Resistance reduction and heat protection structure of hypersonic flight vehicle
By using porous media and cooling devices on the blunt head and resistance rod of the hypersonic aircraft, the speed and carrier capacity of the aircraft faced by the speed and the capacity of the shock resistance of the aircraft are solved. Essence
Patent Information
- Application Number
- CN202411723538.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-28
- Publication Date
- 2025-01-28
AI Technical Summary
The aerodynamic heating and shock resistance caused by bow shock waves during flight seriously affect the flight speed and carrying capacity.
The blunt head and reducing rod made of porous media materials are combined with the cooling device to reduce the peak of the wall surface of the aircraft through the thermal exchange of the cooling agent and the air film anti -heat prevention, and add the resistance rod at the front end of the blunt head to reduce the thrilling resistance power Essence
The excellent resistance and thermal resistance of the aircraft can be achieved. The resistance rate can reach 56.08%, and the peak temperature of the wall surface decreases by 1225K, which significantly improves the flight speed and carrier capacity.
Smart Images
Figure CN119370320A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of drag reduction and thermal protection of hypersonic aircraft, and in particular to a drag reduction and thermal protection structure of a hypersonic aircraft. Background Art
[0002] Hypersonic vehicles, with their high speeds and strong penetration capabilities, are highly valued by both civilian and military applications worldwide. Hypersonic vehicles typically employ a blunt-bodied configuration. During flight, the strong bow shock wave generated in front of the blunt-bodied configuration causes intense aerodynamic heating of the aircraft's fuselage, which can damage the aircraft's structure and critical electronic equipment. Furthermore, the bow shock wave creates significant shock wave drag, which increases dramatically with increasing Mach number. This drag accounts for more than half of the aircraft's total drag, severely hindering further increases in speed and reducing its carrying capacity. Therefore, there is an urgent need for a drag-reducing and heat-protection structure for hypersonic aircraft. Summary of the Invention
[0003] The present invention provides a hypersonic aircraft drag reduction and heat protection structure, which has a simple structure and has excellent drag reduction effect and heat protection performance.
[0004] The present invention provides a hypersonic aircraft drag reduction and heat protection structure, comprising: a drag reduction rod and a cooling device; the drag reduction rod is installed at the head of a blunt head, the cooling device is arranged inside the blunt head, and the blunt head is made of a porous medium material; the cooling device is used to store and release coolant.
[0005] Preferably, the cooling device includes a coolant storage device and a guide channel; the coolant storage device is used to store coolant or release coolant, and the guide channel is used to provide a transportation channel for the coolant so that the coolant flows out of the porous medium material through the guide channel.
[0006] Preferably, the coolant is at least one of liquid nitrogen, liquid helium, carbon dioxide, and hydrocarbon refrigerants.
[0007] Preferably, the guide channel is made of copper, aluminum, copper alloy, aluminum alloy or a composite material with temperature resistance and thermal conductivity.
[0008] Preferably, the pore size of the porous medium material is in the micron level, and the porosity is 0.2 to 0.7.
[0009] Preferably, the porous medium material is copper, aluminum, copper alloy, aluminum alloy or a composite material with temperature resistance and thermal conductivity.
[0010] Preferably, the drag reducing rod is made of the porous medium material.
[0011] Preferably, the aspect ratio of the drag reducing rod is 0.5 to 2.5.
[0012] Preferably, a cavity is provided in the drag reduction rod, and a center line of the cavity coincides with a center line of the drag reduction rod.
[0013] Preferably, the cavity of the drag reducing rod is communicated with the flow guiding channel.
[0014] Compared with the prior art, the present invention has at least the following beneficial effects:
[0015] The present invention provides a drag reduction and heat protection structure for hypersonic aircraft. The original solid metal material of the blunt body of the hypersonic aircraft is replaced with a porous dielectric material. This allows the gaseous or liquid coolant released by the cooling device to undergo heat exchange from within the aircraft through the porous dielectric material, generating an air film on the surface of the aircraft body for heat protection. Simultaneously, a drag reduction rod is added to the front end of the blunt body, giving the aircraft excellent drag reduction. When the coolant mass flow rate is 0.5 g / s and the drag reduction rod aspect ratio is 2.5, the drag reduction effect of the drag reduction and heat protection structure can reach 56.08%, with a decrease in peak wall temperature of 1225 K. The present invention's simple drag reduction and heat protection structure offers both excellent drag reduction and heat protection effects, and has broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.
