Provided are an artificial satellite and a method of controlling the same. The artificial satellite includes a main body flying along an orbit of a planet, an optical payload arranged on the main body to photograph a ground surface of the planet, and a pair of solar cell panels rotatably arranged on both sides of the main body in a first direction, wherein the first direction and a flight direction of the main body form an acute angle with each other.

Disclosed is an environment forming apparatus suitable for biological cultivation in extraterrestrial space. The apparatus includes a shell and a biological cabin configured in an upper space of the shell. A light management system for importing light of biological growth from external world is configured in the upper space, a thermal management system for at least balancing a temperature of the upper space and a water supplying system and configured for providing water for creatures growth are both configured on the shell. The biological cabin and the like are set at the appropriate part of the shell, an environment which is relatively suitable for biological growth or cultivation can be created and simulated on an extraterrestrial star, a condition is provided for ecological cultivation of the extraterrestrial space, an ecosystem of the extraterrestrial space can be formed, smooth extraterrestrial space biological experiment process is guaranteed.

A satellite attitude data fusion system and method is disclosed, applicable to the earth satellite environment to estimate attitude data of the satellite. When the satellite attitude data fusion system of the present invention is used to perform the satellite attitude data fusion method, the first step is to perform a body rates quaternion attitude data processing operation. Then, the next step is to perform an attitude/rates data fusion processing operation, wherein an attitude data fusion algorithm module receives the first IAE result data from the first EKF, and the second JAE result data from the second EKF, and performs an attitude/rates data fusion algorithm in a subsystem level to evaluate an attitude estimation JAE performance.

A method for the deployment of reconnaissance devices including buoy cameras and robotic devices in a target mission area of a remote location in space utilizing a maneuverable descent de-booster capsule and a buoyant vessel for the deployment is disclosed, including identifying the target area from an orbiting spacecraft; deploying the de-booster into orbit over the target area; initiating gradual descent of the de-booster in the atmosphere of the remote location in space; ejecting the buoyant vessel and its payload from the de-booster; filling the buoyant portion of the buoyant vessel with a lifting gas to cause the buoyant portion to become a large balloon; activating reconnaissance devices on the bay portion of the buoyant vessel, including video and other devices for monitoring and surveiling the target mission area; maneuvering the buoyant vessel to refine mission site selection; opening cargo bay doors at a predetermined altitude to deliver payloads including buoy cameras to the target mission area; causing the at least one buoyant vessel to rise in the atmosphere over the target mission area after payload delivery; and activating communication relay functions in the buoyant vessel while maintaining ongoing reconnaissance activities.

The present invention relates to a passive microwave sounder for a satellite, having a fixed reflection plate. The passive microwave sounder for a satellite, having a fixed reflection plate includes: a motor 100 including a first rotary shaft 110 formed to extend in a progressing direction of a satellite; a first rotating reflection plate 200 forming a predetermined angle with respect to the ground surface of a nadir direction and having a first one-side surface 210 and a first other-side surface 220, the center of the first one-side surface 210 being coupled to and rotating with the first rotary shaft 110, such that the first one-side surface 210 and the first other-side surface 220 alternately face the ground surface, and the second other-side surface 220 reflecting incident electromagnetic waves; an auxiliary reflection part 300 reflecting the electromagnetic waves incident from the first other-side surface 220 to a predetermined position; a reception part 400 receiving the electromagnetic waves reflected from the auxiliary reflection part 300; and a fixed reflection plate 500 fixed above the first rotating reflection plate 200 at a predetermined angle with the ground surface and reflecting the electromagnetic waves to the first one-side surface 210 or the first other-side surface 220.

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 sampling method includes: obtaining topographical information about a predetermined wide area by using a first sensor on a work machine; selecting a candidate area within the wide area, the candidate area is less than an area of the wide area, and setting a movement route based on the information about the wide area, the movement route allows a distal end portion of an arm provided on the work machine to reach a preparation position without coming into contact with an obstacle, the preparation position being located above the candidate area; moving the distal end portion of the arm along the movement route to the preparation position, and obtaining topographical information about the candidate area by using a second sensor on the distal end portion of the arm; and specifying a sampling point based on the information about the candidate area and performing sampling at the specified sampling point.

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 lunar orbiting satellite system executes orbit planning of assigning a function (positioning, communication, and flashing) to an artificial satellite (AS) depending on a relative position of the AS to the moon at a time when the moon and the AS are observed from an input point on the earth, and correcting the relative position, which changes in accordance with the moon revolution period. The system includes: a satellite orbit planner which assigns a function to each ASs forming an AS group flying around the moon depending on a relative position of each ASs to the moon at a time when the moon and ASs are observed from an input point on the earth, and set a target orbit according to the function; and a satellite controller which causes the each ASs to execute control based on the function to implement switching of the function.

A craft having a source of deuterium-containing micro-fusion fuel particles is operable above a planetary, lunar or asteroid surface in the presence of ambient cosmic rays. The fuel particles are dispersible from a set of ports, where at least some of the ports are in an underside of the craft body and others are in lateral sides of the craft body. Dispersed fuel particles interact with ambient cosmic rays and muons to generate energetic reaction products, at least some which are then received by the underside of the craft to generate lift and also selected lateral sides of the craft to generate propulsive thrust in a desired lateral direction. The craft can carry tethers and winches to carry a payload above the surface from location to another. In another embodiment, a balloon-based design, such as a dirigible, provides primary buoyant lift, while the micro-fusion particles provide at least lateral thrust, and supplemental lift where needed.