45 results about "Space use" patented technology

The invention is concerned with the computerized controlling double dimension positioning and double order tracking digitization operation system. It mainly consists of first deck (-), second deck (-), full-visual lens groupware (-), and the center control computerized unit, which includes the centerized computer, double dimension positioning and double order tracking module. The invention conducts the digitization scaling to the operation space using positioning and marking points up and down the decks, this way, it ensures the acrruate location of the operation position according to the two marked X-ray images are collectable by model C arm; the double order tracking theory, as well, tracks and identifies the video image to ensure the space location with marked project.

The invention discloses a three-hole parallel magnetic levitation vacuum tunnel structure. The structure comprises running tunnels on the two sides and a service tunnel on the middle. The running tunnels and the service tunnel are connected through a connection channel, the interiors of the running tunnels are vacuum environments, the bottoms of the running tunnels are in under-rail filling, a magnetic levitation rail beam is placed on the filling face, a magnetic levitation train runs on the magnetic levitation rail beam, the interior of the service tunnel is the normal pressure environment,the bottom of the service tunnel is in filling under equipment, equipment needed by magnetic levitation running is placed on the filling face, other spaces serve as evacuation channels, one end of theconnection channel communicates with the running tunnels, the other end of the connection channel communicates with the service tunnel, and a vacuum isolation wall and a vacuum isolation door are arranged on the connecting position of the communication channel and the running tunnels. The low-vacuum environment can be ensured, the ground space use can be reduced, adaptation to the terrain is high, the tunnel structure with good passenger evacuation, personal inspection and equipment arranging capacity is achieved, and meanwhile, practicability, safety and economy are all considered.

The invention discloses an Android system storage space structure construction method and device and a construction structure thereof, and the method comprises the steps: building a first storage directory in a data partition, and the first storage directory being used for storing a preset application; then, the preset application in the first storage directory being in soft link with the second storage directory under the system partition, so that the system can identify the preset application stored in the first storage directory as the system application; setting the attribute and authorityof the first storage directory to ensure the storage security of the first storage directory; and modifying a mirror image packaging process, an upgrading mode and a deleting mode when factory settings are restored, and ensuring that the preset application in the first storage directory normally runs as the preset application originally stored in the system partition. When the preset applicationstored in the first storage directory is upgraded, the storage space of the data partition is occupied, storage of other data in the data partition is not affected, it is guaranteed that the storage space used for storing the preset application is large enough, and it is guaranteed that the storage space is not wasted.

A goods delivery device of a vending machine comprises a front door and a goods delivery bin located on the inner side of the front door. The front door is provided with a goods delivery opening. The goods delivery bin is provided with a goods delivery space used for containing goods. One side of the goods delivery bin is connected to the front door in a pivoted mode, and the goods delivery bin is contained in the goods delivery opening and used for rotating outwards from the goods delivery opening to one opening position so that the goods in the goods delivery space can be exposed.

The invention provides a ground data transmission antenna layout method adapting to inter-satellite transmission. The method comprises the following steps: firstly, determining the requirements of a data transmission antenna on an on-orbit operation satellite for ground and inter-satellite data transmission, secondly, determining the installation position and the axis direction of the data transmission antenna on the on-orbit operation satellite, and finally, determining the connection mode of the data transmission antenna and the on-orbit operation satellite to ensure that the data transmission antenna is not shielded. According to the method provided by the invention, the problems that in the process of multiple satellites fly along and fly around in constellation networking, beam shielding of an on-orbit semi-airspace inter-satellite data transmission antenna of a satellite, interference between the data transmission antenna and a ground load and a solar array, and the narrow configuration layout of a space in a fairing during launching are solved. The beneficial effects of half-airspace data transmission, multi-component interference elimination and adaptation to the internalspace of the fairing are achieved, a selection mode with high expansion capacity and high applicability is provided, and high universality is achieved.

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 real-time route planning method based on a decision tree. The method comprises the following steps: firstly, a low-altitude airspace probability model is established, a three-dimensional continuous space is expressed by using a discrete two-dimensional space, namely, a planning space is expressed as a discrete grid chart with a certain longitude difference and latitude difference, a dangerous area is divided into a no-fly area and a high-risk area, and then the cost value of each node in the model is calculated; secondly, initial route planning is carried out, a direct flight path and a fly-around path are planned for a high-risk area, only the fly-around path is planned for a no-fly area, a route decision tree is generated, and an initial route set is determined; according to the actual situation in flight, the planned route set is selected, and the planning result is updated in real time. Threatening factors such as terrain obstacles and severe weather are comprehensively considered, and the method is safer; the route decision-making tree comprising a plurality of routes is planned in consideration of uncertainty of prior information of a dangerous area, and the method is more practical; and according to the actual situation in flight, the planning result is updated in real time, which is more flexible.

