30results about How to "Good heat control effect" patented technology

The invention relates to a combined heat dissipating device provided with fins and a foam heat conduction structure and used for assisting heat dissipation of an individual battery (5). The combined heat dissipating device comprises a shell sleeve (4) sleeving the individual battery (5), wherein a foam structure fills the space between the shell sleeve (4) and the individual battery (5), the foam structure (2) is full filled with a phase-change material (1), multiple fins (3) separating the foam structure (2) are further arranged between the shell sleeve (4) and the individual battery (5), and the two sides of each fin (3) are respectively in tight fit with the shell sleeve (4) and the individual battery (5). Compared with the prior art, the combined heat dissipating device has the advantages of effectively reducing the temperature of a lithium ion battery and preventing thermal runaway.

The invention discloses a novel antistatic white thermal control coating and a preparation method thereof; wherein the coating, from interior to exterior, comprises a surface treatment agent layer, a prime coat layer and a finishing coat layer; the prime coat layer and the finishing coat layer all use room temperature curing type organic silicone resin as a matrix resin; a plurality of sheet-shaped metal powders are crossedly overlapped and arranged in the prime coat layer, and one ends of part of the sheet-shaped metal powders extend to the finishing coat layer; and white zinc oxide is distributed in the finishing coat layer. The coating provided by the invention is white, thickness is 100-140mum, solar absorptance is 0.24-0.29, hemispherical emissivity is 0.85-0.91, total mass loss TML is less than 1%, a collected volatile condensable material CVCM is less than 0.1%, and volume resistivity rhoV is not less than 107 ohm*m. The coating, through 100 times of high and low temperature heat cycle test in a temperature range from -100 to 100 DEG C, has advantages of non-cracking, non-spalling, non-foaming and non-discoloring phenomena, stable optical property and good adhesion force, and can basically satisfy demand of a spacecraft on the antistatic white thermal control coating.

A thermally controlled alumina-potassium silicate coating with low solar absorptivity for artificial satellite, space aircraft, etc is prepared from potassium silicate, diethanolamine, emulsifier, sodium hexametaphosphate, disperser, defoaming agent, light calcium carbonate, heavy calcium carbonate, talc power, mica powder, alumina powder and water through preparing slurry and proportionally mixing with phenylacrylic acid emulsion. Its advantages are high space stability, resistance to atomic oxygen corrosion, and thermal control effect, and low heat absorptivity.

The invention relates to thermal control film on the surface of magnesium lithium alloy, and a preparation method of the thermal control film. According to the preparation method, because a micro-arcoxidation electrolyte system suitable for the magnesium lithium alloy is built on the basis of a lot of solution screening experiments, electrical parameters matched with the solution system are created on the basis of a lot of electrical parameter optimization tests, the binding force of the film prepared on the surface of the magnesium lithium alloy is guaranteed, and the composition of the filmis changed by doping the electrolyte with zirconium salt, then remarkable improvement on thermal control performance of the film is achieved, and the thermal control film meeting the requirements forthermal control of a spacecraft product is prepared on the surface of the magnesium lithium alloy finally. According to the thermal control film on the surface of the magnesium lithium alloy, a micro-arc oxidation technology is adopted, the magnesium lithium alloy is used as a substrate, one layer of ceramic film grows on the surface of the magnesium lithium alloy in an in-situ manner, the film is doped with the zirconium oxide with good thermal control performance, infrared emittance of the film ranges from 0.80 to 0.90, the solar absorptance ranges from 0.20 to 0.30, the part dimensions andthe assembly accuracy of the magnesium lithium alloy are not affected, and the film can be applied to spacecrafts instead of organic coatings.

The invention discloses a novel antistatic white thermal control coating and a preparation method thereof; wherein the coating, from interior to exterior, comprises a surface treatment agent layer, a prime coat layer and a finishing coat layer; the prime coat layer and the finishing coat layer all use room temperature curing type organic silicone resin as a matrix resin; a plurality of sheet-shaped metal powders are crossedly overlapped and arranged in the prime coat layer, and one ends of part of the sheet-shaped metal powders extend to the finishing coat layer; and white zinc oxide is distributed in the finishing coat layer. The coating provided by the invention is white, thickness is 100-140mum, solar absorptance is 0.24-0.29, hemispherical emissivity is 0.85-0.91, total mass loss TML is less than 1%, a collected volatile condensable material CVCM is less than 0.1%, and volume resistivity rhoV is not less than 107 ohm*m. The coating, through 100 times of high and low temperature heat cycle test in a temperature range from -100 to 100 DEG C, has advantages of non-cracking, non-spalling, non-foaming and non-discoloring phenomena, stable optical property and good adhesion force, and can basically satisfy demand of a spacecraft on the antistatic white thermal control coating.

