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.

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.

UAV (400, 500, 600) systems and methods for simulation of reduced-gravity environments are disclosed. A UAV (400, 500, 600) system has an ascent vehicle (104), comprising ascent thrust means, and an aerodynamic, free fall descent UAV (102, 706), comprising descent thrust means. The ascent vehicle (104) comprises means to convey the descent UAV (102, 706) to a drop altitude (108), and the descent UAV (102, 706) is separable from the ascent vehicle (104). The descent thrust means is operable, following separation of the descent UAV (102, 706) from the ascent vehicle (104), to provide a thrust component in a descent direction (256), for countering air resistance on the UAV (400, 500, 600). The descent UAV (102, 706) may comprise a sensor system and controller (204), and the descent thrust means may comprise a ducted fan system. The sensor system may be operable, during descent of the UAV (400, 500, 600), to determine values for parameters associated with the acceleration due to gravity of the UAV (400, 500, 600), the controller (204) being operable to use the determined parameter values to control the ducted fan system to provide the thrust component.

UAV (400, 500, 600) systems and methods for simulation of reduced-gravity environments are disclosed. A UAV (400, 500, 600) system has an ascent vehicle (104), comprising ascent thrust means, and an aerodynamic, free fall descent UAV (102, 706), comprising descent thrust means. The ascent vehicle (104) comprises means to convey the descent UAV (102, 706) to a drop altitude (108), and the descent UAV (102, 706) is separable from the ascent vehicle (104). The descent thrust means is operable, following separation of the descent UAV (102, 706) from the ascent vehicle (104), to provide a thrust component in a descent direction (256), for countering air resistance on the UAV (400, 500, 600). The descent UAV (102, 706) may comprise a sensor system and controller (204), and the descent thrust means may comprise a ducted fan system. The sensor system may be operable, during descent of the UAV (400, 500, 600), to determine values for parameters associated with the acceleration due to gravity of the UAV (400, 500, 600), the controller (204) being operable to use the determined parameter values to control the ducted fan system to provide the thrust component.

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 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.

Provided is a deployment test apparatus including a fixing frame configured to fix a first portion of a target object in which the first portion is hingedly coupled to a second portion, a rotation axis module including a rotary shaft and disposed on one side of the fixing frame, a rotary arm radially extending from the rotary shaft in an upper portion of the fixing frame, and a support module connected to the rotary arm to clamp the second portion of the target object to be floated, wherein when deploying the target object, the deployment test apparatus is configured to reduce an external force applied to the target object.

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.