387 results about "Thermal control" patented technology

The invention discloses a synchronous temperature control method for co-extrusion molding of a multilayer polymer film, and relates to the technical field of high polymer material processing, and the method comprises the following steps: setting a target temperature interval of each polymer layer of the multilayer polymer film, and according to the melting characteristics, heat sensitivity and interface bonding requirements of each layer of material, setting a target temperature interval of each polymer layer of the multilayer polymer film; respectively determining an extrusion temperature set value and an allowable fluctuation range; through layered independent temperature control and preheating matching, thermal behavior synchronization of multiple polymer melts is achieved, and the interface bonding stability is improved; through a die head heat insulation and buffer structure, interlayer heat interference is effectively shielded, and the integrity of a functional layer is guaranteed; through the intelligent closed-loop temperature control system, the state of each temperature control area is predicted and adjusted in real time, and self-adaptive optimization of thermal control is achieved. And the co-extrusion quality, the consistency and the production intelligent level of the multi-layer film are integrally improved.

The invention discloses a single-phase immersion battery intelligent thermal management control method and device for an energy storage power station, and relates to the technical field of battery thermal control. The intelligent thermal management control method and device for the single-phase immersed battery for the energy storage power station comprises the steps that S1, battery state data and external environment data in the operation process of the energy storage power station are collected and preprocessed, and a standardized thermal state data set is constructed; s2, performing working condition evaluation on the current working condition state by combining the battery heat flow density, and dynamically adjusting the flow direction of the cooling liquid; s3, the current heat exchange load and the phase state safety boundary are comprehensively analyzed, and the valve opening degree is driven to change; and S4, carrying out stability evaluation on the local thermal stability, and adjusting a power supply loop safety response strategy in real time. The problems that a traditional heat management system lacks the bidirectional regulation and control capacity for coping with wide-temperature-range extreme climate and cannot give consideration to the collaborative requirements of high-temperature heat dissipation and low-temperature heat supply, and consequently system structure redundancy, energy consumption increase and operation and maintenance complexity are caused are solved.

The invention relates to the technical field of PCB heat dissipation, and discloses a distributed heat dissipation structure and a distributed heat dissipation method for a PCB under a high-temperature working condition, the distributed heat dissipation structure comprises a PCB base material, an electronic component is mounted on the A surface of the PCB base material, and active thermal control units are mounted on the B surface of the PCB base material corresponding to the electronic component needing to be cooled in a distributed manner; according to the distributed heat dissipation structure for the PCB under the high-temperature working condition, the active thermal control units are installed in the area, corresponding to the heating element, of the B face of the PCB base material in a distributed mode, active refrigeration can be conducted on electronic components (such as a microprocessor and a storage) with the large heating value in a targeted mode, the highest working temperature of a system is increased, and the heat dissipation efficiency is improved. Normal operation of the system is guaranteed, meanwhile, energy waste caused by cooling of the whole plate is avoided, and the heat dissipation efficiency and the energy utilization rate are remarkably improved.

The invention relates to the technical field of thermal measurement simulation, in particular to a thermal measurement simulation system based on digital twinning, which comprises a spectrum data construction module, an energy level parameter conversion module, a temperature zone reference generation module, a disturbance data correction module and a simulation embedding module. According to the method, continuous dynamic simulation of thermal field evolution of an airspace engine under different working conditions can be realized by constructing a multi-layer data structure including spectral peak intensity distribution, an energy level proportional structure and a spectral point response and thermal disturbance bidirectional mapping relation, and difference extraction and logic feedback are performed by combining spectral response behaviors and thermal disturbance data; the thermal measurement simulation process which can be corrected, embedded and iterated is effectively constructed, the real-time performance and precision of thermal field change simulation are remarkably improved, and the high-precision pre-judgment of engine thermal characteristic evolution and the response capability of a dynamic thermal control strategy under the extreme environment condition are ensured. And a complete thermal measurement simulation support is provided for the airspace engine under a complex thermal field condition.