The invention provides a power module based on phase change material and a manufacturing method thereof, which belong to the technical field of power modules. The power module comprises a substrate (1), a ceramic copper-clad plate (2), a phase-change module and a power terminal (7). The upper surface of the substrate (1) is rectangular, a plurality of ceramic copper-clad plates are respectively arranged on the substrate (1), and the ceramic copper-clad plates (2) are connected through a copper bar. The phase-change module is arranged on the ceramic copper-clad plate (2), and a plurality of power terminals (7) are arranged on a power terminal mounting end. The phase change module comprises a heat transfer enhancing frame (3) and a sealing cover (4), and the heat transfer enhancing frame (3)is filled with phase change material. A power semiconductor chip (5) is welded to the outer surface of the sealing cover. The invention is advantageous in that the power module with short-time and controllable junction temperature is provided, which can respond to transient temperature rise of the power module, and is suitable for occasions when short-circuit current is actively provided for supporting the power grid voltage during a power grid fault period, and other impact power occasions of electromagnetic ejection and super-capacitor charging.

The invention provides an optical solar reflector thermal-control coating on the satellite solar panel surface and a preparation method of the coating. The coating comprises the following components:an optical solar reflector, a conductive adhesive and a surface treatment agent, wherein the conductive adhesive is an adhesive formed by mixing an A component, a B component and silver powder according to a predetermined ratio, and the surface treatment agent includes a KH550 silane coupling agent. The coating provided by the invention has better coating electrical conductivity on the basis thatgood thermal control performance (solar absorption ratio and hemispherical emissivity) of the coating is ensured, and the coating has very good adhesion after subjected to surface treatment.

The invention relates to a flexible phase-change material for electronic device thermal control. The flexible phase-change material comprises a phase-change substrate and a support carrier. The support carrier is an elastic polymer. The flexible phase-change material is prepared by the following steps: heating the phase-change substrate and the support carrier in the certain temperature, and placing in the environment of which the temperature is higher than the phase-change temperature after completely fusing and mixing, cooling and rolling. The flexible phase-change material can produce the deformation, such as elastic stretching, bending and torsion, while the temperature is higher than the phase transformation point. The flexible phase-change material is adhered to the surface of the heat production part or filled in clearances between a hot plate and a packaging component while used for the electronic device thermal control. The phase-change material has the good flexibility, so the phase-change material has the performance of a thermal interface material, and is capable of reducing the contract thermal resistance. The flexible phase-change material is capable of solving the problems that the installation is difficult and the contract thermal resistance is larger because the common phase-change material is excessive hard in the thermal control process of the electronic device, and greatly improving the thermal control performance.

The invention discloses a POSS-modified long life thermal control coating combination and a preparation method thereof. The composition comprises a priming paint, a finish paint, and a substrate; a priming paint organic solvent and modified organic fluororesin and zinc oxide powder with mass ratio of 60-75: 25-40; and an finish paint organic solvent and modified multi functional groups methyl silicone resin and zinc oxide powder with mass ratio of 65-75: 25-35. The prepared POSS-modified long life white thermal control coating can prolong the life of space usage and increases stability, the performance of the long life heat thermal control coating prepared by the coating combination is stable, space environment-resistant capability is stronger, the coating construction is simple and is easy to learn, has strong enforcement performance, has longer design and usage time in space environment, and can satisfy the requirement of high-stability white thermal control coating on the product, the adhesive force through 100 times of temperature impact tests between the temperature of -100-+100 DEG C is good, and the vacuum discharge quantity is low.

