High-speed aircraft based on micro-scale tangential gas film and drag reduction and heat reduction design method thereof

Abstract

The application discloses a high-speed aircraft based on micro-scale tangential gas film and a drag-reducing and heat-reducing design method thereof. The high-speed aircraft based on micro-scale tangential gas film comprises a first gas film generator, wherein the first gas film generator is laid on a first heat protection position of a surface of the high-speed aircraft, the first gas film generator is provided with a first spray joint of a first height from the surface of the high-speed aircraft, the first gas film generator injects gaseous or liquid coolant into the first spray joint to form a gaseous film, and the effective cooling length of the gaseous film is a first length.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a high-speed aircraft based on a microscale tangential air film and its drag reduction and heat reduction design method. Background Technology

[0002] A hypersonic vehicle is a vehicle that flies at a speed greater than Mach 5. When a hypersonic vehicle flies at a hypersonic speed in the dense atmosphere, the airflow in the atmosphere will generate strong friction with the surface of the hypersonic vehicle. The kinetic energy lost by the airflow in the boundary layer of the hypersonic vehicle surface is converted into heat energy, which causes the temperature of the gas in the boundary layer of the hypersonic vehicle surface to rise.

[0003] However, the high temperatures within the boundary layer of a hypersonic vehicle will ablate its surface materials, reducing surface strength and structural integrity. Simultaneously, the ablation caused by these high temperatures within the boundary layer will alter the shape and texture of the hypersonic vehicle's surface, affecting its aerodynamic performance (including reduced lift and increased drag), flight performance, and fuel efficiency. Furthermore, for reusable hypersonic vehicles, the ablation caused by these high temperatures within the boundary layer will increase maintenance and repair costs and may pose a potential threat to the flight safety of the hypersonic vehicle's legal entity.

[0004] Therefore, how to implement safe, effective, and low-cost thermal protection measures on the surface of hypersonic vehicles is the technical problem that this invention aims to solve. Summary of the Invention

[0005] The purpose of this invention is to provide a high-speed aircraft based on a microscale tangential gas film and its drag reduction and heat reduction design method. By applying a gaseous film to the wall of the hypersonic aircraft, not only is heat reduction and drag reduction achieved on the surface of the hypersonic aircraft, but the outer surface of the hypersonic aircraft is also safely, efficiently, and cost-effectively thermally protected.

[0006] According to one aspect of the present invention, at least one embodiment provides a drag reduction and heat reduction design method, comprising: obtaining a thermal protection region on the surface of a high-speed aircraft based on a microscale tangential air film; and determining the type and number of air film generators arranged in the thermal protection region according to at least one effective cooling length of at least one air film generator.

[0007] According to another aspect of the present invention, at least one embodiment also provides a thermal protection device, comprising: a processor adapted to implement various instructions; and a memory adapted to store a plurality of instructions, said instructions being adapted to be loaded and executed by the processor: the drag reduction and heat reduction design method of the present invention.

[0008] According to another aspect of the present invention, at least one embodiment also provides a computer-readable non-volatile storage medium for storing computer program instructions, which, when executed by a computer, execute: the drag reduction and heat reduction design method of the present invention.

[0009] According to another aspect of the present invention, applying the drag reduction and heat reduction design method of the present invention, at least one embodiment of the present invention also provides a high-speed aircraft based on microscale tangential air film, comprising: a first air film generator, wherein the first air film generator is laid on a first thermal protection position on the surface of the high-speed aircraft, the first air film generator and the surface of the high-speed aircraft are provided with a first spray slit of a first height, the first air film generator injects gaseous or liquid coolant into the first spray slit to form a gaseous film, and the effective cooling length of the gaseous film is a first length.

[0010] This invention, through the aforementioned method, designs tangential nozzles of a certain thickness on the surface of a hypersonic vehicle and injects gaseous or liquid coolant into these nozzles to form a tangential gaseous film. This gaseous film elevates the boundary layer on the hypersonic vehicle's surface, effectively preventing direct friction between the high-speed main stream and the hypersonic vehicle's surface during flight, thus achieving cooling. Simultaneously, the friction between the high-speed main stream and the hypersonic vehicle's solid wall during flight is transformed into friction between the high-speed main stream and the low-speed gaseous film. Since the friction between gases is much less than the friction between a gas and a solid wall, applying a gaseous film to the hypersonic vehicle's surface also reduces drag, improving the hypersonic vehicle's fuel efficiency. Attached Figure Description

[0011] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0012] Figure 1 This is a schematic diagram of a thermal protection device according to an embodiment of the present invention;

[0013] Figure 2 This is a flowchart of the drag reduction and heat reduction design method according to an embodiment of the present invention;

[0014] Figure 3 This is a top view of the outer surface of a high-speed aircraft based on a microscale tangential air film, according to an embodiment of the present invention;

[0015] Figure 4This is a schematic diagram of the surface of a high-speed aircraft based on a microscale tangential air film with a tangential air model according to an embodiment of the present invention.

