. Reprovisioning also eliminates the need for a dedicated attached life extension vehicle.