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 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.

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.

Disclosed is a testing apparatus and a testing method using the same, the apparatus having soil in a vacuum chamber includes: a buffer chamber having an entrance/exit opening through which an object to be inspected is inserted, and a first door for opening and closing the entrance/exit opening; a testing chamber divided at one side of the buffer chamber so as to be separated therefrom, and having a connection passage communicating with the buffer chamber; a shutter unit for opening and closing the connection passage; a soil storage part disposed inside the testing chamber, and accommodating soil for testing the object to be inspected; and a vacuum generation means for suctioning air inside the buffer chamber and the testing chamber so as to create a vacuum state.

Disclosed is a testing apparatus and a testing method using the same, the apparatus having soil in a vacuum chamber includes: a buffer chamber having an entrance/exit opening through which an object to be inspected is inserted, and a first door for opening and closing the entrance/exit opening; a testing chamber divided at one side of the buffer chamber so as to be separated therefrom, and having a connection passage communicating with the buffer chamber; a shutter unit for opening and closing the connection passage; a soil storage part disposed inside the testing chamber, and accommodating soil for testing the object to be inspected; and a vacuum generation means for suctioning air inside the buffer chamber and the testing chamber so as to create a vacuum state.

A computer-implemented system and method for testing a space-destined payload in which the system comprises one or more test cells. Each test cell designed to test a space-destined payload within a test environment. Payload specifics and the payload space trajectory are provided to the system, which then designs a test environment for each test cell and then executes one or more tests on the payload within the test environment of each cell.

The present disclosure provides a data acquisition and control system of pulsed power supply for multi-load, and relates to the technical field of pulsed power. The system of the present disclosure is configured to control 18 sets of pulsed power supplies to provide 18 coils with stable and reliable excitation current featuring multiple output time sequences and flexible adjustability, such that a near-earth space plasma environment ground-based simulation device can simulate the magnetic field topology of the earth magnetosphere and realize a background magnetic field required by physical experiments. The system mainly achieves the following functions: control over charge and discharge of pulsed power supplies, selection of power supplies put in use, delay trigger setting, voltage monitoring, status monitoring of key components and output current display; and it is also necessary to realize failure alarm and failure handling for the purpose of ensuring the safety of equipment and personnel.

A modular satellite testing platform system having an upper and a lower member along with a plurality of support members, intermediate members, and lower bar members that are interconnected to the upper member and the lower member. The system further includes a plurality of shelf members that are attached to the support members. The satellite also includes a plurality of bottom cover members that are attached to the lower member by a plurality of hinge members that allow the cover members to selectively rotated about an axis to be rotatably translated between an opened position and a closed position. The system yet further includes a thermal control system to allow maintaining the thermals of the satellite as desired.

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.