The invention relates to the technical field of thermal control of commercial spaceflight unfolding mechanisms, in particular to a deformable liquid metal thermal control commercial spaceflight flexible unfolding mechanism which comprises a flexible unfolding mechanism body and a flexible fluid circulation pipeline integrated inside or on the surface of the flexible unfolding mechanism body and synchronously folded and unfolded along with the flexible unfolding mechanism body. The fluid driving and heat exchange unit is arranged in the non-flexible area of the spacecraft platform or the body and is connected with the flexible fluid circulation pipeline to form a closed circulation loop; wherein the flexible fluid circulation pipeline is filled with a liquid metal working medium. The liquid metal working medium has high thermal conductivity and flow characteristics, and is matched with the vein-shaped / grid-shaped microtube array, so that the temperature of each region of the flexible unfolding mechanism can be quickly balanced, and structural stress deformation caused by temperature gradient is effectively eliminated; and the adaptive capacity of the mechanism in extreme space environments such as high and low temperature alternation and intense radiation is greatly improved.

The invention provides a millimeter wave tile-type phased-array antenna heat transfer-heat storage system, and the system comprises a heat transfer main body which is provided with a radiating surface, a heat conduction surface, and at least one heat dissipation surface; wherein an electrical function module of the phased-array antenna is arranged on the heat conduction surface to transfer heat generated by operation to the heat conduction surface, a heat conduction path and a phase change heat storage unit are formed in the heat conduction surface, the phase change heat storage unit is used for absorbing and storing part of heat, the heat conduction path is connected with the heat dissipation surface, and the phase change heat storage unit is connected with the heat dissipation surface. At least part of heat generated by the electrical function module is transmitted to the heat dissipation surface through the heat conduction path of the heat conduction surface for heat dissipation. The radiating surface is used as a signal radiating window of the phased-array antenna; and the phase change heat storage module is arranged outside the heat transfer main body, is connected with the heat dissipation surface and is used for absorbing heat dissipated by the heat dissipation surface. The invention provides an efficient heat transfer-heat storage technical scheme, and solves the thermal control problem of high-power work of the phased-array antenna on a platform within limited time.

The invention relates to the technical field of antennas, in particular to a low-orbit satellite antenna board card. Comprising a first radiation unit, a second radiation unit and a PCB. The first radiation unit and the second radiation unit are circularly polarized antennas and respectively work in different frequency bands. The first radiation unit is of a cross-shaped structure, the second radiation unit is of a hollow structure, and the first radiation unit and the second radiation unit are both made of metal materials. The first radiation unit and the second radiation unit are nested on the PCB, the upper surface of the PCB is provided with a thermal control material, the lower surface of the PCB is provided with a heat conduction material, the antenna board card provided by the invention is suitable for being used outside a cabin, the application of the PCB to the outside of the cabin becomes possible, and thus light weight and low cost of a low-orbit satellite antenna are realized.

The invention discloses an optical thermostat with comprehensive vibration reduction and low-temperature in-situ displacement functions, which adopts upper and lower opposite vibration absorbers and a large-mass base to realize first-order to second-order inertial vibration absorption, and further realizes thorough decoupling with an optical platform in a suspension type non-contact manner, and the vibration transmissibility can be reduced to be less than 10%. Resonant frequencies of two systems (a sample table system and a cold head system) are designed to achieve vibration decoupling. The technical problems that in the prior art, the high-grade vibration isolation capacity is insufficient, refrigerator noise is easily coupled to a measuring light path, the low-temperature in-situ precision displacement capacity is lacked, and the contradiction between heat isolation, convenience and cost is difficult to balance can be solved. Under the support of a conventional GM refrigerator, the comprehensive requirements of ultralow basic vibration, strong decoupling of a measurement light path, low-temperature in-situ micron-sized displacement, convenient sample replacement and efficient refrigeration / thermal control are met at the same time.

