34results about How to "Good engineering feasibility" patented technology

The invention relates to a connector device for replenishing gas and liquid on the orbit. The connector device is used for replenishing gas and liquid for a target satellite by a service satellite on the orbit. The connector device comprises an active mechanism and a passive mechanism. The service satellite and the target satellite are positioned and conveniently separated through guide devices on respective butt-joint surfaces of the active mechanism and the passive mechanism, the service satellite and the target satellite are caused to move relative to each other through a drive mechanism having the axial spacing function, and the service satellite and the target satellite are locked through a positioning locking structure, so that the service satellite and the target satellite are guaranteed to be at fixed positions relative to each other in the on-orbit gas-liquid replenishing process. Through the measures, the efficiency of the on-orbit gas-liquid replenishing process is improved, and the safety of the on-orbit gas-liquid replenishing process is guaranteed.

The invention relates to a low-orbit satellite anchoring-based autonomous orbit determination method of Beidou navigation constellation. The low-orbit satellite anchoring-based autonomous orbit determination method comprises the steps of performing inter-satellite bidirectional pseudo-range observation by a Beidou inter-satellite link, sending Beidou inter-satellite bidirectional observation quantity information and prior position and speed information of a local satellite under a geocentric inertial coordinate system to an adjacent Beidou navigation satellite by the inter-satellite link; receiving Beidou downlink observation quantity information sent from a low-orbit satellite and autonomous orbit determination data of the low-orbit satellite; performing error correction on pseudo-range between Beidou double satellites and pseudo-range between the Beidou satellite and the low-orbit satellite, and eliminating a transceiving equipment error and a link error; and unifying the corrected pseudo-range between the Beidou satellite and the low-orbit satellite and the pseudo-range between the Beidou satellite and the low-orbit satellite to the same moment, decoupling inter-satellite distance and relative clock error in the bidirectional observation information between Beidou satellites, taking the low-orbit satellite pseudo-range, the distance between the Beidou satellites and the relative clock error as observation quantity, and calculating position, speed and clock error of the Beidou satellite by an extended Kalman filtering method.

The invention, which relates to the space optical remote sensing field, provides an alignment system and adjusting method for a large-calibre space optical camera lens. With the system and method, problems of low optical transfer function and imaging quality of the optical system of the existing large-calibre space optical camera lens can be solved. The alignment system comprises a camera lens, a lens alignment frame, three lens connecting bases, a secondary lens alignment frame, a secondary lens adjusting frame, a plane lens, a plane lens two-dimensional adjusting mechanism, an interferometer, an interferometer adjusting frame, and a three-lens adjusting frame. The camera lens consists of a camera frame, a secondary lens assembly, a secondary lens pad block, a main lens assembly, a camera substrate, a rear bracket, a first folding lens assembly, a three-lens assembly, a three-lens pad block, a second folding lens assembly, and three connecting supports. With the alignment structure at the vertical direction of the optical axis of the camera lens, the precision changes of relative positions of all reflection lenses are small and the imaging quality of the optical system is kept to be the same when the large-calibre space optical camera lens enters a microgravity environment of the space after alignment on the ground.

A ground gravity unloading support method for a large spatial reflector belongs to the technical field of space optics. In order to solve the problem that the gravity environmental variation of the large spatial reflector results in the decline of the surface shape precision of the reflector, a finite element analysis software is adopted to carry out finite element modeling on a spatial reflector assembly and analyze the variation of the reflector surface shape precision caused by gravity when the spatial reflector assembly is horizontally placed; the number and distribution of active support points at the back of the spatial reflector are primarily determined according to the size of the spatial reflector, the variation analysis result of the reflector surface shape precision and the layout condition of a support structure; after support force is applied on the active support points of the spatial reflector, the variation condition of the reflector surface shape precision caused by gravity when the spatial reflector assembly is horizontally placed is analyzed, the reflector surface shape precision result of the spatial reflector assembly is enabled to meet optical design requirements through analyzing and adjusting the size of the support force applied on the active support points and the number and distribution of the active support points, and the gravity unloading of the reflector is realized.

