An innovative landing system for a spacecraft according to the invention includes a foldable tether-based carrier structure that when unfolded assumes wheel-type shape and in its centre supports a carrier platform for the payload of the spacecraft.

A pair of opposing, spaced apart bracket assemblies is mounted on a lower surface of a landing vehicle deck with each bracket assembly having a latch receiver extending therefrom. A pair of opposing, spaced apart latch assemblies is mounted on an upper surface of an exploration vehicle with each latch assembly having a latch pivotally mounted for releasably engaging one of the bracket assembly latch receivers. A plurality of tethers with each tether releasably connecting one of plurality of wheels to the landing vehicle deck is provided. Each of the latch assembly latches pivots relative to the exploration vehicle upper surface to disengage from one of the bracket assembly latch receivers, so that the plurality of tethers suspend the exploration vehicle from the landing vehicle deck.

Stacked satellite dispensing systems are described herein. The disclosed systems can release individual satellites or small batches of satellites from a satellite stack in a controlled manner. Dispensing individual satellites at different locations in space can more evenly dispense satellites or to dispense satellites at distinct locations. A deployment system, including a motor, a cable, and spacers, can allow for the individual satellites to be deployed from the satellite stack. The disclosed satellite dispensing systems also include spacers that are positioned between two or more satellites to help attenuate the force of the mass of satellites stacked above.

A passive landing system for decelerating a payload delivered from orbit or at orbital velocity onto a non-atmospheric celestial body, including a catcher assembly positioned to intercept incoming payloads at orbital speeds, and a deceleration system mechanically coupled to the catcher assembly and extending along a sloped terrain, wherein the system decelerates the payload by exchanging momentum between the descending payload and the extended deceleration system, without the use of propulsion. A landing system for oversized payloads on a non-atmospheric celestial body, which can be used in combination with the passive landing system, including a structure configured to house and secure large-volume cargo during descent and deceleration, a surface interaction mechanism configured to establish frictional contact with regolith of the celestial body, and a dynamic deployment system that controls the extent and duration of surface contact during descent, wherein the landing system decelerates primarily by converting kinetic energy into heat and mechanical resistance through friction with the regolith.

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 spacecraft servicing device may include a thruster assembly coupled to a boom arm, where the boom arm is configured to alter an orientation of the thruster assembly as the boom arm is rotated about the spacecraft body and a docking device.

A device comprises a solenoid of reinforced HTS material, wherein the solenoid of reinforced HTS material comprises a plurality continuous ordered fibers embedded in a high temperature superconducting material. A device comprises one or more coils, wherein the one or more coils comprise HTS solenoids; an armature coupled to a stem in a control valve, wherein the armature comprises a HTS solenoid; and coolant access paths, wherein the coolant access paths enable cooling the one or more coils and the armature. A device comprises a photovoltaic cell; and a parallel array of HTS solenoids, wherein the parallel array of HTS solenoids is coupled to the photovoltaic cell.

Spacecraft servicing devices and related methods may include a propellant tank configured to store a propellant and to be placed into fluid communication with a portion of the target spacecraft.

Deployable devices, systems, and methods are provided. Some embodiments include a system that may include: multiple frames configured to support multiple elements; multiple longerons; multiple diagonals coupled with the multiple longerons; and multiple battens. One or more battens may be coupled with at least one or more longerons and one or more frames such that the respective batten is offset at least along a length of the respective longeron with respect to at least a hinge point between the respective longeron and another longeron from the multiple longerons or along a length of the respective frame with respect to a hinge point between the respective frame and another frame from the multiple frames. Some embodiments include a method for ensuring synchronous deployment of a system that may include orienting a hinge axis coupled with at least one longeron substantially perpendicular to a hinge axis coupled with two or more frames.

The present invention discloses an ejection deployment and retrieval mechanism for a tethered satellite with repeatable unlocking and locking and a working method thereof, the present invention includes a separation ejection docking assembly and a sub-satellite; the separation ejection docking assembly includes an ejection sleeve, a locking mechanism, and a sub-satellite connector, the ejection sleeve adopts a two-stage internal-external sliding connection and provides initial kinetic energy to the sub-satellite by compressing a spring; the locking mechanism is mounted inside the ejection sleeve, one end of the sub-satellite connector is connected to the sub-satellite, and another end of the sub-satellite connector is slidably engaged with the locking mechanism to complete the locking/unlocking operations of the sub-satellite. The present invention can effectively reduce the complexity of the mechanism and improve the overall reliability of the mechanism without the additional control assembly to control the unlocking and locking of the mechanism.

Stacked satellite dispensing systems are described herein. The disclosed systems can release individual satellites or small batches of satellites from a satellite stack in a controlled manner. Dispensing individual satellites at different locations in space can more evenly dispense satellites or to dispense satellites at distinct locations. A deployment system, including a motor, a cable, and spacers, can allow for the individual satellites to be deployed from the satellite stack. The disclosed satellite dispensing systems also include spacers that are positioned between two or more satellites to help attenuate the force of the mass of satellites stacked above.