[0017] Figure 1 1 is a schematic diagram of a hypersonic aircraft drag reduction and heat protection structure provided by one embodiment of the present invention;
[0018] Figure 2 1 is a schematic diagram of another hypersonic aircraft drag reduction and heat protection structure provided by one embodiment of the present invention;
[0019] Figure 3 1 is a schematic diagram of another hypersonic aircraft drag reduction and heat protection structure provided by one embodiment of the present invention;
[0020] Reference numerals: 10 - drag reduction rod; 20 - cooling device; 30 - blunt head; 101 - cavity; 201 - coolant storage device; 202 - guide channel. DETAILED DESCRIPTION
[0021] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.
[0022] Please refer to Figure 1 An embodiment of the present invention provides a hypersonic aircraft drag reduction and heat protection structure, including: a drag reduction rod 10 and a cooling device 20; the drag reduction rod 10 is installed at the head of a blunt head 30, and the cooling device 20 is arranged inside the blunt head 10, and the blunt head 10 is made of a porous medium material; the cooling device 20 is used to store and release a coolant.
[0023] The present invention replaces the original solid metal material of the blunt body of a hypersonic aircraft with a porous medium material, so that the gas or liquid coolant released by the cooling device can exchange heat from the interior of the aircraft through the porous medium material and generate an air film on the surface of the aircraft body to protect against heat. At the same time, a drag reduction rod is added to the front end of the blunt body, so that the aircraft has an excellent drag reduction effect.
[0024] In a preferred embodiment, Figure 2 As shown, the cooling device 20 includes a coolant storage device 201 and a guide channel 202; the coolant storage device 201 is used to store coolant or release coolant, and the guide channel 202 is used to provide a transportation channel for the coolant so that the coolant flows out of the porous medium material through the guide channel 202.
[0025] It should be noted that the coolant storage device includes but is not limited to a storage tank, an air bag, and other devices that can store gas or liquid. The coolant release method includes but is not limited to using a pump or releasing by its own pressure.
[0026] In a preferred embodiment, the coolant is at least one of liquid nitrogen, liquid helium, carbon dioxide, and hydrocarbon refrigerants.
[0027] It should be noted that at least one is any one or a mixture of any several in any proportion.
[0028] In a preferred embodiment, the flow guiding channel 202 is made of copper, aluminum, copper alloy, aluminum alloy or a composite material with temperature resistance and heat conductivity.
[0029] In a preferred embodiment, the porous medium material is copper, aluminum, copper alloy, aluminum alloy or a composite material with temperature resistance and thermal conductivity.
[0030] In the present invention, since hypersonic aircraft are affected by aerodynamic heating, the selected guide channels and porous medium materials must have heat resistance to ensure that the aircraft can operate stably at high temperatures; at the same time, in order to further export the temperature of the aircraft, the selected guide channels and porous medium materials must also have thermal conductivity.
[0031] In a preferred embodiment, the pore size of the porous medium material is in the micron order, and the porosity is 0.2 to 0.7 (for example, 0.2, 0.3, 0.4, 0.5, 0.6 or 0.7).
[0032] In the present invention, by limiting the pore size of the porous medium material to the micron level, coolant discharge is achieved while avoiding the problem of too small a pore size hindering rapid coolant discharge, and the problem of too large a pore size causing excessive coolant discharge, resulting in excessive coolant consumption and limited coolant storage capacity. Furthermore, this avoids the problem of coolant clogging caused by too few pores when the porous medium material has a porosity below 0.2, and the problem of insufficient heat exchange caused by excessive pore distribution when the porous medium material has a porosity above 0.7. Therefore, the porosity of the porous medium material is limited to 0.2-0.7.
[0033] In a preferred embodiment, the aspect ratio of the drag reducing rod 10 is 0.5 to 2.5 (for example, 0.5, 0.6, 0.8, 1.0, 1.2, 1.5, 1.8, 2.0, 2.2 or 2.5).
[0034] In the present invention, experiments have shown that the aspect ratio of the drag reduction rod is limited to a range of 0.5 to 2.5, which can simultaneously take into account greater drag reduction and heat protection efficiency.
[0035] In a preferred embodiment, the drag reducing rod 10 is made of a porous medium material.
[0036] It should be noted that the drag reduction rod includes but is not limited to a flat head, a pointed head, etc.
[0037] In a preferred embodiment, Figure 3 As shown, a cavity 101 is provided in the drag reduction rod 10 , and the center line of the cavity 101 coincides with the center line of the drag reduction rod 10 . The drag reduction rod 10 is made of a porous medium material.