The invention provides a coal-fired power generation system based on a bypass flue at the tail part of a boiler as well as warm air obtained through steam extraction. The coal-fired power generation system adopts fuel to heat feed water so as to generate power, and is characterized by comprising a boiler body subsystem, an air supply subsystem, a tail flue subsystem, a turboset subsystem and a generator, wherein the boiler body subsystem comprises the boiler and a boiler flue, the boiler is provided with a hearth, and the boiler flue is connected with an outlet of the hearth and divided into a main flue and the bypass flue; the air supply subsystem comprises an air feeder, a front air preheater and a flue air preheater, the air feeder is used for supplying environment cold air, the front air preheater is connected with the air feeder and used for preheating the environment cold air to obtain warm air, and the flue air preheater is arranged in the main flue and used for heating the warm air; the tail flue subsystem comprises a high-pressure feed water heat exchanger and a low-pressure condensed water heat exchanger, the high-pressure feed water heat exchanger is arranged in the bypass flue and close to an inlet of the bypass flue, and the low-pressure condensed water heat exchanger is arranged in the bypass flue and close to an outlet of the bypass flue.

The invention provides a method for gluing two seams of a spatial reflector, relates to the technical field of spatial optical remote sensing, and aims at solving the problems of small positioning precision, non-uniform glue layer thickness, reduction of surface figure accuracy of the spatial reflector caused by residual stress after solidifying of a glue layer, and unstable stress distribution in the existing method of gluing the spatial reflector and an embedded part through three jackscrew. The method is that glue coats the lower side of the inner hole wall of the spatial reflector; the upper side of the inner hole wall of the spatial reflector is in match with a large seam of a double-seam adhering tool; meanwhile, the glue coats the outer wall of the embedded part; the inner wall of the embedded part is in match with a small seam of the double-seam adhering tool to finish the adhering of the spatial reflector and the embedded part; the large seam and the small seam of the double-seam adhering tool are processed based on the same reference, so that the coaxiality of the two seams can be ensured, and the uniformity of the glue layer thickness can be greatly improved; the glue layer is uniform in thickness; the residual stress is small after the solidifying of the glue layer; therefore, the surface figure accuracy of the spatial reflector can be fully ensured. The method is simple and reliable to operate.

Provided is a coaxial three-mirror zooming optical system based on photoisomerization materials. The coaxial three-mirror zooming optical system based on the photoisomerization materials comprises a primary mirror, a secondary mirror, a tertiary mirror and a caliber-variable diaphragm, wherein the caliber-variable diaphragm is located at a system exit pupil position in a short focal length mode, a system aperture diaphragm is arranged on the primary mirror, a classic R-C optical system is formed by the primary mirror and the secondary mirror, radiation light beams of a target scenery are converged by the primary mirror and the secondary mirror to form a middle real image, and the middle real image is imaged on the focal plane of the optical system through the tertiary mirror. According to the coaxial three-mirror zooming optical system based on the photoisomerization materials, the primary mirror, the secondary mirror and the tertiary mirror are made of the photoisomerization materials, changes of coefficients of aspheric surfaces of the mirrors are controlled through the material characteristics of the coaxial three-mirror zooming optical system in the zooming process of the coaxial three-mirror zooming optical system, and finally the coaxial three-mirror zooming optical system can have both the advantages of being large in focal length and high in resolution, and the advantages of being short in focal length and wide in field of view only through the changes of the coefficients of the aspheric surfaces of the mirrors and slight adjustment of the mirror spacing under the condition that the radii of curvature of all the mirrors of the optical system are unchanged.

The invention discloses a high thrust liquid rocket fault reconfiguration control method, which does a research on a fault reconfiguration strategy and a reconfiguration control technology of the high thrust liquid rocket during a booster ascending flight. Possible faults of the rocket are classified according to a logic sequence from a set to a unit to a fault type, a specialistic systematic knowledge base is built, and basic condition equations which need to be met for realizing fault reconfiguration are obtained through deduction; and a swing angle deviator when an engine works normally is acquired, and in view of each different fault condition, the swing angle deviator each time when a fault happens to the engine is detected; and finally, the basic condition equations which need to be met for realizing fault reconfiguration are used for calculating a specific form for a fault reconfiguration control law in each different fault condition. The rocket anti-fault ability is improved, and research on the high thrust liquid rocket is promoted.

The invention provides a phased-array antenna unit with flat-top directional diagram characteristics. The phased-array antenna unit comprises a metallic waveguide area and a free space area, wherein the metallic waveguide area is composed of a cylindrical waveguide and a conical waveguide connected with the cylindrical waveguide, a micro-strip plate laminating cylinder conformal array used for achieving flat-top wave beam unit directional diagram shape design through slot coupling is arranged on a port of the conical waveguide, evenly distributed eccentric round metal sheets are etched on each layer of micro-strip plates and arranged into a matrix, an light insulator is arranged on a cascaded superposition slot area of every two adjacent micro-strip plates, and then a free space area multi-layer conformal array unit is formed. The phased-array antenna unit has the advantages that the structure is simple, rotary symmetry is adopted for the structure, directional diagram equalization performance is good in the electric aspect, the unit can be applied to both linear polarization and circular polarization, external grating lobes generated during array scanning can be effectively restrained, margin gain of scanning can be improved, and the design method can be applied to a limited scanning two-dimensional phased-array antenna unit with a wide scanning range.

