8 results about "Orbit" patented technology

The present invention relates to satellite autonomous relative navigation. In order to solve the problem of long-distance autonomous relative navigation, the present invention provides a relative navigation method using the line-of-sight angle information on the satellite. ;Establish the system model in the modified spherical coordinate system; carry out filter calculation. Compared with the existing technology, its advantages and beneficial effects are: no active ranging equipment is required to work, only the elevation angle and azimuth angle of the target need to be detected by the passive tracking and aiming equipment, combined with the relative navigation initial value, the relative navigation can be passed The filtering algorithm realizes real-time autonomous estimation of relative position and relative velocity, and provides the required information for relative orbit control. The relative navigation with only angle information is realized, so that the active star in the orbital rendezvous mission can realize autonomous relative navigation at a long distance, and the reliability of the rendezvous mission is improved.

The invention relates to a de-orbiting sail unfolding method and a device thereof. The de-orbiting sail expanding device comprises an unfolding sail and a folding sail, wherein the unfolding sail is rotatably connected to the folding sail to form a de-orbiting sail for driving a star body to de-orbit; the folding sail comprises at least one first framework which can be used for folding a sail bodyin a folding state and supporting the sail body in an unfolding state, one or more of at least one first framework can start to rotate around the folding sail in a mode parallel to a first side in acase that a first included angle, to which the first side, opposite to the unfolding rail, of the folding rail rotates, of the folding rail and the unfolding rail is a first critical value; and moreover, the first side, opposite to the unfolding rail, of the folding rail continuously rotates, so that the first included angle can be continuously increased to define a second critical value, betweenthe folding sail and the unfolding rail, of the de-orbiting sail. Before being launched, the folding sail can be folded to reduce the size to the greatest extent; and under an unfolding state, the de-orbiting sail has an area-mass ratio which is big enough.

The invention provides a device and a method for realizing sun capture by zero momentums of micro-satellites. The device comprises an analog sun sensor, a magnetometer and a magnetic torquer, whereinthe analog sun sensor and the magnetometer are used for together determining the attitude of a satellite; and the magnetic torquer is used for providing a control moment in a rate damping process andused for enabling a normal axis of a solar array of the satellite to point to the vector direction of the sun as well as controlling an included angle between a normal line of the solar array of the satellite and the vector direction of the sun to be less than a preset threshold, thereby realizing sun capture by a zero momentum magnetic control mode of the satellite. The device and the method provided by the invention simplify the working mode of an attitude and orbit control system and improve the working reliability when the satellite enters an orbit in the early stage.

Orbital debris removal (ODR) systems under the present approach may use a ground- or surface-based FEL and mirror system with sufficient power and both spatial and temporal resolution to both locate Category II OD (1 cm to 10 cm diameter) in low Earth orbit (LEO, 160 to 2000 km altitude) and remove these objects from orbit. Locating the Category II OD is performed by having the light beam from an FEL and its beam director scan a volume of space of interest and then observing the light reflected from the OD. Removing the OD may include heating the OD to a sufficiently high temperature to evaporate the OD, changing the orbit of the OD such as to lower the perigee, or both. Megawatt-class MOPA FELs for, inter alia, removing OD, are described.

The invention discloses a laser material processing system capable of finely adjusting warping distance through a striker for laser marking. The laser material processing system structurally comprisesan emergency stop pull buckling block, a top cover block, a coil rotating block, a lock catch ear seat, a patch reinforcement plate, a laser device, a sealing end cap, and a striker light cutting cap. The laser material processing system realizes the application and cooperation of the laser device and the striker light cutting cap; a radiation side frame sliding brush block can elastically lift in small distance and shakes through linkage; a stacked ring hitting ball block intermittently moves through a barbed pinpoint block along a ratchet wheel top ring disc on the top, is matched with a corrugated oblique orbit to form a high-precision warping lifting effect for the engagement scale advancement, so that the fine adjustment of the distance when the laser penetrates the laser material isfacilitated, and the flatness of the warping radian is also guaranteed; the stability of a shell of a trapezoidal base wraps the clamping degree of an inner ring, so that the deflection of a strikerrod is driven by the fine adjustment of the ratchet wheel top ring disc; the smoothness and uninterrupted nature of the overall laser penetrating the laser material are ensured; the marking is smooth;and the fineness of the warping distance is improved.