Abstract: A spacecraft includes a body having a motor, a lander interface, a sensor and a power source for powering the motor and the sensor, and the power source being mounted thereon. An integrated avionics unit has a module and an integrated circuit with the module having a central computer and a motor controller for controlling the motor and the integrated circuit having a temperature monitoring system for monitoring the temperature of the spacecraft and a power regulator having a cell balancer for regulating the power of the power source. The module and the integrated circuit are connected to one another for constant communication therebetween. The central computer communicates with the sensor.

Abstract: A system can include a reservoir configured to hold working material, a decontamination module configured to remove contaminants from the working material, a flow control mechanism configured to regulate working material flow between the reservoir and the decontamination module, and a manifold fluidly connecting the reservoir to the decontamination module.

Abstract: A system can include a reservoir configured to hold working material, a decontamination module configured to remove contaminants from the working material, a flow control mechanism configured to regulate working material flow between the reservoir and the decontamination module, and a manifold fluidly connecting the reservoir to the decontamination module.