A satellite system includes a satellite in an orbit that is configured to reduce a number of exclusion regions and improve the observation coverage of resident space objects (RSOs) positioned in near Earth orbits. The satellite system includes at least one satellite positioned in a sun synchronous orbit (SSO) with a noon/midnight nodal crossing. The altitude of the SSO is between 1000 and 2000 kilometers and the satellite includes at least one sensor arranged on the satellite that is configured for detection, tracking, and/or identification. Using the noon/midnight nodal crossing is advantageous in that three main exclusion regions, the sun, eclipse, and Earth exclusion regions, are combined into only two exclusion regions for improved performance of the satellite system in observing RSOs.

Methods and devices to implement mid-wave and long-wave infrared point spectrometers are disclosed. The described methods and devices involve bi-faceted gratings, high-operating-temperature barrier infrared and thermal detectors. The disclosed concept can be used to design flight spectrometers that cover broad solar reflectance plus thermal emission spectral ranges with a compact and low-cost instrument suitable for small spacecraft reconnaissance of asteroids, the Moon, and planetary satellites as well as mass-constrained landed missions.

A system utilizing an antenna generating an electromagnetic (EM) wave to interact with a solar EM wave to streamline magnetic flux in the polar cusp and to facilitate the flow of solar plasma through the Polar Cusp, resulting in an elevated plasma flux at the exit of the Polar Cusp. The elevated plasma flux intercepts and removes small space debris from Low Earth Orbit (LEO), Geosynchronous Earth Orbit (GEO) and Geosynchronous Transfer Orbits (GTO) transiting the LEO altitude regimes.

Systems and methods for obtaining images of a lunar surface and cislunar space using a hybrid telescope are provided. One hybrid telescope is carried by each of two spacecraft. Each spacecraft is in an elliptical orbit about the Moon. The periapsides of the spacecraft orbits are 180° apart from one another. In addition, the spacecraft can be phased 180° apart from one another to enable an offset in access times of each telescope to the cislunar and surface domains respectively. The image sensors associated with the telescopes can include a staring mode for collecting images from cislunar space, and a scanning mode for collecting images from the lunar surface.

The present invention relates to a resident space object orbit determination system comprising a high efficiency module for determining a resident space object's orbit and a highly efficient method for determining same. Applicants developed a method and system to determine the orbits of residence space objects including resident space objects that do not reflect energy that is directed at them and/or may be coated to minimize the ability to accurately see such resident space objects. Thus, a method, a module and a system for making such determinations that can easily and inexpensively be added to an early warning reentry system is provided.

NASA, ESA, and Japanese Space Agency (JAXA) have undertaken studies (e.g., “Lunar Ice-Trap ISRU Mining, Processing and Storage Infrastructure: An infrastructure that mines and breaks down lunar ice into oxygen and hydrogen fuel”) to determine likely sources of water and oxygen for human colonies on Mars or Moon. Some of these studies are university-level research through fund allocations for departmental research, or through student interest in space exploration. Other studies are conducted at national levels through space agencies and through privately funded space probes. One of these studies was executed by the JAXA determined the source of the lunar-ice on the Moon (from the Kaguya/ZELENE lunar probe). JAXA estimated that 90 metric tons of Earth's atmosphere escapes per day with oxygen ions reaching energies of between 1 keV and 10 keV.

A reconnaissance rover configured for multiple agile and autonomous landings over a small body or moon. The reconnaissance rover comprises a detection unit, a processing unit, a control unit and a drive unit. The detection unit is configured to detect at least an environment in front of the reconnaissance rover, in the direction of a trajectory of the reconnaissance rover over a surface of the small body or moon. The detection unit is further configured to provide environmental data based on the detected environment. The processing unit is configured to update the trajectory based upon the provided environmental data. The control unit interacts with the drive unit to move the reconnaissance rover according to the updated trajectory.

A system utilizing an antenna generating an electromagnetic (EM) wave to interact with a solar EM wave to streamline magnetic flux in the polar cusp and to facilitate the flow of solar plasma through the Polar Cusp, resulting in an elevated plasma flux at the exit of the Polar Cusp. The elevated plasma flux intercepts and removes small space debris from Low Earth Orbit (LEO), Geosynchronous Earth Orbit (GEO) and Geosynchronous Transfer Orbits (GTO) transiting the LEO altitude regimes.

Based on determined locations of Kukharev (K) regions, and the estimated times of their formation on Earth, in the atmosphere, and in space, antimatter may be produced and collected, as described by the present invention. Due to jumps in the gravitational field, various standing waves are formed from the resonances of the gravitational tides. A wave of charged particles is formed within the K region and can be setup to collide with targets comprising heavy metal atoms (or other equivalents), the colliding thereby creating antimatter particles. These antimatter particles can then be stored in various traps and used for various purposes, e.g., energy formation.

A system utilizing an antenna generating an electromagnetic (EM) wave to interact with a solar EM wave to streamline magnetic flux in the polar cusp and to facilitate the flow of solar plasma through the Polar Cusp, resulting in an elevated plasma flux at the exit of the Polar Cusp. The elevated plasma flux intercepts and removes small space debris from Low Earth Orbit (LEO), Geosynchronous Earth Orbit (GEO) and Geosynchronous Transfer Orbits (GTO) transiting the LEO altitude regimes.