A space seeker motion test system comprises a rough vacuum chamber including a space seeker holding fixture, a space chamber including a target to be imaged by a space seeker disposed in the space seeker holding fixture, a bellows coupling the space seeker holding fixture to the space chamber, a gate valve providing selective fluidic communication between the space seeker holding fixture and an internal volume of the space chamber through the bellows, a first vacuum pump configured to maintain the rough vacuum chamber at a rough vacuum, and a second vacuum pump configured to maintain the space chamber at high vacuum.

A space seeker motion test system comprises a rough vacuum chamber including a space seeker holding fixture, a space chamber including a target to be imaged by a space seeker disposed in the space seeker holding fixture, a bellows coupling the space seeker holding fixture to the space chamber, a gate valve providing selective fluidic communication between the space seeker holding fixture and an internal volume of the space chamber through the bellows, a first vacuum pump configured to maintain the rough vacuum chamber at a rough vacuum, and a second vacuum pump configured to maintain the space chamber at high vacuum.

Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

A space oven operates in microgravity environments by forcing convection towards the center through a unique heating element and airflow design. The space oven includes a tubular chamber, a heating rack, a heating system, a cooling system, a hatch, a user interface, a microcontroller, an enclosure, at least one first vent, at least one second vent and at least one temperature sensor. The tubular chamber is the cooking area. The heating rack holds consumables in place. The heating system heats up consumables. The cooling system prevents any overheating. The hatch closes off and allows access to the inside of the tubular chamber. The user interface allows a user to input commands. The microcontroller manages the electronic components. The enclosure protects the tubular chamber. The at least one first vent and the at least one second vent reduce pressure buildup. The at least one temperature sensor monitors the internal temperature.

A space oven operates in microgravity environments by forcing convection towards the center through a unique heating element and airflow design. The space oven includes a tubular chamber, a heating rack, a heating system, a cooling system, a hatch, a user interface, a microcontroller, an enclosure, at least one first vent, at least one second vent and at least one temperature sensor. The tubular chamber is the cooking area. The heating rack holds consumables in place. The heating system heats up consumables. The cooling system prevents any overheating. The hatch closes off and allows access to the inside of the tubular chamber. The user interface allows a user to input commands. The microcontroller manages the electronic components. The enclosure protects the tubular chamber. The at least one first vent and the at least one second vent reduce pressure buildup. The at least one temperature sensor monitors the internal temperature.

A spacecraft capable of generating an artificial gravity environment comprises frame with a circular track with at least two modules traveling on the track. The two modules are configured to engage the first track opposite the first module to minimize mass imbalance, and a balancing system for the first and second modules configured to mass balance the first and second modules relative to each other. The frame itself does not rotate, and may have other mission supporting structures attached, including storage and supply modules, and observational modules, and spacecraft hangars and spacecraft docking modules. A method of operating a spacecraft to generate artificial gravity in a habitation module comprises operating a frame in space, propelling first and second habitation modules about the frame to generate artificial gravity environments in the modules, and mass balancing the first module relative to the second module to maintain balance of the spacecraft.

Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

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 moon/planet complex, an orbiting docking spaceport, and transportation vehicles therebetween that includes i) moon/planet base station having a landing platform with a plurality of charged plates; ii) a moon/planet orbiting craft, docking spacecraft having landing platform with a plurality of charged plates; iii) a personnel transport spacecraft to shuttle personnel between an orbiting craft and planetary/moon base station having rotating electromagnetic rings 320 and/or rotating electromagnetic plates to interact with charged plates; iv) a large personnel/cargo transport spacecraft to shuttle personnel between an orbiting craft and planetary base station having rotating electromagnetic plates to interact with charged plates.

A moon/planet complex, an orbiting docking spaceport, and transportation vehicles therebetween that includes i) moon/planet base station having a landing platform with a plurality of charged plates; ii) a moon/planet orbiting craft, docking spacecraft having landing platform with a plurality of charged plates; iii) a personnel transport spacecraft to shuttle personnel between an orbiting craft and planetary/moon base station having rotating electromagnetic rings 320 and/or rotating electromagnetic plates to interact with charged plates; iv) a large personnel/cargo transport spacecraft to shuttle personnel between an orbiting craft and planetary base station having rotating electromagnetic plates to interact with charged plates.