Systems, methods and devices for planet observation are provided. A planet observation system is provided, comprising at least one vehicle comprising one or more sensors on board at least one vehicle, the at least one vehicle configured to follow a trajectory around a celestial body; and a control system comprising memory and a processor(s), the memory including one or more modules that are executable by the processor(s) to: direct, based at least in part on a geometric ground pattern covering partially or wholly a surface or volume of the celestial body, the one or more sensors to collect data; and store the data in memory on-board the at least one vehicle and/or transmit the data to another location. A computer-implemented planet observation method and a computer-implemented method of designing a geometric ground pattern for at least one vehicle configured to orbit around a celestial body are also provided.

A satellite that includes a housing, a circuit board containing circuitry and disposed in the housing, a battery disposed in the housing and electrically connected to the circuit board, one or more weights disposed in the housing, wherein the one or more weights are disposed away from a center of the housing, one or more solar panels on the housing and electrically connected to the circuit board, and an antenna electrically connected to the circuit board and including at least one segment that extends out of the housing. When multiple satellites are launched into orbit having different mass weights, they move away from each other at least partially because of the weight difference. In orbit, each satellite is subjected to aerodynamic drag torque and gravity gradient torque.

A constellation of satellites may include a plurality of satellites in each of two or more different orbits. Satellites in a given orbit may operate in pairs, flying in tandem, one satellite leading, the other trailing closely behind, to be positioned to image the same target(s) of interest with substantially the same orientation (geographical coincident) at substantially the same time (temporally coincident). The first satellite may acquire SAR data, determine a location of a target of interest, assess cloud cover, and based on an extent of cloud cover, can acquire additional SAR data or cause the second satellite to capture optical imaging data (e.g., cross-cueing). Selection of orbits can provide a relatively high revisit rate may be obtained, allowing frequent opportunities to image given locations on a planet (e.g., Earth). One or more ground stations communicate with the constellation of satellites, and inter-satellite communications may be employed.

The invention concerns a method for reducing the costs of a satellite remote sensing service. The method comprises providing a satellite remote sensing system that includes only one satellite equipped with a sensor configured to acquire images of areas of the earth's surface, the satellite remote sensing system being designed to provide a satellite remote sensing service based on the images acquired by the sensor on board the satellite. In particular, the satellite follows a predefined orbit around the earth with an orbit repeat cycle shorter than three days, whereby a satellite remote sensing service with very good time performance, excellent interferometric capabilities and with drastically reduced costs is obtained.

A satellite constellation forming system forms a satellite constellation (20) including two orbital planes each having a different normal direction and in each of which the same number of satellites fly. A satellite constellation forming unit gradually changes an orbital altitude of at least one orbital plane of the two orbital planes from a state in which satellite passage timings of satellites flying in the two orbital planes do not coincide with each other at an intersection neighborhood point (Pc) between the two orbital planes in each of the two orbital planes, while maintaining the state in which the satellite passage timings do not coincide with each other.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

Described herein is a method for wireless transmission of energy in space, wherein a constellation of transmitting satellites orbiting around a celestial body, such as the planet (P) Earth or the Moon (L), are equipped with a laser apparatus for sending a beam of coherent electromagnetic waves to an orbiting satellite or another receiving target, such as a mobile vehicle or a fixed base on said generic celestial body, in order to transmit energy thereto. The total power transmitted is divided among the orbiting satellites in the constellation, resulting in less contraindications than in the case of a single transmitting system with equivalent total power. The advantage of such division among a constellation of satellites mainly consists of shorter periods of solar eclipse, since sunlight is necessary for the operation of the transmission system. The receiving target or satellite converts the beam of electromagnetic waves into electric energy.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.