[0038] In the present invention, the drag reduction rod also uses porous medium materials, which enables the gas or liquid coolant released by the cooling device to pass through the pores of the blunt head and the drag reduction rod for heat exchange, and generate an air film on the surface to prevent heat, thereby achieving heat protection and drag reduction of the drag reduction rod.
[0039] In a preferred embodiment, Figure 3As shown, the cavity 101 of the drag reduction rod 10 is communicated with the flow guide channel 202 , and the drag reduction rod 10 is made of a porous medium material.
[0040] In the present invention, the cavity of the drag reduction rod is connected to the flow guide channel, allowing the gaseous or liquid coolant released by the cooling device to be directly transferred to the cavity through the flow guide channel. The coolant in the cavity then undergoes heat exchange through the pores of the drag reduction rod, forming an air film on the surface to provide heat protection, thereby achieving heat protection and drag reduction for the drag reduction rod. It should be noted that the cavity can be cylindrical or rectangular.
[0041] In order to more clearly illustrate the technical solutions and advantages of the present invention, a hypersonic aircraft drag reduction and heat protection structure is described in detail below through several embodiments.
[0042] Example 1
[0043] This example was prepared as Figure 2 The hypersonic aircraft drag reduction and heat protection structure shown in the figure has a blunt head made of aluminum porous medium material with a pore diameter of 39 μm and a porosity of 0.3; the coolant is liquid nitrogen, and the mass flow rate of the liquid nitrogen is controlled by a pump at 0.5 g / s; the guide channel is made of metal pipes; and the drag reduction rod is made of aluminum with an aspect ratio of 0.5.
[0044] Example 2
[0045] This example was prepared as Figure 3 The hypersonic aircraft drag reduction and heat protection structure shown in the figure has a blunt head made of aluminum porous medium material with a pore diameter of 39 μm and a porosity of 0.3; the coolant is liquid nitrogen, and the mass flow rate of the liquid nitrogen is controlled by a pump at 0.5 g / s; the guide channel is made of metal pipes; and the drag reduction rod is made of aluminum with an aspect ratio of 0.5.
[0046] Example 3
[0047] This example was prepared as Figure 2 The hypersonic aircraft drag reduction and heat protection structure shown in the figure has a blunt head made of aluminum porous medium material with a pore diameter of 39 μm and a porosity of 0.3; the coolant is liquid nitrogen, and the mass flow rate of the liquid nitrogen is controlled by a pump to be 0.5 g / s; the guide channel is made of metal pipes; and the drag reduction rod is made of aluminum with an aspect ratio of 1.
[0048] Example 4
[0049] This example was prepared as Figure 2The hypersonic aircraft drag reduction and heat protection structure shown in the figure has a blunt head made of aluminum porous medium material with a pore diameter of 39 μm and a porosity of 0.3; the coolant is liquid nitrogen, and the mass flow rate of the liquid nitrogen is controlled by a pump at 0.5 g / s; the guide channel is made of metal pipes; and the drag reduction rod is made of aluminum with an aspect ratio of 1.5.
[0050] Example 5
[0051] This example was prepared as Figure 2 The hypersonic aircraft drag reduction and heat protection structure shown in the figure has a blunt head made of aluminum porous medium material with a pore diameter of 39 μm and a porosity of 0.3; the coolant is liquid nitrogen, and the mass flow rate of the liquid nitrogen is controlled by a pump at 0.5 g / s; the guide channel is made of metal pipes; and the drag reduction rod is made of aluminum with an aspect ratio of 2.
[0052] Example 6
[0053] This example was prepared as Figure 2 The hypersonic aircraft drag reduction and heat protection structure shown in the figure has a blunt head made of aluminum porous medium material with a pore diameter of 39 μm and a porosity of 0.3; the coolant is liquid nitrogen, and the mass flow rate of the liquid nitrogen is controlled by a pump at 0.5 g / s; the guide channel is made of metal pipes; and the drag reduction rod is made of aluminum with an aspect ratio of 2.5.
[0054] Comparative Example 1
[0055] Comparative Example 1 is the same as Example 1, except that no drag reduction rod and cooling device are provided at the blunt end.
[0056] Comparative Example 2
[0057] Comparative Example 2 is the same as Example 1, except that no cooling device is provided on the blunt tip.
[0058] Comparative Example 3
[0059] Comparative Example 3 is the same as Example 1, except that no drag reduction rod is provided at the blunt end.