The invention relates to a control method based on low-temperature cold start of a heuristic integrated heavy oil engine, and relates to the field of heuristic integrated heavy oil engines. According to the technical scheme, the preheating plug in the cylinder is combined with the air inlet heating grid, synchronous control is achieved through the same relay, the electric energy requirements of synchronous work and dragging and preheating are met by means of sufficient battery capacity, and the device can be adapted to the ultra-low temperature of-40 DEG C or below and the plateau environment of 4700 m or above; three starting attempts are supported by single-time power-on through intelligent preheating control logic, the pre-preheating and heating-while-dragging processes are executed each time, fault information is automatically uploaded after starting fails, frequent power-off is not needed, and the starting efficiency is improved. And moreover, through an intermittent post-preheating and intake synchronous heating strategy, the combustion stability in the cylinder is effectively improved, the rotating speed fluctuation time is shortened, and mechanical damage caused by flameout and unstable idling after starting is avoided. In addition, the dragging rotating speed control based on the torque can prevent the problem of engine damage caused by accidental detonation after multiple starting failures.

The invention relates to the technical field of commercial spaceflight, in particular to a self-repairing liquid metal heat pipe for commercial spaceflight, which comprises a polyether-ether-ketone composite pipe, gallium bismuth zinc liquid gold, a micro-nano repairing film, a main hot runner, a pressure detector, a standby hot runner and an emergency plugging valve, and the main hot runner is an axial through channel in the polyether-ether-ketone composite pipe, and the standby hot runners are annularly and circumferentially arrayed along the inner wall of the main hot runner. Compared with heat conduction in the prior art, medium leakage is stopped through cooperative plugging in a damaged scene, so that the heat conduction efficiency is improved, and the service life of the heat exchanger is prolonged. And meanwhile, the detector is in signal linkage with the plugging valve, a heat transfer loop is rapidly switched in the case of serious damage, the continuous and stable thermal control function is achieved, and therefore the on-orbit operation life of a spacecraft is further prolonged.

The invention provides a float glass product quality optimization method and system, a medium and a product, and relates to the technical field of automatic control. Comprising the following steps: comparing a real-time transverse thickness distribution curve with a standard datum line to screen abnormal areas; tracing and positioning a target thermal control partition and a component according to the pulling speed; generating a mechanical stretching and temperature adjusting instruction based on the thickness out-of-tolerance quantity; when the temperature of the tin liquid does not reach the standard, mechanical stretching is executed, and temperature is increased synchronously; in the process, the difference value between the stretching speed and the glass flow speed is dynamically adjusted according to the temperature closeness degree until the temperature reaches the standard, and synchronous operation of the edge roller is recovered. According to the process, a non-response dead zone in a traditional single temperature control mode is eliminated, a long-distance waste strip generated by waiting for temperature rise is avoided, and the extremely short-term response speed and the long-term steady-state control precision in the float glass forming process are improved.

The invention relates to the technical field of oxygen production, and discloses an air suspension oil-free VPSA oxygen production system and method based on multi-dimensional closed-loop control, the system adopts a buffer-tank-free direct connection architecture, and a real-time surge margin is calculated through a sensing reconstruction module, and a power bypass module is driven to dynamically match fluid impedance to suppress surge. A thermal control buffer module is introduced, cooling adjustment is locked under the sensitive working condition through dynamic thermal interlocking logic, and temperature fluctuation is buffered and stabilized through thermal capacity. And the central decision-making module executes a density compensation and time sequence feedforward strategy, and preadjusts the torque of the compressor and the opening slope of the valve according to the air inlet density and the process time sequence. The closed-loop control logic based on the real-time surge margin and the change rate of the real-time surge margin is utilized, the high-speed unloading valve is driven to provide a discharge channel when the system impedance abnormally rises, and the hydrodynamic instability caused by process switching of the direct connection system and the equipment overload risk caused by environment load change are effectively restrained.