[0016] Figure 5 This is a schematic diagram of the gaseous thin film cooling principle according to an embodiment of the present invention. Detailed Implementation

[0017] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] Generally, thermal protection measures on the surface of hypersonic vehicles can be divided into passive thermal protection and active thermal protection. Passive thermal protection involves using high-temperature resistant and ablation-resistant materials to be applied to the surface of the hypersonic vehicle to reduce heat conduction and provide protection and insulation. Active thermal protection refers to using active mechanisms to control heat transfer on the surface of the hypersonic vehicle and reduce the degree of heating of materials to provide more effective thermal protection.

[0019] Passive thermal protection commonly includes: (1) applying thermal protection coatings, which are usually composed of ceramic or metal materials and can work stably in high-temperature environments; (2) installing heat-insulating corrugated sheets, whose internal structure is usually made of heat-insulating materials, which can reduce heat conduction and provide insulation while providing a certain structural strength. The inventors found that thermal protection coatings or heat-insulating corrugated sheets are usually made of high-density materials and are relatively heavy. If these materials are added to the surface of hypersonic vehicles, it will increase the total weight of the hypersonic vehicles and have a negative impact on the flight performance and fuel efficiency of the hypersonic vehicles. Thermal protection coatings or heat-insulating corrugated sheets are expensive, and adding these materials will increase manufacturing and maintenance costs. In addition, for reusable hypersonic vehicles, the thermal protection coatings or heat-insulating corrugated sheets installed on them are affected by environmental factors such as wind, sun, high temperature, and high-speed flight, and their durability will deteriorate, requiring regular inspection, maintenance and replacement.

[0020] Active thermal protection commonly employs the following methods: (1) perspiration cooling, which involves spraying cooling gas or liquid onto the surface of a hypersonic vehicle through a perforated array or breathable material, allowing it to absorb heat and thus reduce the surface temperature; and (2) convection cooling, which involves designing channels beneath the surface of the hypersonic vehicle to allow cooling gas or liquid to flow, carrying away heat from the hypersonic vehicle surface through convection heat transfer. The inventors have found that ensuring uniform cooling across the entire hot surface of the hypersonic vehicle is a challenge for perspiration cooling, as perspiration through a perforated array may lead to uneven surface temperature, thus affecting the effectiveness of thermal protection; and breathable materials are easily blocked by impurities generated from ablation in other parts or other contaminants, leading to cooling failure. The inventors discovered that for convective cooling, since the channels on the lower surface of a hypersonic vehicle cannot be arranged continuously, uniform cooling cannot be guaranteed. If there are too many channels, it will affect the structural strength of the vehicle surface. When the flight speed of a hypersonic vehicle is too high, that is, when the temperature of the outer surface of the hypersonic vehicle is too high, the effect of controlling the surface temperature of the hypersonic vehicle by convective heat transfer of the coolant is poor.

[0021] Based on in-depth research into thermal protection measures for hypersonic vehicles, at least one embodiment of the present invention provides a thermal protection device, such as... Figure 1 As shown, it includes: a processor 101, adapted to implement various instructions; and a memory 103, adapted to store multiple instructions, which are adapted to be loaded and executed by the processor 101: the drag reduction and heat reduction design method developed in this invention (or a thermal protection method for the surface of an aircraft, or a hypersonic drag reduction and heat reduction design method, or a high-speed aircraft drag reduction and heat reduction design method based on microscale tangential air film, which will be described in detail later in this paper). This high-speed aircraft can also be simply referred to as a hypersonic aircraft or a high-speed vehicle based on microscale tangential air film.

