An integrated active cooling temperature control system for a hypersonic vehicle

Abstract

The application belongs to the technical field of temperature control of hypersonic aircraft, and discloses an integrated active cooling temperature control system for a hypersonic aircraft. The integrated active cooling temperature control system is characterized by different temperature control intervals of two cabins, and cooling air is circulated between the two cabins by a heat exchange fan, so that the outlet low-temperature air of the precision instrument cabin is used to cool the electronic device cabin, and integrated control of the temperatures of the two cabins is realized. The integrated active cooling temperature control system has the characteristics of simple structure, convenient processing, low manufacturing cost and high reliability, and can make the hypersonic aircraft adapt to longer and more complex flight tasks.

Description

Technical Field

[0001] This invention belongs to the field of hypersonic vehicle cabin temperature control technology, and particularly relates to an integrated active cooling and temperature control system for multiple compartments in a hypersonic vehicle. Background Technology

[0002] Compared to traditional aircraft, hypersonic vehicles possess significant practical value due to their extremely high speeds, enabling wide-range, rapid, and precise strikes. During missions, hypersonic vehicles not only endure severe external aerodynamic heating but also the thermal loads of high-power equipment. Furthermore, changes in the external environment can cause drastic variations in the internal thermal load. Internal cabin temperature has become a crucial factor affecting the performance of hypersonic vehicles, necessitating research into long-term active cabin temperature control technologies.

[0003] Due to their high Mach numbers and intense shock waves, hypersonic vehicles cannot utilize ram air to cool their internal thermal loads like conventional aircraft. Existing hypersonic vehicles primarily employ traditional passive thermal protection measures, such as covering the exterior with ablative materials, ceramic heat-resistant tiles, and insulating felt. However, these thermal protection materials have limited thermal adaptability, requiring hypersonic vehicles performing specific missions to carry insulation layers of a thickness matching the mission's requirements. Consequently, the flight trajectories and missions of existing hypersonic vehicles are relatively fixed, severely limiting their performance. For hypersonic vehicles carrying precision instruments and equipment, continuing to rely on passive thermal protection measures is insufficient to meet the requirements of their limited operating temperature range over extended periods.

[0004] To address the challenge of temperature control within hypersonic vehicle cabins, current technologies primarily employ passive thermal insulation measures. Active cooling methods, such as reverse jets and jet impact, are only suitable for cooling localized areas of high heat flux density. For hypersonic vehicles with multiple sections that require extended operation, conventional direct cooling solutions using liquid nitrogen or liquid carbon dioxide are insufficient for large-area, high-precision temperature control. Active temperature control of hypersonic vehicle cabins not only achieves thermal protection and weight reduction but also enables them to perform more complex flight missions for longer durations. Therefore, research into active temperature control technology for hypersonic vehicle cabins is imperative. Summary of the Invention

[0005] The purpose of this invention is to provide an integrated active cooling and temperature control system for the precision instrument compartment and electronic equipment compartment of a hypersonic vehicle, which can not only meet the different temperature control requirements of the two compartments, but also greatly extend the flight time of the hypersonic vehicle under different flight missions.

[0006] Typical hypersonic vehicles often have internal compartments divided into a precision instrument compartment and an electronics compartment, depending on the operating environment of the equipment. The normal operating temperature range for the precision instrument compartment is generally 15~30℃, while the operating temperature range for the electronics compartment is generally -30~60℃. To achieve independent active temperature control for the two compartments, this invention proposes an integrated active cooling and temperature control system based on forced air convection cooling and electric heating. This integrated active cooling and temperature control system, taking into account the different temperature control ranges of the two compartments, uses a heat exchange fan to drive cooling air to circulate between the two compartments, fully utilizing the low-temperature air exiting the precision instrument compartment to cool the electronics compartment, thus achieving integrated temperature control for both compartments.

[0007] The specific technical solution of the present invention is as follows:

[0008] An integrated active cooling and temperature control system for hypersonic vehicles is disclosed. This system is used for integrated active cooling and temperature control of the precision instrument compartment and the electronic equipment compartment of the hypersonic vehicle. The precision instrument compartment houses precision instruments and equipment with an operating temperature range of 15~30℃. The electronic equipment compartment houses electronic equipment, including low-heat-generating equipment, non-heat-generating equipment, and / or high-heat-flux-density heating equipment, with an operating temperature range of -30~60℃.

