Method for observing the surface of a planet from space and space satellite system for the implementation thereof
The invention relates to satellite information systems. Satellites for observing a region of a latitude belt with lower latitudes are placed into orbits with an inclination that is less than the inclination of the orbits into which satellites for observing a region with higher latitudes are placed. The orbits of all of the satellites must have the same nodal line regression rate. The result is an increase in observation efficiency.
Publication number: WO2015057103A1 | Search similar patents
Method for controlling the orbit of a satellite in earth orbit, satellite and system for controlling the orbit of such a satellite
The present invention relates to a method (50) for controlling the orbit of a satellite (10) in earth orbit, the orbit of the satellite (10) being controlled by commanding, according to a plane of operation, the propulsion means (30, 31), including at least one thruster, and means for moving (20, 21) said propulsion means. According to the invention, said plane of operation includes at least two orbit-control operations, thrust powers of the propulsion means (30, 31) during said two orbit-control operations having respective thrust directions that are not parallel in an inertial frame of reference, each one of said thrust powers being determined so as to simultaneously control the inclination and the position of the orbit of the satellite as well as to form a momentum that is suitable for unloading a device for storing angular momentum of said satellite in a plane orthogonal to the direction of thrust of said thrust power.
Publication number: WO2015193499A1 | Search similar patents
Method for controlling orbital plane of artificial satellite
[Problem] To provide a method for controlling the orbital plane of an artificial satellite that is capable of achieving orbit control that is substantially equivalent to that of an artificial satellite equipped with a propulsion system having a high thrust level, with the intention of reducing the size and weight of the artificial satellite without impairing the mission of a main satellite. [Solution] This method for controlling the orbital plane of artificial satellite involves directing a plurality of small artificial satellites (11, 12), which are launched together with a main satellite, to respective target orbits, and is characterized in that the orbital altitudes of the small artificial satellites (11, 12), which are directed to a target orbit (S1) of the main satellite, are altered by using propulsion systems having a low thrust level, and the plurality of artificial satellites (11, 12) is introduced to respective target orbits (S5, S9) by utilizing transitions in the orbital planes caused by the flatness of the Earth's gravity field at said orbital altitudes.
Publication number: WO2014115753A1 | Search similar patents
Method for stationing a satellite and for testing the payload thereof in orbit
Publication number: EP2977321A1 | Search similar patents
Satellite with variable main cross-section
Publication number: EP2962942A1 | Search similar patents
Manipulation of a satellite in space
Publication number: EP3012194A1 | Search similar patents
Satellite stabilized by gravity gradient
The invention relates to a satellite which orbits the Earth or another planet and uses the gradient in the planet's gravity field for passive attitude control. The satellite is a combination of a first satellite body (12) equipped with instruments for operation of the satellite, a second satellite body (14) equipped with at least one instrument (24) for operation of the satellite and an elongate structure called a mast (16) which extends from the first satellite body (12) to the second satellite body (14) when the satellite is in an orbit about the planet. The total weight of the second satellite body (14) including the instrument(s) (24) is adjusted such that the second satellite body (14) serves as a gravitational balancing mass which is necessary for aligning the mast (16) along the direction of the gradient in the planet's gravity field and orienting a specific side of the first satellite body (12) toward the planet. The mast (16) is extensible and contractable to adjust the mast length according to the orbit altitude. Solar cell panels (20) can be mounted on outer surfaces of both the first and second satellite bodies.
Publication number: EP0533489A1 | Search similar patents
Communication system, communication receiving device and communication terminal in the system
A communication line not affected by artificial structures and plants is established between mobile objects and stationary stations surrounded with skyscrapers, and economical artificial satellite service capable of efficiently performing satellite broadcast, mobile satellite communication, satellite-to-satellite communication and earth surveillance is provided using the communication line and by constructing the system with a small number of satellites.Six orbital elements 7-12 of a plurality of artificial satellites at reference time 5 are determined, and a plurality of elliptical orbits corresponding to the determined six orbital elements are combined, and then each of the satellites is appropriately arranged on each of the orbits to form a group of artificial satellites. Satellite communication or satellite broadcast is performed using the group of artificial satellites.
Publication number: US6695259B1 | Search similar patents
Planetary impact defense system
A system for defending a planet having a satellite against impact from an incoming body includes an explosive system and a propulsion system. The explosive system is adapted for deployment on the satellite and detonation thereon with sufficient explosive force to produce at least one ejectum to which is imparted a velocity increment sufficient for the ejectum to exceed the satellite's escape velocity and enter orbit about the planet. The propulsion system is adapted to be secured to at least one ejectum and impart a velocity increment to the ejectum sufficient to leave orbit about the planet and enter an orbit intercepting the incoming body.The system is used in a planetary defense method in which the explosive system is deployed at a deployment site on the satellite and detonated to produce at least one ejectum having a velocity that exceeds the escape velocity of the satellite. The ejectum enters into orbit around the planet, at which time the propulsion system is secured to the ejectum to produce a projectile. The propulsion system is then activated to increase the velocity of the projectile, causing the projectile to enter into an intercept orbit targeting the incoming body and subsequently intercept and impact the incoming body. The impact prevents the incoming body from impacting the planet.
Publication number: US2009321578A1 | Search similar patents
The invention relates to a planetary transmission, especially for motor vehicles, which comprises a sun wheel (2) that is rotationally connected to the input shaft (1), several planet wheels (3) that are mounted in a satellite carrier (5), and a ring gear which surrounds the planet wheels (3) and which is connected to a ring gear carrier, whereby each planet wheel (3) is arranged on a planet shaft (4) that is fastened to the satellite carrier (5). Each planet shaft is provided with an axial projection, whereby this projection engages inside a boring of a coupling body (7) that is adapted to said projection.
Publication number: WO0135004A1 | Search similar patents