The invention belongs to the technical field of thermal control of spacecrafts, and discloses a topological optimization fin for a spacecraft and a phase change heat storage and transfer system with the topological optimization fin. The fins are of a tree-shaped topological structure and are optimally designed based on an SIMP method, the size does not exceed 12% of a design domain, and the fins are made of AISi10Mg aluminum alloy. The system integrates the fins, the phase change material and the heat insulation container, is adaptive to equipment with different powers, the peak temperature is as low as 55.63 DEG C, the thermal management time is as long as 4820s, and the thermal control efficiency and reliability of the satellite are remarkably improved.

The invention discloses a high-stability back-mounted resistive flexible pressure sensor simulating an energy barrier structure. The high-stability back-mounted resistive flexible pressure sensor comprises a flexible substrate layer, a gradient conductive layer, a high conductive layer and a packaging layer which are sequentially stacked from bottom to top, the gradient conductive layer comprises a gradient conductive substrate, a left gradient conductive area and a right gradient conductive area are arranged on the gradient conductive substrate at intervals, each gradient conductive area is provided with a plurality of through holes, and conductive materials filled in the through holes form conductive columns. The conductive columns in part of the through holes are multi-section type conductive columns formed by multiple sections of column bodies which are vertically arranged at intervals, and the conductive columns in the rest of the through holes are continuous conductive columns; the flexible substrate layer is a thermal control reversible bonding layer, and two substrate layer conductive areas corresponding to the two gradient conductive areas respectively are arranged on the flexible substrate layer. Compared with the prior art, the resistance-type flexible pressure sensor has the following remarkable advantages that the problem that the resistance-type flexible pressure sensor is difficult to realize high sensitivity and high linearity at the same time is effectively solved, and the stability and repeatability of the resistance-type flexible pressure sensor are remarkably improved.

The invention provides an aluminum alloy precision forging forming die multi-area independent temperature control system and method, the system comprises a forming die assembly, a force thermal decoupling support base, a fluid temperature control supply station and a main control unit, the forming die assembly comprises a plurality of heat conduction inserts separated by heat insulation isolation layers; a rigid bearing loop and a dynamic thermal control loop which are parallel to each other are integrated on the force thermal decoupling supporting base, the dynamic thermal control loop drives the high-thermal-conductivity telescopic thermal bridge and the interface flexible dielectric layer to ascend and descend through a displacement actuator, and in a non-forging state, the thermal bridge supports the heat conduction insert and maintains a safety gap with the rigid bearing stand column; in the forging impact stage, the heat conduction insert moves downwards to eliminate the safety gap, the rigid bearing stand column bears the forming load, the main control unit adjusts the output force of the actuator according to temperature feedback, and the contact thermal resistance is adjusted and controlled in real time by changing the interface contact pressure. The problem that a precise temperature control assembly is difficult to bear forging impact is solved, and quick and precise response of multi-area independent heat flow is achieved.

The application discloses a kind of satellite-borne infrared emissivity differential measurement method and device using cold black background, belong to spacecraft thermal control and material on-orbit testing technical field, purpose is to eliminate environmental stray radiation and conduction heat leakage interference, realize material emissivity high-precision in-situ on-orbit test.The application relies on deep space cold black environment and differential disturbance thought, supporting layout emissivity known standard unit and unit to be measured, make two in consistent light thermal condition, respectively establish transient heat balance equation.Because two kinds of units are consistent, such as common-mode interference of stray radiation, conduction heat leakage, two formula difference can be removed interference term, only keep and emissivity related radiation heat loss term.Through the design of different thermal control conditions (such as balance heating, constant temperature control, dynamic heating), the real emissivity of the material to be measured is solved.The application is suitable for in-situ, high-precision measurement of the infrared emissivity of spacecraft surface materials, especially intelligent thermal control materials such as thermochromic materials in space environment.

