A multi-purpose planet planetary exploration rover is provided in this invention, which relates to the field of planet exploration. The multi-purpose planetary exploration rover includes a case body, mounted with a first wheel at left and right sides respectively; and a cantilever, having a front end connected to the case body, a rear end of the cantilever being mounted with a second wheel; wherein the cantilever is rotated or fixed relative to the case body, the second wheel is steered relative to the cantilever, and the first wheel and the second wheel are used to drive the multi-purpose planetary exploration rover. Compared with the prior art, the multi-purpose planetary exploration rover of this invention can effectively explore special geographic locations such as cliffs, volcanic craters, craters and lava caves on alien planets.

A multi-purpose planet planetary exploration rover is provided in this invention, which relates to the field of planet exploration. The multi-purpose planetary exploration rover includes a case body, mounted with a first wheel at left and right sides respectively; and a cantilever, having a front end connected to the case body, a rear end of the cantilever being mounted with a second wheel; wherein the cantilever is rotated or fixed relative to the case body, the second wheel is steered relative to the cantilever, and the first wheel and the second wheel are used to drive the multi-purpose planetary exploration rover. Compared with the prior art, the multi-purpose planetary exploration rover of this invention can effectively explore special geographic locations such as cliffs, volcanic craters, craters and lava caves on alien planets.

A space vehicle comprising an optical system having a field of view, the optical system comprising at least two optical elements spaced from one another along an optical axis, thereby defining an interior cavity; at least one control system comprising at least one physical element configured for performing function(s) for enabling operation of the vehicle; and at least one holding assembly for holding the at least one control system and comprising a folding mechanism configured to move between a folded position corresponding to an inoperative mode of the optical system, and a deployed position corresponding to an operative mode of the optical system, such that in the folded position, the control system is at least partially located in the interior cavity for stowage, and in the deployed position, the control system is located outside the interior cavity and outside the field of view of the optical system, allowing operation of the optical system.

A reconnaissance rover configured for multiple agile and autonomous landings over a small body or moon. The reconnaissance rover comprises a detection unit, a processing unit, a control unit and a drive unit. The detection unit is configured to detect at least an environment in front of the reconnaissance rover, in the direction of a trajectory of the reconnaissance rover over a surface of the small body or moon. The detection unit is further configured to provide environmental data based on the detected environment. The processing unit is configured to update the trajectory based upon the provided environmental data. The control unit interacts with the drive unit to move the reconnaissance rover according to the updated trajectory.

A real-time scheduling apparatus and method for suppressing battery aging of a satellite system are disclosed. A real-time scheduling method for suppressing battery aging of a satellite system according to an exemplary embodiment of the present disclosure may include acquiring task information including a request period and an execution time of each of a plurality of tasks which is performed in the satellite system; determining an execution limit range and an execution order for each of the plurality of tasks which satisfies a predetermined real-time constraint based on the task information; and determining an optimal execution timing within the execution limit range of each of the plurality of tasks, based on the execution order and consumed current information of each of the plurality of tasks.

A radioactive power generation system is disclosed, the system comprising a radioactive power generator and a releasable antiproton containment. The radioactive power generator includes a radioisotope material. The releasable antiproton containment comprising a plurality of antiprotons contained in isolation from the radioisotope material. The releasable antiproton containment is configured to selectively release the antiprotons from the releasable antiproton containment such that the antiprotons can annihilate the radioisotope material in a fission event to reenergize the radioactive power generator.

A rover can include a spherical shall and an avionics hub. The spherical shell defines a spherical volume and having an inner surface and an outer surface. The avionics hub is disposed within the spherical volume. The avionics hub includes an avionics shell, a data acquisition unit, and a plurality of motortrain assemblies. The avionics shell is disposed with the spherical volume of the spherical shell. The data acquisition unit is disposed within the avionics shell. Each motortrain assembly includes a motorized wheel extending at least partially through the avionics shell and in contact with the inner surface of the spherical shell, the plurality of motortrain assemblies configured to rotate the spherical shell relative to the avionics shell to move the rover.

A wafer-scale satellite bus and a manner of making the same include using wafer reconstruction techniques to stack functional diced circuits onto each other and bond them. The disclosed techniques allow for a variety of functions in each die, including providing, without limitation: ground-based communications, attitude and propulsion control, fuel tanks and thrusters, and power generation. The wafers are initially manufactured according to a common wafer design that provides electrical and power interconnects, then different wafers are further processed using subsystem-specific techniques. The circuits on differently-processed wafers are reconstructed into a single stack using e.g. wafer bonding. Surface components are mounted, and the circuitry is diced to form the final satellites. Mission-specific functions can be incorporated, illustratively by surface-mounting, to the bus at an appropriate stage of assembly, on-wafer circuitry or instrument packages for performing these functions.

A flying capacitor multilevel (FCML) converter including a gate driver circuit comprising a DC-DC flyback converter having a plurality of isolated outputs. In various examples, the FCML circuit further includes a first control circuit connected to the FCML circuit determining the load current associated with a desired power output from the load; and determining a desired output voltage associated with the load current; a second control circuit that drives an inductor current (I.sub.L) through the inductor so that the output applies an output voltage comprising the desired output voltage; and a third control circuit obtaining a comparison of an average of the inductor current (I.sub.L) through the inductor with a predetermined reference current (I.sub.LREF) and setting the duty cycle so that the average does not exceed the predetermined reference current. Also described is the converter driving a load comprising a plasma and a propulsion system comprising the converter.

A sublimation generator including a sublimation tank configured to receive ice including at least carbon dioxide. The sublimation generator also includes a first heat exchanger in thermal communication with the sublimation tank. The first heat exchanger being configured to expel heat from a coolant into the sublimation tank to sublimate the carbon dioxide into a gaseous state. The sublimation generator also includes a gas turbine generator fluidly connected to the sublimation tank and configured to receive the carbon dioxide in the gaseous state.