[0009] An open partition is provided between the precision instrument compartment and the electronic equipment compartment, and a ventilation opening is provided in the center of the open partition;

[0010] The precision instrument compartment is equipped with an air supply duct and an electric heating device. The air supply duct is located on the outside of the precision instrument, with one end connected to an air supply hole on the open partition and the other end extending to the top of the precision instrument compartment. The electric heating device is located on the inner wall of the precision instrument compartment.

[0011] The electronic equipment compartment is equipped with a heat exchanger, a heat exchange fan, a liquid delivery pipeline, a liquid storage container, a refrigerant, a pressure and flow control device, and an exhaust pipeline. One end of the heat exchanger is connected to the liquid storage container via the liquid delivery pipeline, and the other end is connected to the exhaust pipeline. The liquid storage container contains a refrigerant, and the liquid delivery pipeline is equipped with a pressure and flow control device for adjusting the flow rate and pressure of the refrigerant.

[0012] When the integrated active cooling and temperature control system needs cooling, the refrigerant travels along the liquid delivery line to the heat exchanger, where it evaporates and / or boils to absorb heat, cooling the high-temperature air in the electronic equipment compartment to low-temperature air. Driven by the heat exchange fan, the low-temperature air travels through the air supply duct to the top of the precision instrument compartment, where it absorbs heat and then flows out through the vent in the center of the open partition, returning to the electronic equipment compartment to complete the cooling cycle. When the integrated active cooling and temperature control system needs heating, the liquid delivery line and the vent in the center of the open partition are closed, and the electric heating device is turned on.

[0013] Preferably, the electronic equipment compartment is also equipped with a turbulence fan.

[0014] Preferably, the electronic equipment compartment is further provided with a microchannel radiator, which is installed on a high heat flux density heating device. One end of the microchannel radiator is connected to a liquid storage container via a liquid delivery line, and the other end is connected to an exhaust line. A pressure and flow control device is installed on the liquid delivery line to regulate the flow rate and pressure of the refrigerant.

[0015] Preferably, the heat exchanger is a finned tube phase change heat exchanger.

[0016] Preferably, the refrigerant is liquid ammonia or pentafluoropropane.

[0017] The beneficial effects of this invention compared to the prior art are as follows:

[0018] 1. The integrated active cooling and temperature control system proposed in this invention makes full use of the cooling capacity of the carried refrigerant, and can actively control the temperature of the precision instrument compartment and the electronic equipment compartment regardless of the ambient temperature and flight mission conditions, and keep their temperatures within the allowable operating range of the equipment.

[0019] 2. The integrated active cooling and temperature control system proposed in this invention achieves cooling and temperature reduction inside the hypersonic vehicle without changing the geometry of the hypersonic vehicle or generating any air resistance.

[0020] 3. The integrated active cooling and temperature control system proposed in this invention has a simple structure, is easy to process, has low manufacturing cost, and a high reliability coefficient.

[0021] 4. By making reasonable use of the integrated active cooling and temperature control system of the present invention, a better heat prevention and weight reduction effect can be achieved, enabling hypersonic aircraft to adapt to longer and more complex and varied flight missions. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the accompanying drawings used in the embodiments will be briefly introduced below. The features and advantages of the present invention can be more clearly understood by referring to the accompanying drawings. The accompanying drawings are schematic and should not be construed as limiting the present invention in any way. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the structure of an integrated active cooling and temperature control system for hypersonic vehicles according to the present invention.

[0024] Among them, 1-Insulation layer, 2-Metal structure of the body, 3-Air supply duct, 4-Precision instrument, 5-Electric heating device, 6-Open partition, 7-Finned tube phase change heat exchanger, 8-Heat exchange fan, 9-Liquid delivery line, 10-Liquid storage container, 11-Refrigerant, 12-Pressure and flow control device, 13-Microchannel radiator, 14-High heat flux density heating equipment, 15-Exhaust line, 16-Turbulence fan, 17-Low heat generation equipment, 18-Non-heat generation equipment. Detailed Implementation

[0025] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other.

