Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.

A nuclear reactor system includes a nuclear reactor core disposed in a pressure vessel. Nuclear reactor system further includes control drums disposed longitudinally within the pressure vessel and laterally surrounding fuel elements and at least one moderator element of the nuclear reactor core to control reactivity. Each of the control drums includes a reflector material and an absorber material. Nuclear reactor system further includes a control drum controller with a counterweight to impart a reverse torque on the control drum. Control drum controller includes a driven pulley coupled to the counterweight, a tension member coupled to the driven pulley to rotatably control the driven pulley and apply torque to the driven pulley, and an actuator to apply a tension force to the tension member. The actuator counteracts the reverse torque with the applied tension force, and the tension member applies the torque in response to the tension force.

A thermal power reactor (100) includes a reactor core (102) that generates thermal energy and a solid state thermal conductor (106) extending into and thermally integrated with the reactor core (102). The solid state thermal conductor (106) transfers thermal energy generated by the reactor core (102) away from the reactor core (102).

An electromagnetic propulsion system for the movement of spacecraft by means of ejection of the perturbed dark matter. In the present invention, to perturb and accelerate the dark matter, the electromagnetic energy generated by microwave generators is supplied to a number of position-adjustable electromagnetic vibrators that form a phased antenna array inside the waveguide. Since the dark matter permeates the Universe and its reserves are unlimited, it can be used as a working medium in the constant acceleration propulsion system for as long as the electric power supply lasts. Since the electromagnetic propulsion system has infinite reserves of the working medium, the specific impulse is also infinite. The speed of the dark matter jet approaches the speed of light.

The disclosure describes various aspects of a space-based radioisotope production system and methods use. In one aspect, a propellant is accelerated by decay energy to yield thrust. The decay energy is provided by activating a target material. In one aspect, a radioisotope rocket thruster may be recharged or “reactivated” in a space-borne charging station. The activated isotopes may also be used generate electricity. The space-borne charging station may also be used for irradiating other items in space for any number of purposes.

A method for generating a fissile material is described. The method includes positioning a fertile, non-fissile material within outer space, the position within an area of proton or other high energy particle radiation, rather naturally or artificially occurring, allowing the high energy particle radiation to impinge the fertile but non-fissile material over a time, the time based on amount of high energy particle radiation at the position, such that the non-fissile material gradually transmutes into a fissile material due to the impingement, and deploying the fissile material within a spacecraft.

A control system configured to execute a safing mode sequence for a spacecraft is disclosed. The control system includes one or more star trackers that each include a field of view to capture light from a plurality of space objects surrounding the celestial body. The control system also includes one or more actuators, one or more processors in electronic communication with the one or more actuators, and a memory coupled to the one or more processors. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to determine a current attitude of the spacecraft, and re-orient the spacecraft from a current attitude into a momentum neutral attitude.

Disclosed are a method of flying on the moon and a device for flying using the method. A medium on a surface of a moon and a medium accelerating module are used in the flying method. The medium is transferred into the medium accelerating module, accelerated by the medium accelerating module, and ejected out of the medium accelerating module by using a power supply. A counterforce is generated in accordance with the momentum conservation, and the counterforce overcomes the lunar gravity and drives a load to take off. The method is suitable for the environment of the moon where flight by means of atmospheric buoyancy is impossible due to the shortage of atmosphere.

An electromagnetic propulsion system for the movement of spacecraft by means of ejection of the perturbed dark matter. In the present invention, to perturb and accelerate the dark matter, the electromagnetic energy generated by microwave generators is supplied to a number of position-adjustable electromagnetic vibrators that form a phased antenna array inside the waveguide. Since the dark matter permeates the Universe and its reserves are unlimited, it can be used as a working medium in the constant acceleration propulsion system for as long as the electric power supply lasts. Since the electromagnetic propulsion system has infinite reserves of the working medium, the specific impulse is also infinite. The speed of the dark matter jet approaches the speed of light.

Methods, systems, and devices for satellite operations are described. A system for satellite communications may include a payload, a power system, and a thermal management component. The payload may be configured to provide a service with varying levels of capacity based on a demand profile. The payload may consume electrical energy at a peak rate when a level of demand indicated by the demand profile is above a threshold and at a lower, off-peak rate when a level of demand indicated by the demand profile is below a threshold. The peak rate may exceed a rate at which electrical energy is generated by the power system. The thermal management component may process excess thermal energy generated by the payload when the payload operates at the peak rate. Processing the excess thermal energy may include storing thermal energy while the payload operates at the peak rate.