49 results about "Orbital operations" patented technology

The invention discloses a method and device for cleaning space debris. According to the method, electromagnetic force is applied to the space debris running on an original orbit; the speed and/or direction of the space debris are/is changed under the action of the electromagnetic force; the space debris of which the speed is changed is changed to run on a new orbit under the action of gravity; at least the height of the perigee of the space debris on the new orbit is smaller than the height of the perigee of the space debris on the original orbit; the space debris running on the new orbit finally falls into the atmosphere of the earth under the action of atmosphere resistance. The device comprises a satellite bearing platform which is provided with an electric field device cleaning the space debris or a magnetic field device cleaning the space debris or a combination of the electric field device and the magnetic field device. The method and device for cleaning the space debris do not have high requirements for the accuracy of position detection of the space debris, micro space debris can be effectively cleaned, solar energy can be fully utilized for power generation, and self-carried energy is saved. The device for cleaning the space debris has the advantages of being simple in structure, low in manufacturing cost, and better in pulse action effect.

A floor treatment device having a handle assembly having a pair of handles at one end and a rotational engagement to a frame at the other. A head assembly, having a motor and flywheel and offset drive for a pad, is rotationally engaged to the frame to allow all the components to tilt over uneven surfaces. The handles are positioned vertically to provide an ergonomic grip for users. Enhanced orbital operation of the cleaning or other pad is yielded by system of paired weights on the flywheel. A spray system is also engageable to the device.

A lifting body aircraft suitable for atmospheric flight and/or as a reentry vehicle. The craft has a substantially flat upper surface, a lower surface with a doubly convex first section and a flat sloping second section. The doubly convex first section allows the craft to have its center of gravity forward of its longitudinal center line. The flat sloping second half of the lower surface and the substantially flat upper surface form the aft end of an airfoil. A pair of vertical stabilizers enhance stability and include rudders which, along with a pair of elevons, provide steerage. The craft may glide or it may have an engine or rockets for thrust. The result is an extremely stable lifting body design that is well suited for launch or conventional take off, insertion, orbital operations, reentry, atmospheric flight, and conventional landings.

A lifting body aircraft suitable for atmospheric flight and/or as a reentry vehicle. The craft has a substantially flat upper surface, a lower surface with a doubly convex first section and a flat sloping second section. Chines may be provided between the upper and lower surfaces. The doubly convex first section allows the craft to have its center of gravity forward of its longitudinal center line. The flat sloping second half of the lower surface and the substantially flat upper surface form the aft end of an airfoil. A pair of vertical stabilizers enhance stability and include rudders which, along with a pair of elevons, provide steerage. The craft may glide or it may have an engine or rockets for thrust. The result is an extremely stable lifting body design that is well suited for launch or conventional take off, insertion, orbital operations, reentry, atmospheric flight, and conventional landings.

The invention provides a cell selection method and device, which are used for reducing resource waste. The cell selection method comprises the following steps that terminal equipment determines candidate measurement frequency points according to geographic position information, star orbit graph information and a corresponding relationship between the star orbit graph information and a satellite use frequency band, the geographic position information is used for indicating a current geographic position coordinate of the terminal equipment, and the star orbit graph information comprises orbit operation data information of a satellite in a service area where the terminal equipment is located and/or identification information of the satellite; the terminal equipment measures the candidate measurement frequency points to obtain a measurement result; and if the measurement result meets a first preset condition, the terminal equipment selects or reselects a target cell capable of meeting thefirst preset condition.

The invention mainly discloses a retractable gymnasium roof with an ultra large curved space and a control method thereof. A large multi-point hydraulically-actuated hoister is used for pulling the movable roof to realize the retraction and the extension of the roof, the movable roof is supported and driven to move by trolleys mounted on a main arch track of the gymnasium, the hoister pulls the movable roof under the control of a central control system to enable the roof to move along the main arch track so as to complete the inward retraction or the outward extension of the roof, and the position and the height of each support trolley is adjusted according to the relative design height and the lateral deviation extent of the gymnasium arch in the moving process of each trolley so as to ensure the smooth slippage of the roof and the integral structural safety of the gymnasium. By establishing a secure foundation based on a mechanical model and realizing technical breakthrough in multiple aspects of construction, structure, machinery and control, the invention ensures the safe, smooth and long-time movement of the movable gymnasium roof.