The invention provides a low solar absorption rate alumina-potassium silicate thermal control coating and a preparation method thereof. The coating consists of potassium silicate, diethanolamine, emulsifier, sodium hexametaphosphate, dispersant, defoamer, Light and heavy calcium carbonate, talcum powder, mica powder, alumina powder and water form a slurry, which is mixed with phenylacrylic acid emulsion at a weight ratio of 1:0.4-0.9. The coating of the present invention has stable space behavior, significant anti-atomic oxygen erosion effect, low heat absorption rate, and good thermal control effect, and is suitable for low-earth orbit vehicles such as satellites, manned spacecraft, space stations, space shuttles and other spacecraft and various types of space. detector.

The invention discloses a method for preparing a coating with high absorptivity and high emissivity, which relates to a method for preparing a coating. The purpose of the present invention is to solve the problem that the coating prepared by the existing magnesium-lithium alloy surface treatment technology has poor bonding force, instability, easy aging and falling off, low absorption rate and low emissivity, which are unfavorable for its application on spacecraft . Methods: 1. Pretreatment of specimens; 2. Preparation of thermal control coating with high absorption and high emissivity in silicate electrolyte system by micro-arc oxidation. The thermal control coating prepared by the invention has higher absorptivity and emissivity and good thermal control performance. The invention can obtain a coating with high absorptivity and high emissivity.

The invention provides a method for preparing a low-resistivity filler and an anti-electrostatic thermal control coating thereof. The low-resistivity filler is obtained through carrying out doping modification on zinc oxide by metal ions and carrying out high-temperature sintering aftertreatment; the anti-electrostatic thermal control coating takes polyfunctional methyl silicone resin as a matrix and the low-resistivity doping-modified zinc oxide powder as a filler, and doping-modified zinc oxide can form a conductive network in the coating. According to the anti-electrostatic thermal control coating prepared by the method, the appearance is white, the thickness is 130 to 180 microns, the solar absorption ratio is 0.22 to 0.27, the hemispherical emittance is 0.85 to 0.91, the total mass loss TML is lower than 1%, the condensable volatile matter CVCM is lower than 0.1%, the volume resistivity [rho]V is not greater than 10<7> omegam, and after the coating is subjected to -100 DEG C-to-+100 DEG C high- / low-temperature heat cycle tests for 100 times, the coating is free of cracking, peeling, blistering and discoloring phenomena and is stable in optical performance and good in adhesive power, so that the requirements of spacecrafts on anti-electrostatic white thermal control coatings are fundamentally met.

The invention discloses an electrochromic thin film device with adjustable light performance in the visible to mid-infrared band and a preparation method thereof. The preparation method comprises the following steps: S1: select a substrate, and perform pretreatment on the substrate; S2: after the treatment Prepare a high transmittance conductive layer on the substrate; S3: deposit WO on the high transmittance conductive layer 3 layer as the color change layer, then in the WO 3 Continue to deposit Ta on the layer 2 o 5 As an electrolyte layer, and then annealed to obtain crystalline WO 3 ; S4: Continue to deposit metal oxide as an ion storage layer, and then repeat step S2 on the basis of metal oxide to obtain an electrochromic thin film device; wherein, if the substrate is a transparent conductive material, the step is directly carried out on the processed substrate S3. The electrochromic thin film device obtained by this method can regulate light performance from visible to infrared light, and can design components for different wavelength bands to obtain various discoloration and heat management performances.

The invention discloses an antistatic thermal control coating composition, a preparation method and applications thereof. The coating composition comprises priming paint and finish paint. The priming paint is composed of a matrix namely organic fluorine resin and a filling material namely modified zinc oxide powder; wherein the zinc oxide is capable of forming vertical channels in the priming paint layer. The finish paint is composed of a matrix namely methyl silicone resin with multiple functional groups and a filling material namely modified zinc oxide powder; wherein part of the filling material penetrates the interface between the priming paint layer and the finish paint layer. The prepared antistatic thermal control coating has a white color, a thickness of 130 to 200 [mu]m, a solar absorption ratio of 0.20 to 0.25, a hemispherical emissivity of 0.85 to 0.91, a total mass loss (TML) not more than 1%, collectable volatile condensed mass (CVCM) not more than 0.1%, and a volume resistivity ([rho]v) not more than 107 [omega].m. The coating does not have the phenomenon of cracking, peeling, bubbling, and fading after 100 times of high-low temperature thermal cycle experiments in a temperature range of -100 to 100 DEG C, the optical properties of the coating is stable, and the adhesive force of the coating is high.