[0022] The processor 101 described above can be any applicable processor, such as a central processing unit, microprocessor, embedded processor, etc., and can adopt architectures such as x86 and ARM. The memory 103 described above can be any applicable storage device, such as a non-volatile storage device, including but not limited to magnetic storage devices, semiconductor storage devices, optical storage devices, etc., and can be arranged as a single storage device, a storage device array, or a distributed storage device. The embodiments of the present invention do not impose any limitations on these.

[0023] Furthermore, the present invention can also incorporate a computer-readable non-volatile storage medium within the thermal protection device. The embodiments of the present invention also provide at least one computer-readable non-volatile storage medium storing computer program instructions. When the computer executes the program instructions, it executes: the drag reduction and heat reduction design method developed in this invention (or a thermal protection method for aircraft surfaces, or a high-speed aircraft drag reduction and heat reduction design method based on microscale tangential air film, which will be described in detail later in this paper).

[0024] In the operating environment of the thermal protection device and / or computer-readable non-volatile storage medium described above in this invention, at least one embodiment of this invention also provides a drag reduction and heat dissipation design method, such as... Figure 2 As shown, it should be noted that the steps illustrated in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be performed in a different order than that shown here, and may include the following steps:

[0025] Step S202: Obtain the thermal protection area on the surface of a high-speed aircraft based on a microscale tangential air film;

[0026] Step S204: Determine the type and number of air film generators arranged in the thermal protection zone based on at least one effective cooling length of at least one air film generator.

[0027] This invention is not only applicable to the surfaces of high-speed vehicles with flat plate configurations, but also to various complex high-speed vehicle surfaces, such as curved surfaces (e.g., cylinders) and surfaces with curvature (e.g., spheres). By determining the type and number of gas film generators (i.e., gaseous film generators) required for the thermal protection area of ​​a hypersonic vehicle surface, the invention allows for the selection of thermal protection locations within the microscale tangential gas film-based surface for the placement of these gas film generators. These generators inject a very small mass flow rate of gaseous or liquid coolant into the inner layer of the hypersonic vehicle's boundary layer, thus achieving surface cooling and drag reduction. Furthermore, placing gas film generators on the surface of a hypersonic vehicle is a safe, effective, and low-cost thermal protection measure.

[0028] By applying the hypersonic drag reduction and heat reduction design method of the present invention, after laying at least one (assuming N, N≥1) gas film generator on the surface of a high-speed aircraft based on a microscale tangential gas film, the high-speed aircraft based on a microscale tangential gas film of the present invention can be formed. The gas film generator is a device that generates a gas film. At least one embodiment of the present invention also provides a high-speed aircraft based on a microscale tangential gas film, such as... Figure 3 As shown, it includes:

[0029] A first air film generator 301 is installed on a first thermal protection position on the surface of a high-speed aircraft. The first air film generator 301 and the surface of the high-speed aircraft are provided with a first spray slit at a first height. The first air film generator 301 injects gaseous or liquid coolant into the first spray slit to form a gaseous film. The effective cooling length of the gaseous film is a first length.

[0030] The second air film generator 303 is installed at a second thermal protection position on the surface of the high-speed aircraft. The second air film generator 303 is separated from the first air film generator 301 by a first length. The opening of the first spray slit faces the second air film generator 303. The second air film generator 303 and the surface of the high-speed aircraft are provided with a second spray slit at a second height. The second air film generator 303 injects gaseous or liquid coolant into the second spray slit to form a gaseous film. The effective cooling length of the gaseous film is the second length.

[0031] The third film coolant generator 305 is installed at the third thermal protection position on the surface of the high-speed aircraft. The third film coolant generator 305 is separated from the second film coolant generator 303 by a second length. The opening of the second spray slit faces the third film coolant generator 305. The third film coolant generator 305 and the surface of the high-speed aircraft are provided with a third spray slit at a third height. The third film coolant generator 305 injects gaseous or liquid coolant into the third spray slit to form a gaseous film. The effective cooling length of the gaseous film is the third length.

[0032] ...

[0033] The Nth air film generator 30 (2N-1) is installed at the Nth thermal protection position on the surface of the high-speed aircraft. The Nth air film generator 30 (2N-1) is separated from the N-1th air film generator 30 (2N-3) by a distance of N-1. The opening of the N-1th spray slit faces the Nth air film generator 30 (2N-1). The Nth air film generator 30 (2N-1) and the surface of the high-speed aircraft are provided with the Nth spray slit at the Nth height. The Nth air film generator 30 (2N-1) injects gaseous or liquid coolant into the Nth spray slit to form a gaseous film. The effective cooling length of the gaseous film is the Nth length.

