Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, a rocket propulsion system is configured to produce thrust for a spacecraft and includes: one or more optical elements configured to receive solar energy. The optical elements include: a first window configured to allow energy to enter the rocket propulsion system and form a concentrated energy beam, and a second window positioned to allow the concentrated energy beam to pass to the heat exchanger. The second window is spaced away from the first window to form a pressurized plenum chamber therebetween. The system further includes: a heat exchanger configured to receive the energy and use it to heat and pressurize a propulsion gas, and a rocket nozzle configured to expel the pressurized propulsion gas.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.

Solar collectors can provide power for electricity, thermal propulsion, and material processing (e.g., mining asteroids). In one aspect, an apparatus for collecting solar energy and simultaneously protecting against damage from a resulting energy beam includes a solar energy collection system including at least one concentrator and a target configured to use, store, or convert the solar energy, the collection system configured to cause solar energy to focus on the target, at least one sensor configured to detect misalignment of the concentrator by determining that some or all of the collected solar energy is offset from the target, and a safety system configured to redirect the energy or interpose a safety structure for shielding other non-target systems from receiving too much solar energy from the collection system.

A fusion reactor includes a fusion plasma reactor chamber. A magnetic coil structure is disposed inside of the fusion plasma reactor chamber, and a structural component is also disposed inside of the fusion plasma reactor chamber. The structural component couples the magnetic coil structure to the fusion plasma reactor chamber. A superconducting material is disposed at least partially within the structural component. A plurality of cooling channels are disposed at least partially within the structural component. An insulating material is disposed at least partially within the structural component.

A method of reducing solar irradiance the Earth receives includes placing a solar parasol in sun-synchronous orbit between the Earth and the Sun. The solar parasol provides a reflective shield that faces the Sun. The reflective shield is supported by a frame and a method of positioning the solar parasol in sun-synchronous orbit. The shield may include a coating layer and a gold film layered over the coating layer on the sun-facing surface of the shield, while a heat sink is provided on an opposing surface of the shield.

A method of reducing solar irradiance the Earth receives includes placing a solar parasol in sun-synchronous orbit between the Earth and the Sun. The solar parasol provides a reflective shield that faces the Sun. The reflective shield is supported by a frame and a method of positioning the solar parasol in sun-synchronous orbit. The shield may include a coating layer and a gold film layered over the coating layer on the sun-facing surface of the shield, while a heat sink is provided on an opposing surface of the shield.

A part of a spacecraft, for instance an upper stage, is configured to re-enter into the atmosphere and to be reused for several missions. The part is equipped with a reusable kit comprising non-ablative heat shields, for example constructed with an outer surface formed of Ceramic Matrix Composites, such as Ultra High Temperature Ceramic Matrix Composites, and optionally at least one decelerator and/or at least one parachute and/or parafoil system.

Systems (100) and methods (600) for providing a product with a radiation mitigation feature. The methods comprise: obtaining a composite base layer formed of a fiber-reinforced material; and performing a deposition process to dispose a first coating layer on the composite base layer so as to form the product with a radiation barrier, the first coating layer comprising 35% by mass or less of a metal constituent, at least 65% by mass of a germanium constituent, a zero or substantially zero coating stress, and/or an overall thickness between 2 microns and 8 microns.

In a method of facilitating flight operations, a payload is coupled to a spacecraft via a payload interface. The relative alignment of the payload and the spacecraft is dynamically adjusted (e.g., for thrust alignment) while the payload remains coupled to the spacecraft.

The present disclosure relates to deployable structures and methods of use thereof. In particular, deployable structures with non-cylindrical or irregular shapes and methods of use thereof are disclosed. Non-cylindrical combustion elements can be used to rigidize such non-cylindrical or irregular shapes. The use of gaseous oxidizers along with deployable structures is also disclosed.