Disclosed is a satellite which includes an Attitude Determination and Control System (ADCS) and at least one radiative surface, where the orientation of the satellite with respect to the sun is change

The application relates to the technical field of spacecraft thermal control, and particularly provides a spacecraft multilayer heat insulation assembly thermal bridge suppression type bolt fixing structure which comprises a fixing assembly, a heat insulation bushing, a first heat insulation gasket, a second heat insulation gasket, a multilayer heat insulation assembly and a structural member; a stud passes through the second heat insulation gasket, the structural member and the multilayer heat insulation assembly in sequence; the outer surface of the stud is covered with the heat insulation bushing; the heat insulation bushing is a gradient functional composite structure; the heat insulation bushing comprises, from inside to outside, a heat insulation damping layer, a heat reflection layer and a structural enhancement radiation resistance layer; the contact surface between the second heat insulation gasket and the structural member is provided with a micro-cone array structure; the contact surface between the first heat insulation gasket and the top of the heat insulation bushing is provided with a micro-cone array structure; and the micro-cone array structure is used for filling assembly gaps and reducing solid heat conduction. The application has the advantages of low heat leakage, strong space adaptability and high thermal resistance stability.

The invention discloses a micromotor-driven distributed turbulent flow pumpless liquid cooling device for space thermal control. The micromotor-driven distributed turbulent flow pumpless liquid cooling device comprises a pipeline body and an impeller pump, the impeller pump comprises an impeller with the outer diameter being D and capable of actively rotating. When the impeller pump is used for overall heat dissipation of a single small-size electronic element, one impeller pump is arranged in the cooling flow channel at the position 0.5 D-1. 5D away from the upstream of the small-size electronic element; when the impeller pump is used for eliminating the hot spots of the large-size electronic element, one impeller pump is arranged in the cooling flow channel at the position 0.5 D-1. 5D away from the upstream of each hot spot to be eliminated. An external pump is removed, and the impeller pump is arranged in the cooling flow channel, so that on one hand, a cooling working medium is pumped, on the other hand, a turbulent flow effect is achieved on the cooling working medium, a boundary layer is broken, and the heat dissipation effect is improved. In addition, for a large-scale heat dissipation scene, a plurality of impeller pumps can be arranged in the cooling flow channel in an array mode, the impeller pumps can be placed at local hot spots in a targeted mode, targeted heat dissipation is achieved, and the heat dissipation efficiency and uniformity are further improved.

The invention provides a multi-physics-field coupled core particle microchannel boiling heat exchange experiment testing device and testing method, and belongs to the field of boiling heat exchange experiment testing devices. According to the invention, a laser thermal control module, a reflection temperature measurement module, a particle velocity measurement module, a three-dimensional micro-control module, a stress test module, a sound field test module and an electric field test module are creatively integrated, and flexible combination and active control of each physical field are realized through standardized interfaces. Local point heating is achieved through pulse laser, non-contact transient surface temperature analysis is achieved through a heat reflection method, a micro-nano scale phase change flow field is analyzed through a PIV system, local thermal stress is measured through an embedded film strain gauge set, and automatic alignment and cooperative measurement of all modules are achieved in combination with a high-precision piezoelectric displacement table. Through modular design and system integration, accurate coupling and cooperative measurement of multiple physical fields of light, sound, heat, force and flow on the core particle scale are realized.

The application relates to the technical field of infrared stealth, precise thermal control and electromagnetic compatibility, and particularly discloses a film system structure with visible ultra-high reflectivity, middle-infrared and far-infrared low emissivity and microwave high permeability; the medium stack layer has high reflectivity to visible light; the metal microstructure layer has low emissivity to middle-infrared and far-infrared light and high permeability to microwaves; the film system structure has visible light reflectivity greater than 60%, middle-infrared and far-infrared light emissivity lower than 30% and microwave permeability higher than 60%. The application realizes perfect compatibility of infrared stealth and microwave absorption, keeps infrared low emissivity (epsilon < 0.1) and realizes high permeability (greater than 95%) to 1-18GHz microwave bands. The application solves the thermal failure problem of the composite stealth structure, realizes average visible light reflectivity (greater than 95%) through the medium stack layer, greatly reduces the solar heat load and improves the overall optical performance.