[0060] The present invention conducted thermal protection testing on the hypersonic aircraft drag reduction and thermal protection structures of Examples 1 to 6 and Comparative Examples 1 to 3, using simulation analysis. The simulation conditions were a mainstream static pressure of 5000 Pa, a Mach number of 6, and a temperature of 300 K. The simulation results showed that the peak temperature locations of Examples 1 to 6 were closer to the rear of the blunt nose than those of Comparative Examples 1 to 3. When the drag reduction rod had an aspect ratio of no less than 1.5, the peak temperature was lower than that of other hypersonic aircraft blunt noses. The peak temperature of Example 6 did not exceed 1100 K, while the peak temperature of Comparative Example 1 reached 2200 K. Therefore, the hypersonic aircraft drag reduction and thermal protection structure of the present invention can reduce the peak temperature by approximately 1100 K compared to a blunt nose without drag reduction and thermal protection measures.
[0061] The present invention conducted drag reduction tests by simulating and analyzing the hypersonic aircraft drag reduction and heat protection structures of Examples 1 to 6 and Comparative Examples 1 to 3. The simulation conditions were a mainstream static pressure of 5000 Pa, a Mach number of 6, and a temperature of 300 K. The simulation results showed that the drag reduction rates of the drag reduction and heat protection structures of Examples 1 to 6 ranged from 7.03% to 56.08%, with Example 6 having the highest drag reduction rate, reaching 56.08%. The drag reduction rates of Comparative Examples 2 and 3 were both below 7.03%.
[0062] The drag reduction rate is calculated by the following formula: C dst The drag coefficient of the blunt body of the drag reduction and heat protection structure is set, C d It is the drag coefficient of the blunt body of comparative example 1 without the drag reduction and heat protection structure.
[0063] It should be understood that the structures illustrated in the embodiments of the present invention do not constitute specific limitations on a hypersonic aircraft drag reduction and thermal protection structure. In other embodiments of the present invention, a hypersonic aircraft drag reduction and thermal protection structure may include more or fewer components than shown, or may combine or separate certain components, or employ a different component arrangement.
[0064] It should be noted that, in this article, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply the existence of any such actual relationship or order between these entities or operations. Moreover, the terms "comprises", "comprising" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprising a ..." do not exclude the presence of other identical factors in the process, method, article or device comprising the elements.
[0065] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.
Claims
1. A hypersonic vehicle drag reduction and heat protection structure, characterized in that: include: A drag reduction rod and a cooling device; the drag reduction rod is installed at the head of a blunt head, the cooling device is arranged inside the blunt head, and the blunt head is made of porous medium material; the cooling device is used to store and release coolant.
2. The hypersonic vehicle drag reduction and heat protection structure according to claim 1, characterized in that: The cooling device comprises a coolant storage device and a guide channel; the coolant storage device is used to store coolant or release coolant, and the guide channel is used to provide a transportation channel for the coolant so that the coolant flows out of the porous medium material through the guide channel.
3. The hypersonic vehicle drag reduction and heat protection structure according to claim 2, characterized in that: The coolant is at least one of liquid nitrogen, liquid helium, carbon dioxide, and hydrocarbon refrigerants.
4. The hypersonic vehicle drag reduction and heat protection structure according to claim 2, characterized in that: The guide channel is made of copper, aluminum, copper alloy, aluminum alloy or a composite material with temperature resistance and heat conductivity.
5. The hypersonic vehicle drag reduction and heat protection structure according to claim 1, characterized in that: The pore size of the porous medium material is in the micron level, and the porosity is 0.2-0.
7.
6. The hypersonic vehicle drag reduction and heat protection structure according to claim 1, characterized in that: The porous medium material is copper, aluminum, copper alloy, aluminum alloy or a composite material with temperature resistance and heat conductivity.
7. The hypersonic vehicle drag reduction and heat protection structure according to claim 1, characterized in that: The drag reducing rod is made of the porous medium material.
8. The hypersonic vehicle drag reduction and heat protection structure according to claim 1, characterized in that: The aspect ratio of the drag reducing rod is 0.5 to 2.
5.
9. The hypersonic vehicle drag reduction and heat protection structure according to any one of claims 2 to 8, characterized in that: A cavity is provided in the drag reduction rod, and a center line of the cavity coincides with a center line of the drag reduction rod.
10. The hypersonic vehicle drag reduction and heat protection structure according to claim 9, characterized in that: The cavity of the drag reducing rod is communicated with the flow guiding channel.