The invention discloses a spectrum sharing time parameter design method for an NGSO constellation system. The method comprises the following steps: 1) constructing an interference scene of the NGSO constellation system, comprising an interfering NGSO constellation system and an interfered NGSO constellation system, wherein the interfering NGSO constellation system comprises a plurality of interfering satellites, and the interfered NGSO constellation system comprises a plurality of interfered satellites; 2) according to the interference scene, calculating the time step length of a downlink, the sampling times of an interfered satellite receiving antenna beam main lobe area in the downlink and the geocentric angle of the interfered satellite receiving antenna beam main lobe area in the downlink when passing through an interference earth station; 3) according to the interference scene, calculating the time step length of a uplink, the sampling times of the interfered satellite receiving antenna beam main lobe area in the uplink and the geocentric angle of the interfered satellite receiving antenna beam main lobe area of the uplink when passing through the interference earth station; and 4) calculating the total time length and the total step number of NGSO constellation system orbit operation simulation during interference analysis.

The invention provides an entire loading and transporting technology and equipment for a portal crane. The portal crane is hoisted according to the requirements of final assembly technology and powered on for test to reach the technical requirements. The portal crane is driven to a ship through a running track, a land part temporary track and a ship part temporary track, and transported to the designated site by the ship; and the portal crane runs to the land through the ship part temporary track, the land part temporary track and the running track to finish the loading and transportation. According to the invention, the portal crane is hoisted for test on the site of the manufacturer, and any problem if discovered can be solved in time; the whole hoisting test stage does not occupy the area of the owner, the hoisting equipment of the manufacturer is sufficiently used, and the hoisting cost is saved; the equipment can be put into use quickly after arriving at the area of the owner; and the field installation area and time can be greatly saved.

The invention discloses an on-orbit spacecraft orbital transfer detection method based on TLE elements. The method aims at the characteristics of on-orbit spacecraft space orbit operation rules and orbit control. According to the method for calculating the orbital transfer time and the orbital semi-major axis variation of the spacecraft based on the TLE element number, a dynamic orbital transfer threshold value is set, and the problems of orbital change time, orbital variation and multiple orbital transfer recognition in the on-orbit operation process of the spacecraft are effectively solved.

The invention proposes a weighted space-time graph-based aerospace information network routing method. According to the weighted space-time graph-based aerospace information network routing method, onthe basis that the orbital operation of a node has periodicity and regularity, the motion cycle of a spacecraft is divided into a plurality of static topologies according to the ephemeris; and a weighted space-time graph model is constructed with link bandwidth, delay, storage and other resources used as weights; a route is intelligently selected from a policy library on the basis of topology models, and therefore, routing can be more efficient, and efficient and reliable data transmission in an aerospace information network can be realized.

The invention relates to a method for measuring the angular velocity ({right arrow over (ω)}) of a body (2) orbiting, or in motion anyway, in space depending on the detection of the trajectory of a plurality (n) of feature points (Pi) to be observed of said body (2), said trajectory being detected on the basis of data acquired by at least one remote sensor (1); the invention relate also to the related system for measuring the angular velocity ({right arrow over (ω)}) of a body (2) orbiting, or in motion anyway, in space using such method and that comprises at least one remote sensor (1), it being possible for said at least one sensor (1) to be installed on board a spacecraft (3) or to be housed in a earth station (5).

The present invention has a preferred application for measuring the angular velocity in fields such as for recovering and de-orbiting space debris.

The invention discloses a feeding operation vehicle and a poultry feeding system. The feeding operation vehicle comprises a feeding moving vehicle body and a hanging frame arranged in the interior ofan aisle, wherein the feeding moving vehicle body comprises pulley fixed beams, pulleys arranged on the pulley fixed beams, a transverse frame fixedly arranged on the pulley fixed beams, and blankinghoppers fixedly arranged on the transverse frame; each pulley fixed beam is slidably arranged on a guide rail of a cage through pulleys arranged on the pulley fixed beam; the hanging frame comprises vertical beams and a bearing plate; the vertical beams are erected in the interior of the aisle; the top end of each vertical beam is connected with the transverse frame; the bottom end of each vertical beam is alternated with the ground; and the bearing plate is fixedly arranged on the vertical beams and is close to the bottom ends of the vertical beams. The feeding operation vehicle provided by the invention can realize feeding of poultry, can drive a feeder to work in the aisle, does not need manpower for driving, operates according to a definitive orbit, and is convenient to use.