[0026] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and therefore the scope of protection of the invention is not limited to the specific embodiments disclosed below.

[0027] Hypersonic vehicles typically have two internal compartments: a precision instrument compartment and an electronic equipment compartment, depending on the operating environment of the equipment. The precision instrument compartment houses sophisticated instruments and equipment, requiring a high temperature tolerance, generally controlled within a range of 15–30°C. The electronic equipment compartment stores various electronic devices, including low- or non-heat-generating equipment and high-heat-flux-density equipment, generally requiring a controlled operating temperature range of -30–60°C. To achieve temperature control in both compartments, an active cooling and temperature control system based on forced convection cooling and electric heating is proposed.

[0028] like Figure 1 As shown, an integrated active cooling and temperature control system for hypersonic vehicles includes: a heat insulation layer 1, a fuselage metal structure 2, an air supply duct 3, precision instruments 4, an electric heating device 5, an open partition 6, a finned tube phase change heat exchanger 7, a heat exchange fan 8, a liquid delivery pipeline 9, a liquid storage container 10, a refrigerant 11, a pressure and flow control device 12, a microchannel radiator 13, a high heat flux density heating device 14, an exhaust pipeline 15, a turbulence fan 16, a low-heating device 17, and a non-heating device 18.

[0029] Specifically, an open partition 6 is provided between the precision instrument compartment and the electronic equipment compartment, with a central ventilation opening to connect the airflow areas of the two compartments.

[0030] The precision instrument compartment includes an air supply duct 3, a precision instrument 4, and an electric heating device 5; the air supply duct 3 is located outside the precision instrument 4, with one end connected to an air supply hole on the open partition 6 and the other end extending to the top of the precision instrument compartment; the electric heating device 5 is located on the inner wall of the precision instrument compartment.

[0031] The electronic equipment bay includes an electric heating device 5, a finned-tube phase change heat exchanger 7, a heat exchange fan 8, a liquid delivery line 9, a liquid storage container 10, a refrigerant 11, a pressure and flow control device 12, a microchannel radiator 13, a high heat flux density heating device 14, an exhaust line 15, a turbulence fan 16, a low-heating device 17, and a non-heating device 18. The finned-tube phase change heat exchanger 7 is positioned directly opposite the air inlet of the open partition 6, with the heat exchange fan 8 positioned behind it. One end of the finned-tube phase change heat exchanger 7 is connected to the liquid storage container 10 via the liquid delivery line 9, and the other end is connected to the exhaust line 15. The liquid storage container 10 contains the refrigerant 11. The pressure and flow control device 12 is installed on the liquid delivery line 9 to regulate the flow rate and pressure of the refrigerant 11, thereby controlling the cooling capacity to cope with complex and ever-changing flight missions.

[0032] When the integrated active cooling and temperature control system requires cooling, the refrigerant 11 travels along the liquid delivery line 9 to the finned tube phase change heat exchanger 7. In the finned tube phase change heat exchanger 7, it evaporates or boils, absorbing heat to cool the high-temperature air in the electronic equipment compartment to low-temperature air. The refrigerant, after absorbing heat, turns into vapor and is discharged from the exhaust line 15. Driven by the heat exchange fan 8, the low-temperature air passes through the air outlet of the open partition 6 and reaches the top of the precision instrument compartment via the air supply duct 3. After absorbing heat inside the compartment, it flows out from the vent in the center of the open partition 6, continuing to cool the electronic equipment compartment and completing the cooling cycle. When the integrated active cooling and temperature control system requires heating, the liquid delivery line and the vent in the center of the open partition can be closed, and the electric heating device 5 can be turned on.

[0033] To improve the temperature uniformity of the air inside the electronic equipment compartment, turbulence fans 16 can be arranged in appropriate locations within the compartment, based on the distribution of the electronic equipment. This enhances the disturbance of the air inside the compartment, resulting in a more uniform temperature distribution. The size, performance, installation location, and angle of the turbulence fans need to be determined according to the specific distribution of the equipment within the compartment. Optimization and adjustments can be made by performing simulation analysis on a simplified 3D model of the electronic equipment compartment.