[0034] This invention, through the aforementioned method, designs tangential nozzles of a certain thickness on the surface of a hypersonic vehicle and injects gaseous or liquid coolant into these nozzles to form a tangential gaseous film. This gaseous film elevates the boundary layer on the hypersonic vehicle's surface, effectively preventing direct friction between the high-speed main stream and the hypersonic vehicle's surface during flight, thus achieving cooling. Simultaneously, the friction between the high-speed main stream and the hypersonic vehicle's solid wall during flight is transformed into friction between the high-speed main stream and the low-speed gaseous film. Since the friction between gases is much less than the friction between a gas and a solid wall, applying a gaseous film to the hypersonic vehicle's surface also reduces drag, improving the hypersonic vehicle's fuel efficiency.

[0035] It should be noted that the first air film generator 301, the second air film generator 303, ..., the Nth air film generator 30 (2N-1) can be of the same type, meaning that the nozzle height and effective cooling length of multiple air film generators can be completely identical. If the first air film generator 301, the second air film generator 303, ..., the Nth air film generator 30 (2N-1) are of different types, then each type of air film generator can adaptively calculate its own nozzle height and effective cooling length by referring to the method / principle of calculating the nozzle height and effective cooling length of the first air film generator 301. Simultaneously, for each air film generator, such as... Figure 4 As shown, 1 is a gas film generator used to generate a gaseous film, 2 is a gaseous film, 3 is the wall of a high-speed aircraft based on a microscale tangential gas film, 4 is a pressure sensor, 5 is a pipeline (used to transport coolant), 6 is a control system, 7 is a solenoid valve (used to control the mass flow rate of coolant), and 8 is a coolant storage system (used to store coolant). The control system 6 controls the opening and closing degree of the solenoid valve 7 based on the pressure measured by the pressure sensor 4, thereby controlling the mass flow rate of coolant.

[0036] For example, the first film gas generator 301 obtains the first height of the first nozzle slit by: obtaining the first boundary layer at the first thermal protection position during flight, wherein the first boundary layer includes an inner layer and an outer layer, and the inner layer includes a troposphere and a viscous sublayer; determining the first height by the thickness of the inner layer or the thickness of the viscous sublayer, wherein the thickness of the inner layer or the thickness of the viscous sublayer is corrected by a combination of theoretical calculations, wind tunnel tests, and / or numerical simulations. The thickness of the inner layer is approximately 10% to 20% of the thickness of the first boundary layer, and the thickness of the inner layer is on the sub-millimeter scale; the thickness of the viscous sublayer is approximately 1% of the thickness of the first boundary layer, and the thickness of the viscous sublayer is on the micrometer scale.

[0037] As can be seen, the most crucial aspect of applying a film gas generator to the surface of a hypersonic vehicle is determining the nozzle height of the gas film generator. This nozzle height is determined by the height of the layering within the boundary layer at the thermal protection location (on the order of sub-millimeters or tens of micrometers). In other words, this nozzle can also be referred to as a tangential groove on the surface of the high-speed vehicle based on a microscale tangential gas film, which is less prone to blockage by upstream ablation impurities or other contaminants. For example: First, this invention obtains the boundary layer thickness (such as the inner layer thickness or the thickness of the viscous sublayer) at the location requiring thermal protection during flight based on boundary layer thickness calculation formulas, numerical simulations, or wind tunnel experiments; second, this invention further determines the nozzle height, i.e., on the order of sub-millimeters / micrometers, based on the inner layer thickness or the thickness of the viscous sublayer.

[0038] For example, the first air film generator 301 obtaining the first length may include: utilizing A first length is determined, which is corrected through a combination of theoretical calculations, wind tunnel tests, and / or numerical simulations. x represents the first length, h represents the first altitude, δ1 is the compressible mixing layer growth rate at the first thermal protection location during flight, δ2 is the laminar boundary layer thickness at the first thermal protection location during flight, r = u1 / u2, u1 is the external mainstream velocity at the first thermal protection location during flight, u2 is the gaseous film velocity ejected by the first gas film generator during flight, s = ρ1 / ρ2, ρ1 is the external mainstream density at the first thermal protection location during flight, ρ2 is the gaseous film density ejected by the first gas film generator during flight, v is the kinematic viscosity coefficient of the high-speed aircraft, u e The velocity of the gaseous film ejected by the first gas film generator.