The invention relates to the technical field of laser display, discloses a segmented laser light source system, and solves problems of speckle effect and non-uniformity of laser projection display inthe prior art. The system comprises a semiconductor laser light source, a telescoping beam compression system, and a laser speckle elimination-homogenizer, the semiconductor laser light source comprises a diode array module, array collimating lenses and a beam splitter, the diode array module outputs laser light fields in parallel through respective corresponding array collimating lenses, the laser light fields are coupled to a common-aperture laser light field through the beam splitter and enter the telescoping beam compression system, the telescoping beam compression system performs aperturecompression on the laser light field, the compressed laser light field is output to the laser speckle elimination-homogenizer, the laser speckle elimination-homogenizer performs homogenization and speckle elimination processing on the compressed light field, and a uniform square light field is generated at a light stick outlet thereof. The system is applicable to projection systems including projectors.

The invention discloses a design method for a multi-channel medium frequency transformer, and relates to the field of transformers. The multi-channel medium frequency transformer comprises a single magnetic core and m pairs of windings. All the windings are wound around the same magnetic core. The design method for the multi-channel medium frequency transformer comprises the following steps that 1, according to materials of the magnetic core, the magnetic flux density B of the magnetic core is determined; 2, the sectional area of the magnetic core corresponding to the ith winding is shown in the description; 3, the total sectional area of the magnetic core is shown in the description; 4, voltage Ui of the winding is made to be equal to U, the number N of turns of the coil of the winding are made to be equal to N, and a total sectional area expression of the magnetic core is obtained; 5, the area Q of a window is shown in the description; 6, an appropriate Q is selected, the Q is made to be equal to K1Asum, and the total sectional area Asum of the magnetic core can be worked out; 7, according to the step 4, the number N of turns of the coil of the winding is worked out; 8, the number N of the turns of the coil adopts an integral value, and the step 4 is repeatedly executed. The multi-channel medium frequency transformer is of an integrated structure, the sectional area of the magnetic core is precisely calculated through the formulas, and therefore the size of the transformer is optimized.

The invention relates to a single-pulse guidance method for autonomous fast rendezvous and docking and a readable medium. The method comprises the following steps of acquiring orbit parameters of a tracking spacecraft and orbit parameters of a target spacecraft; computing parameter deviations between the orbit parameters of the spacecraft and the orbit parameters of the target spacecraft accordingto the orbit parameters of the tracking spacecraft and the orbit parameters of the target spacecraft; computing a characteristic point latitude angle for orbital transfer of the tracking spacecraft according to the parameter deviations; acquiring a reference value of the characteristic point latitude angle for orbital transfer, comparing a computed value of the latitude angle with the reference value, enabling the characteristic point latitude angle for orbital transfer to use the computed value when the usable range is met, and otherwise using the reference value; and computing the trace orbital transfer quantity and the radial orbital transfer quantity of the single orbital transfer of the spacecraft according to the orbit parameters of the tracking spacecraft, the orbit parameters of the target spacecraft, the deviation parameters and the characteristic point latitude angle, and applying the orbital transfer quantity to the autonomous fast rendezvous and docking.

The invention relates to a building integrated energy system control method based on comfort, which is used for realizing multi-energy complementation, energy conservation and emission reduction on the premise of ensuring the comfort, and comprises the following steps: 1) establishing a power grid interactive energy management system by considering two dimensions of energy efficiency and power grid interactivity; 2) constructing a target function of a power grid interactive energy management system; 3) taking the temperature comfort level and the user power utilization comfort level as constraint conditions; and 4) solving the objective function of the power grid interactive energy management system to obtain an optimal control scheme considering the temperature comfort level and the userpower utilization comfort level, and executing scheduling. Compared with the prior art, the method has the advantages of considering the user power utilization comfort level and the temperature comfort level, reducing the system operation cost, being good in engineering realizability and the like.