[0034] For the high heat flux density heating device 14 in the electronic equipment compartment, a separate microchannel radiator 13 can be designed to cool it down, taking into account its structural dimensions. Specifically, a microchannel radiator 13 is installed on the high heat flux density heating device 14. One end of the microchannel radiator 13 is connected to the liquid storage container 10 via a liquid delivery line 9, and the other end is connected to the exhaust line 15. A pressure and flow control device 12 is installed on the liquid delivery line 9 to regulate the flow rate and pressure of the refrigerant 11.

[0035] In addition, the mass flow rate of the refrigerant can be adjusted reasonably according to the changes in the ambient temperature inside the two compartments, so as to reduce the amount of refrigerant that needs to be carried.

[0036] Forced convection cooling has limited effectiveness, with convective heat transfer coefficients typically ranging from 20 to 300 W / (m·K). Therefore, a certain thickness of heat insulation structure is required outside the hypersonic vehicle cabin, the thickness of which depends on the specific flight mission and temperature control range. Heat insulation layer 1 is fundamental to ensuring normal hypersonic flight, primarily reducing the penetration of aerodynamic heat into the cabin. With active cooling and temperature control measures implemented inside the cabin, the heat insulation layer can be adjusted appropriately based on the specific flight mission. The temperature control range for the electronics bay is relatively wider, allowing for a further reduction in the thickness of its heat insulation layer compared to the precision instrument bay. For a hypersonic vehicle with a cruising altitude of 8 km and a hypersonic flight time of 20 minutes, if a heat insulation material with a thermal conductivity of 0.08 W / (m·K) is used, the thickness of the heat insulation layer in the precision instrument bay should not be less than 25 mm, and the thickness in the electronics bay should not be less than 20 mm.

[0037] The refrigerant 11 is stored in the liquid storage container 10 and placed inside the electronic equipment compartment. The refrigerant should be a non-flammable, non-explosive refrigerant with a large latent heat of vaporization and a phase change temperature not higher than the lower limit of the temperature control of the precision instrument compartment, such as liquid ammonia or pentafluoropropane.

[0038] The finned tube phase change heat exchanger 7 is the core component of the integrated active cooling and temperature control system. In order to make full use of the latent heat of the refrigerant 11, smooth corrugated fins can be used to improve its heat exchange efficiency. Its specific parameters, such as fin spacing, number of fin layers, and tube diameter, can be designed according to the maximum heat load in the aircraft cabin.

[0039] The air supply duct 3 was structurally designed based on the layout characteristics of the two-compartment equipment to minimize airflow resistance and ensure uniform airflow distribution. Specifically, the use of dual air supply ducts allows cooling air to flow evenly within the precision instrument compartment.

[0040] The heat exchange fan 8 is the power source for air circulation between the two compartments and adopts a small variable frequency axial flow fan. During the design and selection of the fan, the coupling flow resistance between the finned tube phase change heat exchanger 7 and the air supply duct 3 should be simulated and evaluated. Selection should be based on the simulation results and with reference to the flow-static pressure characteristic curves of existing fans. If the existing fan cannot meet the requirements, a small variable frequency axial flow fan can be independently designed.

[0041] When the hypersonic vehicle is idling in a low-temperature environment or cruising in a high-altitude, low-temperature environment, heat continuously flows out of the cabin, and the cabin temperature gradually decreases over time. When the temperature inside the precision instrument cabin approaches the lower limit of its operating temperature range, the fluid delivery line 9 and the vent at the center of the open partition 6 are closed, and the heating device inside the precision instrument cabin is activated. Furthermore, when the temperature inside the electronic equipment cabin approaches the lower limit of its operating temperature range, the electric heating device 5 inside the precision instrument cabin is activated.