The invention discloses a method for heat transfer and heat dissipation with large heat and high heat flux density based on high-dimensional thermoelectricity. The temperature data acquisition / transmission module collects and transmits the real-time temperature data on the temperature detector in real time, and the control / temperature measurement module integrates the temperature detector. The time is modified in real time, the heat transfer channel in the control / temperature measurement module outputs accurate temperature signals for the collected temperature data, the external power measurement signal module analyzes and compares the output accurate temperature signals, and the high-dimensional heat dissipation matrix passes time synchronization constraints module to realize the large-area distribution control of 1~n groups of thermoelectric cooling chips; as a system-level precise temperature control technology, the present invention realizes a heat flux greater than 10^6W / cm2, a heat transfer distance of more than hundreds of meters, and a laboratory stage Precise control -196°C to 1200°C, the temperature difference between the head end and the end product is only 0.5°C, and the heat dissipation structure design can be customized.

The invention relates to a combined heat dissipating device provided with fins and a foam heat conduction structure and used for assisting heat dissipation of an individual battery (5). The combined heat dissipating device comprises a shell sleeve (4) sleeving the individual battery (5), wherein a foam structure fills the space between the shell sleeve (4) and the individual battery (5), the foam structure (2) is full filled with a phase-change material (1), multiple fins (3) separating the foam structure (2) are further arranged between the shell sleeve (4) and the individual battery (5), and the two sides of each fin (3) are respectively in tight fit with the shell sleeve (4) and the individual battery (5). Compared with the prior art, the combined heat dissipating device has the advantages of effectively reducing the temperature of a lithium ion battery and preventing thermal runaway.

The invention designs a mold slag application process for avoiding defects such as transverse and longitudinal cracks on the surface of a slab during high-speed continuous casting of peritectic steel. The mold flux is used for high-speed continuous casting of peritectic steel; the mold flux is composed of the following components in terms of mass percentage: CaO 37%-40%, SiO 2 28%~32%;Al 2 o 3 0.5% to 2%, MgO 1% to 4%, and MgO / Al by mass ratio 2 o 3 =1‑2:1; MnO+Fe 2 o 3 1.0%~8%;Na 2 O 3%~18%, Li 2 O 2.0%~4.0%; F ‑ 3% to 15%; in the mold flux, the binary basicity CaO / SiO 2 1.2 to 1.3. The average crystal size of the precipitated crystal phase of the mold flux designed in the present invention is less than 8 μm, and the crystal phase is a single lance spar; and the precipitated phase is uniformly distributed in the mold flux crystal layer.

The invention discloses a piston heat control device for a refrigerator compressor. A piston is connected onto a crank through a connecting rod, the connecting rod is rotatably connected with the interior of a connecting rod inserting hole of the piston, the piston heat control device for the refrigerator compressor comprises a heat insulation part and a piston cooling mechanism, the heat insulation part is arranged on the end face of the piston, and the piston cooling mechanism can cool the piston. Due to the addition of the heat insulation part, the heat insulation performance of the pistonis increased, and the piston can be prevented from conducting additional heat energy onto chamber air. In addition, the piston cooling mechanism can cool the piston, and heat energy which is not beneficial to the piston is guided to the outside in time through heat exchange, so that the output power loss of the whole compressor is reduced by the measures, the energy is saved, and the efficiency isimproved.

The invention provides a silicon-containing atomic oxygen-resistant polyimide film material and a preparation method thereof. The film material includes a base film layer, a transition layer and a surface protection layer arranged in sequence; the base film layer includes a modified Polyimide matrix and nano-SiO 2 filler; the transition layer is an interpenetrating network structure of Si-O-Si and polyimide; the surface protection layer is a pure silicon dioxide layer. The atomic oxygen-resistant polyimide film prepared by the present invention is light yellow, with a thickness of 50-80 μm, a tensile strength ≥ 200 MPa, a dielectric strength ≥ 230 V / μm, and a total accumulation of atomic oxygen of 7.83×10 22 atom / cm 2 (10 years in low-Earth orbit) The mass loss rate after action is ≤10%, and the optical performance change is ≤10%. Stable performance and good mechanical properties.