Systems, apparatuses, and methods provide for technology that locates one or more masses of a thunderstorm system, as the thunderstorm system starts to organize and before the thunderstorm system spawns a tornado, and controls a transmission of electromagnetic radiation from the space platform to the one or more masses, wherein the transmitted electromagnetic radiation tracks the one or more masses as the thunderstorm system is starting to organize and rotate, and wherein the transmitted electromagnetic radiation prevents the thunderstorm system from rotating and spawning the tornado.

A deformable support apparatus includes a deformable body configured to transition between at least an extended state and a contracted state where a stiffness of the deformable body in the extended state is greater than a corresponding stiffness of the deformable body in the contracted state. The deformable body includes a first member and a second member coupled to and in opposition to the first member, and arranged about a longitudinal axis. In the extended state, the first member has at least a first curved portion and the second member has at least a second curved portion. The at least a first curved portion is a positive curved portion with respect to the longitudinal axis and the at least a second curved portion is a negative curved portion with respect to the longitudinal axis.

A deformable support apparatus includes a deformable body configured to transition between at least an extended state and a contracted state where a stiffness of the deformable body in the extended state is greater than a corresponding stiffness of the deformable body in the contracted state. The deformable body includes a first member and a second member coupled to and in opposition to the first member, and arranged about a longitudinal axis. In the extended state, the first member has at least a first curved portion and the second member has at least a second curved portion. The at least a first curved portion is a positive curved portion with respect to the longitudinal axis and the at least a second curved portion is a negative curved portion with respect to the longitudinal axis.

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

System and method for direct solar energy to device transmission includes collecting and converting solar radiation energy to electrical energy by at least one satellite, generating a transmissive energy from the electrical energy, forming a transmissive energy beam, transmitting the energy beam from space directly to an electronic device located on Earth, receiving the energy beam by the electronic device's rectenna, converting the energy beam to alternating current, matching rectenna's antenna impedance with the rectenna's rectifying circuit impedance, rectifying the alternating current to direct current, and powering a load of the electronic device.

In one embodiment, an air-scoop includes an air inlet that air molecules enter the air-scoop through at an orbital speed when the air-scoop is moving through an atmosphere at the orbital speed. The air-scoop also includes a rotor that is rotated by a motor at a rotational speed, and the rotor includes multiple rotatable blade stages. A first one of the rotatable blade stages has a blade configuration that maximizes transparency of the first one of the rotatable blade stages to air molecules entering the air-scoop through the air inlet at the orbital speed when the rotor is rotating at the rotational speed. A last one of the rotatable blade stages has a blade configuration that maximizes opacity of the last one of the rotatable blade stages to air molecules in the air-scoop flowing directionally toward the air inlet when the rotor is rotating at the rotational speed.

In one embodiment, an air-scoop includes an air inlet that air molecules enter the air-scoop through at an orbital speed when the air-scoop is moving through an atmosphere at the orbital speed. The air-scoop also includes a rotor that is rotated by a motor at a rotational speed, and the rotor includes multiple rotatable blade stages. A first one of the rotatable blade stages has a blade configuration that maximizes transparency of the first one of the rotatable blade stages to air molecules entering the air-scoop through the air inlet at the orbital speed when the rotor is rotating at the rotational speed. A last one of the rotatable blade stages has a blade configuration that maximizes opacity of the last one of the rotatable blade stages to air molecules in the air-scoop flowing directionally toward the air inlet when the rotor is rotating at the rotational speed.

A launch vehicle to transport at least one payload into an earth orbit, wherein the launch vehicle comprises a plurality of solar cells on its outer surface. Furthermore, a manufacturing method for a launch vehicle with a plurality of solar cells on its outer surface and a transport method for at least one payload using a launch vehicle with a plurality of solar cells on its outer surface are provided.

A launch vehicle to transport at least one payload into an earth orbit, wherein the launch vehicle comprises a plurality of solar cells on its outer surface. Furthermore, a manufacturing method for a launch vehicle with a plurality of solar cells on its outer surface and a transport method for at least one payload using a launch vehicle with a plurality of solar cells on its outer surface are provided.

Multi-functional coilable thin-walled structures that can be implemented within space-based satellite modules, and methods for their manufacture are provided. Multi-functional coilable thin-walled structures are comprised of at least one longeron that is capable of rolling and collapsing upon itself. In some embodiments, the coilable thin-walled longeron is a flange longeron. The flange longeron contains at least two major regions: a web and a plurality of flanges. The web region comprises portions of flanges that are bonded to one another. The plurality of flanges separate from one another on the same end of the web region. The plurality of flanges are similar in thickness and shape.