[0039] It can be seen that applying a film cooling generator to the surface of a hypersonic vehicle requires determining the effective cooling length of the gaseous film formed by injecting gaseous or liquid coolant into the nozzle. In other words, this gaseous film is also called a tangential film on the surface of a high-speed vehicle based on a microscale tangential film. This tangential film can achieve cooling over a certain downstream distance (unlike existing sweating cooling technologies that only cool the sweating area), and consumes less cooling fluid mass flow rate. For example: First, the effective cooling length of this gaseous film is the abscissa of the intersection point of the lower boundary of the mixing layer and the boundary layer of the hypersonic vehicle in flight. The analysis is as follows: From Figure 5The principle diagram of gaseous film cooling shows that the gaseous film and the external mainstream shear each other to generate a mixing layer, which is approximately considered to start from the position where the two come into contact. Due to the presence of viscosity, the gaseous film generates a boundary layer on the surface of the hypersonic vehicle. When the boundary layer on the surface of the hypersonic vehicle intersects with the lower boundary of the mixing layer, the high-temperature mixed gas begins to contact the surface of the hypersonic vehicle. At this time, the surface temperature of the hypersonic vehicle rises, and the cooling of the gaseous film fails. Therefore, the abscissa of the intersection point of the lower boundary of the mixing layer and the boundary layer on the surface of the hypersonic vehicle can be regarded as the effective cooling length of the gaseous film. Secondly, the theoretical prediction of the effective cooling length of the gaseous film: (1) Clarify the development of the mixing layer thickness with the flow direction distance. Through a large number of experiments and numerical calculations, the empirical calculation formula of the incompressible mixing layer growth rate λ1 is determined. constant C δ ≈0.17, the above formula is only applicable to the calculation of the growth rate of the incompressible hybrid layer, while in reality the hybrid layer generated by the interaction between the hypersonic mainstream and the gaseous film has strong compressibility; (2) Clarify the calculation formula of the growth rate of the compressible hybrid layer. Given that under the same velocity ratio r and density ratio s, the growth rate λ2 of the compressible hybrid layer and the growth rate λ1 of the incompressible hybrid layer have the following relationship: in, a1 and a2 are the sound velocities of the mainstream and gaseous thin film, respectively. When Mc > 2, f(Mc) ≈ 0.2, so the growth rate of the compressible hybrid layer can be approximated as: The formula for calculating the thickness of the laminar boundary layer is as follows: (3) In summary, the equation set developed in this invention can be obtained, and the effective cooling length of the gaseous thin film can be calculated.

[0040] This invention, through the above-described method, rationally arranges spray slits on the wall of a hypersonic vehicle according to the effective cooling length of the gaseous film, and injects gaseous or liquid coolant into the inner layer of the wall boundary layer. In other words, the gaseous film is tangentially injected into the inner layer of the hypersonic vehicle wall boundary layer, thus applying a gaseous film to the wall of the hypersonic vehicle, forming a high-speed vehicle based on a microscale tangential gas film. This not only reduces heat and drag on the surface of the hypersonic vehicle, but also provides safe, efficient, and low-cost thermal protection for the outer surface of the hypersonic vehicle.

[0041] The present invention has been verified through relevant wind tunnel tests and numerical calculations, showing that it can reduce the surface temperature of the optical window and reduce the wall friction of the hypersonic vehicle, thus achieving the expected design goal and demonstrating technical feasibility.

[0042] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0043] It should be noted that when an element is referred to as being "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0044] As used herein, the term "and / or" placed between the first entity and the second entity means (1) the first entity, (2) the second entity, and (3) one of the first and second entities. Multiple entities listed with "and / or" should be interpreted in the same way, i.e., "one or more" of the entities connected. Other entities may exist, as appropriate, outside the entities specifically identified by the "and / or" clause, whether or not they are related to the specifically identified entities. Thus, as a non-restrictive example, when used in conjunction with open-ended language such as "including," a reference to "A and / or B" may in one specific instance refer only to A (including entities other than B, as appropriate); in another specific instance refer only to B (including entities other than A, as appropriate); and in yet another specific instance refer to both A and B (including other entities, as appropriate). Entities may refer to components, actions, structures, steps, operations, and values, etc.