There is described a multistage friction/traction speed adapter. A first drive can include a plurality of free rollers orbiting around a sun element within a frame, transmitting their orbiting movement to guided rollers which do not contact the sun element or the frame. The guided rollers are driven in the orbiting movement and transmit the rotary movement to a carrier via corresponding pins which engage with the carrier. A second drive can include rollers having radial position variation which is prevented from being transmitted to the carrier by providing accommodation at the pin level, either by providing a bushing around the pins with a bore that is eccentric relative to its outer surface, either by engaging the pins into the carriers in portions thereof which are made more flexible. A friction/traction gear at an angle is also disclosed.

The invention provides an LEO-to-HEO multi-orbit satellite measurement and control system and method. The LEO-to-HEO multi-orbit satellite measurement and control system comprises an orbit measurementmodule, a first telemetry module, a second telemetry module and a remote control module. The orbit measurement module is configured in a mode of combining USB (Universal Serial Bus) orbit measurementwith GNSS (Global Navigation Satellite System) orbit measurement. The remote control module is configured to realize global beam coverage by combining two pairs of measurement and control transceiverantennas and receive remote control signals in all track operation phases. The first telemetry module is configured to realize global beam coverage by combining the two pairs of measurement and control transceiver antennas and transmit low-power telemetry signals in the LEO orbital phase and the early orbit transfer phase. The second telemetry module is configured to achieve hemispherical beam coverage in a single-antenna transmitting mode, achieve time-sharing global beam coverage through switching of two measurement and control transmitting antennas and transmit high-power telemetry signalsin the later orbit transfer phase and the HEO orbital phase.

The invention discloses a real-time dynamic monitoring method, device and system for rail shaking, and relates to the technical field of rail detection. The method comprises the following steps that ahand-held device is fixedly arranged on a locomotive, and the hand-held device and the locomotive are relatively static; when the locomotive runs along rails, the hand-held device is used for detecting the balance of the locomotive during running in real time; and if the hand-held device detects that the balance of the locomotive during running does not meet the balance requirement, the rails aredetermined to be not stable, and an alarm is given. According to the device and the system which are realized through the method, carrying is convenient, arranging is simple, operating is convenientand rapid, and the positions, not meeting the shaking regulations, of the rails can be rapidly found.

A satellite system can include one or more satellites that orbit the Earth. The one or more satellites may have satellite buses that support antenna arrays. The antenna arrays may include space fed arrays. Each space fed array may have an antenna feed array and an inner array that is coupled to a direct radiating array. The direct radiating array may operate in the same satellite band as the spacefed array, or upconversion and downconversion circuitry may be used to communicatively couple a direct radiating array that operates in a different satellite band to the space fed array. The satellites may have peripheral walls with corner fittings that can be selected to provide the satellite bus with particular leg strengths. This can reduce overall mass of the satellites in a payload fairing while accommodating different types of antenna arrays.

The invention discloses a satellite network routing method, device and equipment and a readable storage medium, and relates to the technical field of communication. According to the method, address information corresponding to a domain name address of a service party is obtained from a domain name system server, and a first message carrying an address of a ground station connected with the service party and orbit number information and running direction information of a satellite accessed to the ground station is sent to the service party; therefore, when the first message is forwarded in the inter-satellite route, the first message can access the running direction information of the satellite according to the ground station connected with the service party, the inter-satellite link information transmission distance is reduced, the communication overhead is saved, and the problem of packet loss caused by different orbit running directions is avoided; according to the method, the block information embedded in the address of the ground station connected with the service party and the orbit number information of the satellite accessed to the ground station connected with the service party are combined, so that the high efficiency of determining the landing satellite is realized, the detour problem in the forwarding process is avoided, and the inter-satellite routing capability in a space-ground integrated network communication scene is improved.

The invention discloses a data acquisition and transmission circuit, which is used for detecting whether a track damping spring is broken. A track damping spring break detecting circuit comprises a sensing circuit, a data processing circuit and a transmission circuit. The sensing circuit senses the formation and change of a spring, so as to obtain real-time data about the spring, determines a broken spring according to the difference between data of a normal spring and the broken spring, can identify the existence of the broken spring in a convenient and real-time manner, facilitates the rapidorbit risk elimination, and ensures the safety of orbital operation.