The embodiment of the invention discloses an equipment control method, a space management system and internet of things related equipment. The equipment control method comprises the following steps: through at least one first device associated with a space, obtaining first related information of at least one first user in the space; when determining that a target user exists in the at least one first user based on the first related information, determining personalized information of a use demand of the target user for the type of space based on second related information of the target user; and determining at least one second device needing to be controlled and corresponding control parameters according to the personality information. According to the embodiment of the invention, intelligent control on the equipment associated with the space is realized, so that the use requirements of users in different spaces are met; and the intelligence of space equipment control is greatly improved.

The invention discloses a calibration frame comprising a support assembly, a rotating shaft, two first mounting pieces and two second mounting pieces; the support assembly comprises a first supportingframe, a second supporting frame, and a connecting piece for connecting the first supporting frame and the second supporting frame; the rotating shaft is mounted between the first supporting frame and the second supporting frame and can rotate around a central axis, and the central axis is a core axis; the two first mounting pieces are arranged at the two ends of the rotating shaft respectively and used for mounting and supporting a first target, and the first target is provided with a calibration pattern and is used for calibrating a camera assembly in a four-wheel position indicator; the two second mounting pieces are arranged at the two ends of the rotating shaft correspondingly and used for mounting and supporting a hub clamp assembly, and the hub clamp assembly comprises hub clamps and second targets mounted on the hub clamps; and after the camera assembly in the four-wheel position indicator completes calibration through the first target, the camera assembly is further used forcalibrating the hub clamps on the second mounting pieces. Therefore, the installation of the target and the installation of the hub clamp assembly are realized, the cost is reduced, the space is saved, and the use is more convenient.

The invention relates to the technical field of spaceflight, in particular to a NandFlash-based non-uniform correction coefficient storage method and a NandFlash-based non-uniform correction coefficient storage system. According to the method, the storage format of the correction coefficient in the NandFlash is planned firstly, the storage space is efficiently utilized, and the correction coefficient is stored in the NandFlash on the ground in advance; then, a bad block management table is developed in the FPGA by using an RAM (Random Access Memory) and corresponds to all storage spaces of a group of NandFlash, and a mapping relation between a logic address and a physical address of a block is established by using the bad block management table; after the camera is powered on in orbit, reading data of a NandFlash initial address to replace the bad block management table; and finally, exporting the correction coefficient in the NandFlash into a DDR3 (Double Data Rate 3) memory, and performing non-uniformity correction on the shot image.

The invention discloses a management system, a device control method, a shared space, a device and a storage medium. The management system comprises: at least one first device used for acquiring data information related to an environment in a shared space and a monitored object; at least one second device is arranged in the shared space, so that the shared space has a corresponding space use function to meet user requirements of users in the shared space; and a gateway, which is connected with the at least one first device and the at least one second device, and is used for analyzing the data information so as to formulate a control management scheme for the at least one second device, and controlling the at least one second device to work according to the control management scheme. According to the technical scheme provided by the embodiment of the invention, the high intelligence of space management is ensured, and the real-time performance of data transmission is higher because the gateway performs calculation and control on the edge side close to the space equipment.

The invention relates to the field of space flight and aviation, and discloses an offset side hanging type rocket adapter structure, which comprises a force bearing part, a side hanging part, a side hanging part and a side hanging part, and is characterized in that the force bearing part is eccentrically arranged relative to a central shaft of a rocket fairing; the bearing bottom plate is arranged at one end of the force bearing piece; the supporting connecting piece is connected with the force bearing piece and the bearing bottom plate; wherein the force bearing piece, the bearing bottom plate, the supporting connecting piece and the fairing of the rocket are encircled to form an enveloping space used for arranging an effective load of the rocket, and a center shaft of the fairing of the rocket penetrates through the enveloping space. By eccentrically arranging the force bearing piece, under the condition that the size of the fairing is not changed, the effective enveloping space in the rocket can be expanded, and the effective load with the larger single size can be conveniently carried. Through the effect of the supporting connecting piece, the strength of the adapter structure can be improved, the situation that the force load borne by the force bearing piece exceeds the allowable range is avoided, and connection between the rocket adapter structure and other sections of the tail stage of a rocket can be achieved through the bearing bottom plate.

The invention relates to a satellite pipeline pushing system based on a limited space, and belongs to the field of satellite design. Gas outlets of the helium tank The1 and the helium tank The2 are both communicated with the gas path module; the gas circuit module is respectively communicated with the oxidant storage box MON-1, the combustion agent storage box MMH-1 and the combustion agent storage box MMH-2; the oxidant storage box MON-1 is communicated with the oxygen path module; the combustion agent storage box MMH-1 and the combustion agent storage box MMH-2 are both communicated with the combustion path module; the oxygen path module is respectively communicated with an external thruster A1, an external thruster A2, an external thruster A3, an external thruster A4 and an external engine ENGINE; the fuel path module is communicated with an external thruster B1, an external thruster B2, an external thruster B3, an external thruster B4 and an external engine ENGINE; the method is suitable for GEO satellite limited space pipeline layout, the space use efficiency on the satellite is improved, and therefore the pipeline layout space is reduced, and the pipeline length is reduced.