[0045] As used herein, the phrase "at least one" in relation to a list of one or more entities should be understood to mean selecting at least one entity from any one or more entities in the list, but not necessarily including at least one entity from each or every entity specifically listed in the list, and does not exclude any combination of entities in the list. This definition also allows an entity to exist, as appropriate, rather than being specifically identified in the list of entities referred to by the phrase "at least one," whether or not it is related to those specifically identified entities. Thus, as a non-limiting example, "at least one of A and B" (or equivalently, "at least one of A or B" or equivalently "at least one of A and / or B") may, in one specific instance, mean at least one A, and as appropriate, include more than one A, while no B exists (and, as appropriate, include entities other than B); in another specific instance, at least one B, and as appropriate, include more than one B, while no A exists (and, as appropriate, include entities other than A); in yet another specific instance, at least one A, and as appropriate, include more than one A, and at least one B, and as appropriate, include more than one B (and, as appropriate, include other entities). In other words, the phrases "at least one," "one or more," and "and / or" are open expressions of union and separation in operation. For example, "at least one of A, B, and C," "at least one of A, B, or C," "one or more of A, B, and C," "one or more of A, B, or C," and "A, B, and / or C" can mean a single A, a single B, a single C, A and B together, A and C together, B and C together, A, B, and C together, and, as appropriate, any of the above combined with at least one other entity.

[0046] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A high speed aircraft based on microscale tangential gas film, wherein, According to at least one effective cooling length of at least one gas film generator, the type and quantity of gas film generators arranged on a thermal protection area of a high-speed vehicle surface are determined, characterized in that comprising: a first gas film generator, wherein the first gas film generator is laid on a first thermal protection position of the high-speed vehicle surface, the first gas film generator is provided with a first slot with a first height on the high-speed vehicle surface, the first gas film generator injects a gaseous or liquid coolant into the first slot to form a gaseous film, and the effective cooling length of the gaseous film is a first length; wherein the first length is determined by theoretical calculation, wind tunnel test and / or numerical simulation, determining a first length, wherein the first length is corrected by theoretical calculation, wind tunnel test and / or numerical simulation, denotes the first length, denotes the first height, is the growth rate of the compressible mixing layer at the first heat protection position in flight state, is the thickness of the laminar boundary layer at the first heat protection position in flight state, , is the velocity of the external main flow at the first heat protection position in flight state, is the velocity of the gaseous film jetted by the first gas film generator in flight state, , is the density of the external main flow at the first heat protection position in flight state, is the density of the gaseous film jetted by the first gas film generator in flight state, is the kinematic viscosity coefficient of the high-speed aircraft, u e is the velocity of the gaseous film jetted by the first gas film generator.

2. The microscale tangential gas film based high speed vehicle of claim 1, wherein, the first height is obtained by the following method: obtaining a first boundary layer at the first thermal protection position in a flight state, wherein the first boundary layer includes an inner layer and an outer layer, and the inner layer includes a logarithmic layer and a viscous bottom layer; determining the first height by the thickness of the inner layer or the thickness of the viscous bottom layer, wherein the thickness of the inner layer or the thickness of the viscous bottom layer is obtained by theoretical calculation, wind tunnel test and / or numerical simulation and is corrected.

3. The microscale tangential gas film based high speed vehicle of claim 2, wherein, The thickness of the inner layer is 10% to 20% of the thickness of the first boundary layer, the thickness of the inner layer is sub-millimeter level, the thickness of the viscous bottom layer is 1% of the thickness of the first boundary layer, and the thickness of the viscous bottom layer is micrometer level.

4. The microscale tangential gas film based high speed vehicle of claim 1, wherein, Further comprising: a second gas film generator, wherein the second gas film generator is laid on a second thermal protection position of the high-speed vehicle surface, the second gas film generator is spaced apart from the first gas film generator by a first length, and the opening of the first slot faces the second gas film generator.

5. The microscale tangential gas film based high speed vehicle of claim 4, wherein, The second gas film generator is provided with a second slot with a second height on the high-speed vehicle surface, the second gas film generator injects a gaseous or liquid coolant into the second slot to form a gaseous film, and the effective cooling length of the gaseous film is a second length.

6. The microscale tangential gas film based high speed vehicle of claim 5, wherein, Further comprising: a third gas film generator, wherein the third gas film generator is laid on a third thermal protection position of the high-speed vehicle surface, the third gas film generator is spaced apart from the second gas film generator by a second length, and the opening of the second slot faces the third gas film generator.

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