Elements described herein provide enhancements for spacecraft exploration platforms. In one example, a method of space exploration is provided that includes identifying target objects for approach by a spacecraft, and determining nodal crossings of the target objects with regard to a selected orbital plane about a central body. The method also includes positioning a spacecraft into an initial orbit in the selected orbital plane, determining one or more orbital adjustments for the spacecraft that are restricted to the selected orbital plane to sequentially approach the target objects at the nodal crossings, and approaching the target objects using the one or more orbital adjustments to detect at least a characteristic related to each of the target objects.

A spacecraft is propelled by a high energy beam propulsion device that emits a high energy beam, such as a neutron beam, from the spacecraft. The high energy beam propulsion device has a neutron beam source and a neutron beam generator that emits the neutron beam through a magnetic coil. The magnetic coil may be a discrete coil or extend over a length of the neutron beam length. The magnetic coil may be self-contained and utilize natural magnets or may be a powered magnet, wherein the magnetic field is produced by a flow of electrical current. The neutron source may be powered or self-contained and utilizes neutron emitting materials including Californium-252, Cesium-137, and Polonium-Beryllium.

This invention serves as the fundamental design for a space-based, nuclear-powered spacecraft for deep space journeys. Nuclear energy is used as the motive power for the propulsion. The spacecraft propellant is a gas (such as helium or hydrogen), which is also the coolant for the onboard nuclear reactor. Nuclear energy is converted to thermal energy in the reactor, which heats up the propellant gas. That superheated gas then expands through the spacecraft nozzle and creates the thrust. The nuclear fuel consists of high enriched uranium. The amount of fuel is mission dependent, and requires declaration of payload, and desired speed, which is limited to sub-light for the first generation of this invention. The spacecraft will be assembled in, and launched from low earth orbit. The spacecraft final assembly consists of modular components delivered to low earth orbit from earth by conventional chemical rockets.

The invention relates to a satellite-supported solar storm early warning system for providing a warning signal upon approach of a solar storm to Earth, comprising a number of satellites in a region between the Earth and the Sun and stationary with respect to the center of the Earth and to the connecting line between the Earth and Sun, which satellites are respectively equipped with at least one sensor for measuring at least one parameter of a particle flow in the surroundings thereof, and all of which satellites are in radio signal connection with a receiver on Earth, directly and/or via a satellite or one of the satellites, and each of which satellites is equipped to transmit a measured value of a sensor of the system and/or a warning signal upon exceeding a threshold value by a measured value of a sensor of the system to the receiver via the radio signal connection.

The present invention provides an innovative apparatus and method for onboard spacecraft location determination and celestial navigation by employing observations of extrasolar planetary star systems. In one apparatus embodiment a gas absorption cell is placed between a sensor and the light from a reference star system with at least one exoplanet, such that the sensor can detect the spectrum through the gas absorption cell. Radial velocities can be calculated via Doppler Spectroscopy techniques and incorporated into a spacecraft navigation solution. The present invention can enable and enhance significant mission capabilities for future manned and unmanned space vehicles and missions.

A method, apparatus and composition are described for a payload delivery system capable of moving a radioactive high level waste payload from the Earth to being captured by the Sun. The payload delivery system comprises a rocket system capable of being carried and launched from an aircraft. The rocket system has at least one stage that utilizes one and only one propellant being a single liquid propellant and a final stage that utilizes pneumatic cannon driven by the final stage combustion or ullage gases to propel the radioactive high level waste payload toward the Sun.

This present invention describes initial sequential methods for constructing and placing into operation a multi-purpose maintenance complex and a space dock in high geosynchronous orbit. This is dual function complex that can provide a orbital platforms to a commercial profitable enterprise or to the Department of Defense (DoD) to enhance their capabilities. A complex will have the capability to fabricate, assemble, test, and place into full operation any size orbital and planetary surface complexes and spacecraft. DoD mission capabilities embracing satellite repairs, research, national security and deterrence, space junk disposal support and other services while in orbit.

A method of solar occultation, and in particular solar coronagraphy, employing a spacecraft 200 is disclosed. The spacecraft is controlled to achieve a position within a target zone relative to a celestial body, such as the Moon, such that the celestial body occults the Sun, allowing observations of the Sun or the space around the Sun, and in particular the Sun's corona, to be made from the spacecraft. The spacecraft has an orbit 40 around the Earth in a plane S, which like the Moon's orbit 20 in plane M, is inclined relative to the ecliptic plane E. Once inside the target zone, the spacecraft's orbit is controlled such that it remains in the target zone for longer than it would otherwise. This is achieved through the orbit within the target zone being at least partly non-Keplerian, when the orbit is under the influence of spacecraft translational thrust for example. The invention also extends to a method of controlling a spacecraft, to a spacecraft, and to a solar coronagraph comprising a spacecraft and a celestial body.

In order to collect and analyze data from the gamma-ray spectrometer of a lunar exporation satellite in real time, the present disclosure provides a system for monitoring gamma-ray spectrometer data from a satellite, comprising: a data collection unit configured to collect a raw data including a gamma-ray data from a planetary exploration satellite having a gamma-ray spectrometer; an environment setting unit configured to set and input a time range for monitoring and a display environment; a data processing unit configurd to store a filing data in which the raw data collected based on the inputted time range is classified and processed by time and by item; and a visualization unit configured to visualize the stored filing data as a graphic data.

The present invention provides an innovative apparatus and system for onboard spacecraft location determination and celestial navigation by employing spectral observations of extrasolar planetary star system motion. In one apparatus embodiment a gas absorption cell is placed between a sensor and the light from a reference star system with at least one exoplanet, such that the sensor can detect the spectrum through the gas absorption cell. Radial velocities can be calculated via Doppler Spectroscopy techniques and incorporated into a spacecraft navigation solution. The present invention can enable and enhance significant mission capabilities for future manned and unmanned space vehicles and missions.