The utility model discloses a quick dismounting and connecting device of intelligent thermal control equipment, the quick dismounting and connecting device comprises an upper connecting frame and a lower connecting frame, the upper connecting frame is connected to the side wall of an upper shell, and the upper connecting frame is provided with a limiting part which bends and extends inwards; the lower connecting frame is connected to the bottom shell in a sliding mode, the lower connecting frame is provided with a locking part which is bent and extends outwards, an adjusting bolt is further connected to the lower connecting frame in a driving mode, and the adjusting bolt penetrates through the rear side wall of the upper shell and is in threaded connection with the lower connecting frame so as to drive the lower connecting frame to move relative to the upper connecting frame. The limiting part and the locking part are mutually clamped or separated, when the limiting part and the locking part are mutually clamped, the upper shell and the bottom shell are mutually locked and fixed, and when the limiting part and the locking part are mutually separated, the upper shell is separated from the bottom shell. According to the technical scheme, the disassembly and connection efficiency of the intelligent thermal control equipment is improved.

The invention discloses a high-temperature-resistant thermal control film and a preparation method thereof, relates to the technical field of thermal control materials, and aims to solve the problems that the high temperature resistance, the mechanical strength and the component compatibility of a traditional thermal control film are difficult to consider at the same time, and the aging resistance and the environmental corrosion resistance are poor. The preparation method comprises the following steps: by taking polytetrafluoroethylene and fluorinated ethylene propylene as matrixes, firstly preparing silicon-fluorine modified graphene and a modified cross-linking agent, and then preparing a product through the steps of preparation of fluoroalkene grafted graphene composite powder, preparation of pre-crosslinking type mixed slurry, film casting and stepped drying, cross-linking curing, segmented post-curing and the like. Through synergistic modification, a compact three-dimensional cross-linked network is constructed, and process optimization is matched, so that the prepared film has excellent high-temperature-resistant stability, mechanical strength, heat insulation and temperature control effects and flame retardance, and can be widely applied to the fields with strict requirements on thermal control materials, such as aerospace, electronic and electrical engineering and the like.

A glass article comprising a photocatalytic coating including a titanium nitride layer and an outer titanium oxide layer, preferably at least partially in anatase form, said article being configured to impart a blue colour in transmission to a multiple glazing unit in which it constitutes the outer face, said multiple glazing unit further comprising a low-emissivity coating on another face of said multiple glazing unit, in particular face 2 or 3.

The invention discloses a mold coating and a casting mold, relates to the technical field of casting manufacturing, and discloses the mold coating which comprises a demolding layer, the surface of the demolding layer has a pore structure; the metal melt is in a Cassie-Baxter state under the condition that the demolding layer is in contact with the metal melt and the pressure applied to the metal melt is smaller than preset critical pressure; and under the conditions that the demolding layer is in contact with the metal melt and the pressure applied to the metal melt is greater than or equal to the critical pressure, the metal melt is in a Wenzel state. According to the mold coating, staged dynamic thermal control can be achieved, efficient heat insulation is provided in the initial stage of mold filling so as to guarantee the fluidity, meanwhile, rapid heat conduction is achieved in the solidification stage so as to promote densification, and then the casting quality can be improved.

The invention relates to the technical field of power distribution network energy storage safety, and discloses a lithium battery thermal runaway identification method based on mixed cooperation of a polynomial function and a logarithmic function, and the method comprises the steps: carrying out model simulation calculation through employing the polynomial function or the logarithmic function at each stage in the whole thermal runaway process of a lithium battery pack, and obtaining a mixed function model; performing movement correction on the mixed function model; according to a real-time temperature data sample and a data homology and isomerism discrimination method, carrying out localized abnormal inflection point calculation, and carrying out offset processing on the corrected mixed function model at a corresponding time point when the abnormal inflection point appears and the current environment temperature; and performing thermal failure condition study and judgment on the currently received temperature data, deducing an optimal window period of energy dissipation thermal control according to the shifted mixed function model, and starting a temperature suppression device at the same time, so that the temperature of the lithium battery pack is recovered to a normal temperature state. According to the invention, early-stage thermal runaway fault early warning and health state management are realized.

