A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.

The embodiments herein provide a system and method for integrated optimization of design and performance of satellite constellations. The present disclosure provides a method for optimization of design and performance of satellite constellation to provide internet connectivity at preset geographic regions. In current methods, the optimizations of subsystems are performed independently and the results are combined, resulting in a loss of overall optimality. The present disclosure defines the relationships between subsystems such that integrity of complete design is tested with fewer complexities and provides an integrated optimization framework, in which every subsystem is optimized individually and collectively. The present disclosure provides a method for optimization of power subsystem of satellites by determining the pattern of payload operation and need for peak power. The present disclosure also provides a method to minimize the number of satellites required in constellations by carefully regulating spot beams formed by individual satellites in constellations.

A combination two vehicle system is provided that includes a land-based vehicle configured for traversal over ground and an aerial vehicle configured for travel through air, where the aerial vehicle is configured to detachably couple with the land-based vehicle. The aerial vehicle includes stabilizing legs to provide stability for take-off or landing. A method of operating the vehicle system includes steps of: providing the land-based and the aerial vehicle having the stabilizing legs, and aerially transporting the vehicle system including the land-based vehicle and the aerial vehicle, where the stabilizing legs provide stability for take-off or landing. In addition, the land-based vehicle may transport a removable cargo pod, which the aerial vehicle may independently retrieve from the land-based vehicle.

A matrix thruster that may be used to reposition and/or stabilize a CubeSAT satellite. The matrix thruster includes a conductive plate with an opening, a plurality of wires within the opening, a power supply electrically connected to the conductive plate or each of the plurality of wires via an inductor, and an electrical switch. The electrical switch creates a current change that creates an electric potential spike across the inductor. The electric potential spike across the inductor initiates an arc discharge between one of the wires and the conductive plate, which forms plasma that ejects cathode particles from the matrix thruster. Using multiple wires (e.g., four titanium wires) extends the lifetime of the thruster, as each wire restores an inter-electrode film needed for the other wires to continue generating plasma.

This invention relates to a power supply module for nanosatellite systems which will find application in the field of space technology and satellite communications, and in particular for powering nanosatellites. The created power supply module consists of at least one battery pack and at least one control and energy distribution module and provides maximum efficiency at a given illumination by adjusting the operating output voltage of the input stages (1.1, 1.2 and 1.3) according to the illumination of the panels. All nodes in the module are duplicated, which achieves complete redundancy of the module, which is activated after the main node is defective, or when the load is greater than the load which this main node can withstand. The use of power busbars, on the other hand, leads to a reduced voltage drop on the respective line, as well as to lower temperature losses. The input channels for the solar panels are transferred to the battery pack and it is possible to connect them in parallel when there are more than one.

Ruggedized avionics assemblies for use on kinetically launched space vehicles are disclosed. The avionic assemblies are able to maintain structural integrity and functionality under high acceleration forces generated during kinetic launch, including acceleration forces of >5,000 times Earth's gravity in a single direction of loading. The avionics assembly is ruggedized to withstand this level of acceleration force during launch via a plurality of constraining elements to constrain a plurality of printed circuit boards aligned in parallel to an acceleration vector. Further, a high specific strength and stiffness composition of the plurality of constraining elements aids in supporting the printed circuit boards and preventing them from bending and dislodging electronic components mounted to the printed circuit boards.

A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure

A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions to include propellant tank pressurization, attitude control, vehicle settling, and electrical requirements. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a starter/generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle settling thrusters. Accumulators which store the waste ullage gases are pressurized and provide pressurization control for the propellant tanks. The system is constructed in a modular configuration in which two redundant integrated fluid modules may be mounted to the vehicle, each of the modules capable of supporting the upper stage functions.

A space vehicle electromechanical system may employ an architecture that enables convenient and practical testing, reset, and retesting of solar panel and antenna deployment on the ground. A helical antenna winding fixture may facilitate winding and binding of the helical antenna.

Ruggedized avionics assemblies for use on kinetically launched space vehicles are disclosed. The avionic assemblies are able to maintain structural integrity and functionality under high acceleration forces generated during kinetic launch, including acceleration forces of >5,000 times Earth's gravity in a single direction of loading. The avionics assembly is ruggedized to withstand this level of acceleration force during launch via a plurality of constraining elements to constrain a plurality of printed circuit boards aligned in parallel to an acceleration vector. Further, a high specific strength and stiffness composition of the plurality of constraining elements aids in supporting the printed circuit boards and preventing them from bending and dislodging electronic components mounted to the printed circuit boards.