The invention discloses a composite heat source flexible clean heat supply method and system based on cross-seasonal graded heat storage, and the system consists of a soil source graded heat storage system, a solar system, an ultra-efficient heat pump, an indoor tail end and a pipeline system, and the soil source graded heat storage system is divided into an inner ring high-temperature area, a middle ring medium-temperature area and an outer ring low-temperature area; in the non-heating period, high-temperature, medium-temperature and low-temperature waste heat sources from industrial enterprises can be received for heat storage, and solar energy can store heat in a medium-temperature area. In the heating period, high-temperature area heat storage and a high-temperature waste heat source can be combined to heat the indoor high-temperature tail end; the medium-temperature area heat storage and the medium-temperature waste heat source can be combined for heating the medium-temperature tail end; the low-temperature area heat storage and the low-temperature waste heat source can be combined for heating the low-temperature tail end; the heat pump unit can absorb heat stored in a low-temperature area and a low-temperature waste heat source for heating and supply heat to the high-temperature tail end and the medium-temperature tail end. Solar energy can directly heat the medium-temperature tail end. According to the invention, cross-seasonal heat supply of clean energy based on industrial waste heat and solar energy can be realized, and energy can be saved by more than 80%-90% compared with a traditional heat supply mode.

The invention discloses a GEO SAR satellite imaging method based on a single-reflector antenna, belongs to the field of overall design of high-orbit microwave imaging satellites, and aims to perform beam design on GEO SAR of a phased array feed source single-reflector antenna without attitude adjustment and cover all incident angle ranges only through distance-direction electric scanning. In orderto achieve the purpose, the technical scheme of the invention comprises the following steps: S1, selecting an antenna aperture according to the requirements of the minimum unambiguous area and resolution of the antenna, and selecting an antenna focal length according to the antenna aperture; s2, according to an incident angle requirement, calculating a lower visual angle range to obtain a scanning range required to be reached by the antenna, wherein the corresponding relation between the SAR downward viewing angle and the incident angle is shown in the specification, theta is the incident angle, alpha is the downward viewing angle, H is the orbit height and Re earth radius; and S3, setting an antenna feed source to form a scanning range required to be reached by the antenna, and performing satellite imaging.

The invention discloses an optimal single-relay distributed opportunistic channel access method under delay constraint. The method comprises the following steps that: each information source competesfor a channel, when only one information source exists, the information source obtains a channel access opportunity, otherwise, all the information sources restart channel competition; after the information source i competes successfully, the relay receives the RTS packet sent by the information source i, calculates the channel quality from the information source i to the relay, then sends the RTSpacket to the information sink i, the information sink i replies to the relay after receiving the RTS packet, and the relay node calculates the channel quality from the relay to the information sinki; the relay node feeds back all information to a signal source i, and the signal source i calculates the maximum transmissible rate and makes a decision: selecting an access channel, and selecting anoptimal single relay capable of reaching the maximum rate to perform channel access by the signal source i; otherwise, the information source i gives up the channel opportunity, and all the information sources compete for the channel again. According to the method, the user diversity and the time diversity are fully utilized, and the system throughput and the spectrum utilization rate are effectively improved.

The invention relates to a time-varying nonlinear ground physical similarity simulation method for a space interception process. High-speed motion components of two aircrafts are mapped into constant-value or uniform-speed motion through nonlinear transformation, and only remaining low-speed relative motion parts are simulated on the ground. The available space and the capacity of an executing mechanism in ground physical simulation can be fully utilized, so that the precision requirement of ground simulation is lowered, and good engineering realizability is achieved.

The invention discloses an immersion cleaning system and an immersion cleaning method thereof for chromium-polluted building garbage. The immersion cleaning system comprises sulphuric acid storing jars, alkali liquor storing jars, medicament stirring jars, a water retaining and discharging tank, pump tanks, an immersion cleaning tank body of which the section is rectangular, and a medicine distributing pipeline, wherein an acid discharging opening is formed in one side of each sulphuric acid storing jar, a discharging opening is formed in the other side of each sulphuric acid storing jar, andthe discharging opening of each sulphuric acid storing jar is connected with a first feeding opening of each medicament stirring jar through a pipeline; a second feeding opening for adding ferrous sulfate and a water inlet opening are also formed in the top of each medicament stirring jar; the immersion cleaning bank body is arranged on one side of the water retaining and discharging tank; and themedicine distributing pipeline is arranged along the long edge of one side of the immersion cleaning tank body. Treating liquid after immersion cleaning of garbage flows back into the water retainingand discharging tank from the discharging opening of the immersion cleaning tank body, and is drained out through a waste liquid pipeline arranged at the bottom of the water retaining and dischargingtank. The treatment period is short, the technological process is complete, the immersion cleaning course is simple and convenient to operate, and the repair effect is good. The immersion cleaning tank body has a leakproof function, and in the immersion cleaning course, liquid medicaments form liquid seal on the building garbage, so that dust raising is avoided.