The application discloses a high-reliability long-service-life compensator for spacecraft thermal control and a preparation method, relates to the field of space temperature control fluid loop compensators, and comprises a storage tank body, an upper cover and a bellows assembly. The upper cover is welded to one end of the storage tank body, and the bellows assembly is welded to the other end of the storage tank body. The bellows assembly is located inside the storage tank body and is used for connecting a thermal control fluid loop. A liquid cavity is formed in the bellows assembly, the liquid cavity is communicated with the thermal control fluid loop, and an air cavity is formed between the bellows assembly and the storage tank body. The main function of the compensator is to reduce fluid loop pressure fluctuation, prevent cavitation caused by excessively low inlet pressure of the loop pump, and compensate for the reduction of liquid working medium caused by long-term operation, maintenance and micro-leakage of the system. The product provided with a liquid level sensor also has a liquid level display function.

The invention relates to the technical field of monitoring devices, and discloses a monitoring device of thermal control automation equipment, comprising a mounting base, the lower end face of the mounting base is provided with a plug-in groove and a pair of dovetail grooves, the dovetail grooves are located at the front and rear sides of the plug-in groove, the plug-in groove is internally provided with a clamping groove, the inner wall of the clamping groove is provided with a mounting hole, and the mounting hole is communicated with the dovetail grooves. A mounting box is fixedly connected to the right lower end of the mounting base; the upper end of the camera is fixedly connected with a connecting rod, and the upper end of the connecting rod is fixedly connected with a clamping plate. The high-pressure gas generating mechanism is integrated in the mounting box, and the threaded rod rotates to drive the eccentric wheel and the connecting rod to move, so that the sleeve piston reciprocates, clean compressed air is automatically supplemented to the high-pressure tank, and a closed circulating gas source is formed; meanwhile, the filter element in the mounting box performs secondary filtration on ambient air entering the sleeve, corrosive particles such as pulverized coal and sulfide are prevented from entering an air path, it is guaranteed that the purging air pressure is stable under long-term operation, and the lens is not subjected to secondary pollution.

The utility model relates to the technical field of telescopes, in particular to an all-air air conditioning system for thermal control of a telescope dome. The all-air air conditioning system for thermal control of the telescope dome comprises a shell; the air return assembly is arranged in the shell, the air return assembly is provided with a first air return pipe, and the first air return pipe is communicated with the main mirror chamber; the air supply assembly is arranged in the shell, the air supply assembly is provided with a fresh air pipe and an air supply pipe, the fresh air pipe is communicated with the outside, and the air supply pipe is communicated with the main mirror chamber; the temperature control assembly is arranged in the shell, the temperature control assembly communicates with the fresh air pipe and the air supply pipe, and the temperature control assembly is used for heating or refrigerating air in the air supply pipe; and the detection assembly comprises sensors arranged in the main mirror chamber, the air supply pipe and the outside, and the sensors are connected with the temperature control assembly so as to transmit detected temperature information to the temperature control assembly. The air return assembly, the air supply assembly and the temperature control assembly are integrated in the shell, and the whole air conditioning system is simple in structure and convenient to control.

The invention discloses a multi-field coupling robot self-adaptive inspection method and system based on a creative technology stack, and the method comprises the steps: reading a fixed historical parameter set in a previous inspection period, collecting the environment data of a current operation region, generating a control parameter set, calling thermal control and propulsion parameters in the control parameter set, and outputting real-time flow field data and attitude control quantity. Based on real-time flow field data and attitude control quantity, navigation speed and propulsive power are optimized, energy consumption data and path tracking data are synchronously recorded, a real-time signal-to-noise ratio is calculated by using environment real-time parameters, communication states are adjusted by combining communication bandwidth parameters in a control parameter set, and the environment real-time parameters and communication state data are synchronously received. Summarizing the data to complete data archiving; through heat-flow coupling control and multi-mode sensing fusion and environment adaptive communication and parameter iterative optimization cooperation, stable inspection in a complex flow field, zero-visibility defect identification and reliable return of noisy environment key data are realized.