[0042] When the aircraft is idle in a high-temperature environment or achieving supersonic flight, the high-temperature external airflow or severe aerodynamic heating will cause the cabin temperature to gradually rise. When the temperature inside the precision instrument cabin approaches the upper limit of its operating temperature range, cooling should be initiated. Specifically, the pressure and flow control device 12 is turned on, allowing the refrigerant 11 to flow into the finned tube phase change heat exchanger 7; simultaneously, the heat exchange fan 8 is activated to draw air from the electronic equipment cabin into the air supply duct 3. After flowing through the finned tube phase change heat exchanger 7, the air becomes low-temperature air, providing sufficient cooling to the precision instrument cabin. After cooling the precision instrument cabin, the low-temperature air flows back to the electronic equipment cabin to continue cooling the electronic equipment.

[0043] This invention employs an integrated active cooling and temperature control system for the precision instrument compartment and equipment compartment of a hypersonic vehicle. This fully utilizes the cooling capacity of the carried refrigerant, enabling precise temperature control of both compartments throughout the entire lifespan of the hypersonic vehicle. The integrated active cooling and temperature control system features a simple structure, mature technology, and high reliability. The hypersonic vehicle can adjust the amount of refrigerant it carries according to the flight mission, achieving good heat protection and weight reduction effects. This integrated active cooling and temperature control system is particularly suitable for hypersonic vehicles pursuing ultra-long ranges and undertaking complex and varied flight missions.

[0044] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0045] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0046] In this invention, the terms "first," "second," "third," and "fourth" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The term "multiple" refers to two or more unless otherwise expressly defined.

[0047] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An integrated active cooling and temperature control system for hypersonic vehicles, characterized in that, The integrated active cooling and temperature control system is used for integrated active cooling and temperature control of the precision instrument compartment and the electronic equipment compartment of the hypersonic vehicle; the precision instrument compartment stores precision instruments and equipment with an operating temperature range of 15~30℃; the electronic equipment compartment stores electronic equipment, including low-heat-generating equipment, non-heat-generating equipment and / or high heat flux density heating equipment, with an operating temperature range of -30~60℃. An open partition is provided between the precision instrument compartment and the electronic equipment compartment, and a ventilation opening is provided in the center of the open partition; The precision instrument compartment is equipped with an air supply duct and an electric heating device. The air supply duct is located on the outside of the precision instrument, with one end connected to an air supply hole on the open partition and the other end extending to the top of the precision instrument compartment. The electric heating device is located on the inner wall of the precision instrument compartment. The electronic equipment compartment is equipped with a heat exchanger, a heat exchange fan, a liquid delivery pipeline, a liquid storage container, a refrigerant, a pressure and flow control device, and an exhaust pipeline. One end of the heat exchanger is connected to the liquid storage container via the liquid delivery pipeline, and the other end is connected to the exhaust pipeline. The liquid storage container contains a refrigerant, and the liquid delivery pipeline is equipped with a pressure and flow control device for adjusting the flow rate and pressure of the refrigerant. When the integrated active cooling and temperature control system needs cooling, the refrigerant travels along the liquid delivery line to the heat exchanger, where it evaporates and / or boils to absorb heat, cooling the high-temperature air in the electronic equipment compartment to low-temperature air. Driven by the heat exchange fan, the low-temperature air travels through the air supply duct to the top of the precision instrument compartment, where it absorbs heat and then flows out through the vent in the center of the open partition, returning to the electronic equipment compartment to complete the cooling cycle. When the integrated active cooling and temperature control system needs heating, the liquid delivery line and the vent in the center of the open partition are closed, and the electric heating device is turned on.

2. The integrated active cooling and temperature control system for hypersonic vehicles according to claim 1, characterized in that, The electronic equipment compartment is also equipped with a spoiler fan.

3. The integrated active cooling and temperature control system for hypersonic vehicles according to claim 1, characterized in that, The electronic equipment compartment is also equipped with a microchannel radiator, which is installed on a high heat flux density heating device. One end of the microchannel radiator is connected to a liquid storage container via a liquid delivery line, and the other end is connected to an exhaust line. A pressure and flow control device is installed on the liquid delivery line to regulate the flow and pressure of the refrigerant.

4. The integrated active cooling and temperature control system for hypersonic vehicles according to claim 1, characterized in that, The heat exchanger is a finned tube phase change heat exchanger.

5. The integrated active cooling and temperature control system for hypersonic vehicles according to claim 1, characterized in that, The refrigerant is liquid ammonia or pentafluoropropane.

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