Control surface cooling heat protection and steering effect enhancement integrated design method

Abstract

The invention relates to the related technical field of high-speed aircrafts, in particular to a control surface cooling heat protection and steerage enhancement integrated design method. According to the method, a pump is used for enabling a working medium in a storage box to flow in a channel of a rudder shaft and a control surface to take away heat of the rudder shaft and the control surface; the working medium absorbing the heat is sprayed out from small holes in the front edge and the top end of the rudder to form a layer of gas film on the outer surface of the rudder to separate the rudder from high-temperature gas; meanwhile, the sprayed working medium changes the flow field structure around the front edge and the top end of the control surface, and a pressure enhancement area is formed on the surface of the control surface, so that the effective stress load of the control surface is increased, and the control effect of the control rudder is improved. According to the method, an autonomous cooling thermal protection mode is adopted, the working medium is sprayed out from the small holes in the front edge and the top end of the control surface after cooling the control surface and the rudder shaft, temperature control of the control surface in a long-endurance flight task is guaranteed, the problems of thermal protection, thermal deformation and the like in a high-heat-flow area are solved, and the control effect of the control rudder is improved.

Description

Technical Field

[0001] The present invention relates to the technical field related to high-speed aircraft, and in particular to an integrated design method for rudder surface cooling, heat protection and rudder effect enhancement. Background Art

[0002] Flying faster has always been the main theme of human flight development. During high-speed flight, the air at the leading edge of the aircraft is compressed, causing the air temperature to rise sharply, and the heat energy is quickly transferred to the surface of the object, causing the temperature of the aircraft to rise. The control rudder is usually arranged at the tail end of the aircraft. It provides a deflection torque for the aircraft by rotating, thereby correcting the flight direction of the aircraft. It is an important component of the aircraft. The heat protection design of the rudder must not only keep the rudder surface temperature within the allowable temperature range of the material, but also reduce the heat transfer inward to ensure the ambient temperature of the precision equipment inside the aircraft. Generally speaking, the larger the area of ​​the rudder surface, the stronger the control ability of the aircraft. However, the use of a large rudder surface will significantly increase the weight of the aircraft and increase the difficulty of the thermal protection design of the aircraft rudder surface. Therefore, the design of the rudder surface requires comprehensive consideration from many aspects.

[0003] In order to prevent the control rudder of a high-speed aircraft from reducing its reliability due to heat accumulation in a service environment, the traditional design adopts a heat protection layer + load-bearing structure. The silicon-based / carbon-based heat protection layer decomposes and sublimates in a high-density heat flow to absorb a large amount of heat, thereby ensuring that the load-bearing structure of the rudder surface works within a reliable temperature range. The design of the heat protection layer + load-bearing structure is complex. The loss of the heat protection layer will cause the shape of the control rudder to change. There may also be a thermal matching problem between the heat protection layer and the control rudder due to debonding in a high-temperature environment. In addition, passive ablative heat protection is difficult to achieve reusability. Summary of the invention

[0004] In view of this, the purpose of the present invention is to propose an integrated design method for cooling and heat protection of rudder surfaces and enhancing rudder efficiency. This design method adopts an autonomous cooling method, and the working fluid cools the rudder surface and rudder shaft and then sprays out from the small holes on the front edge and top of the rudder surface, which ensures the temperature control of the rudder surface during long-duration flight missions, solves the problems of thermal protection and thermal deformation in high heat flux areas, and improves the control rudder efficiency.

[0005] The present invention proposes an integrated design method for cooling, heat protection and enhancing rudder efficiency of a rudder surface, comprising: a rudder shaft 9 is connected to a rudder surface 1 after passing through an aircraft shell 5; a channel 2 passes through the rudder shaft 9 and is arranged at a certain distance in the rudder surface 1 to serve as a flow channel for a working medium 7; a plurality of small holes 3 are evenly arranged at the leading edge and the top of the rudder surface 1, the axis of each small hole 3 is at a certain angle to the leading edge and the top of the rudder surface 1, the angle being between 0° and 180°, the small hole 3 is connected to the internal channel 2 of the rudder surface 1 to serve as an outlet for ejecting the working medium 7; a storage box 6 is arranged in the aircraft to store the working medium 7; a pump 8 is provided It is arranged on the channel 2 connected to the storage box 6; the pump 8 adjusts the flow rate of the working medium 7 so that the working medium 7 in the storage box 6 flows along the channel 2 to the rudder shaft 9 and the rudder surface 1, taking away the heat of the rudder shaft 9 and the rudder surface 1; the working medium 7 that absorbs the excessive heat is ejected from the small holes 3 at the leading edge and the top of the rudder surface 1, forming a layer of air film on the outer surface of the rudder surface 1 to separate the rudder surface 1 from the high-temperature gas; at the same time, the ejected working medium forms an airflow interference area 10 in front of the leading edge and above the top of the rudder surface 1, changes the flow field structure around the leading edge and the top of the rudder surface, and forms a pressure enhancement area 11 on the rudder surface, thereby increasing the effective force load on the rudder surface and improving the control effect of the rudder.

[0006] The rudder surface is connected to the rudder shaft, and is arranged vertically outside the aircraft. It is a heated body for aerodynamic heating, and has a channel inside. The rudder surface has small holes at a certain distance distributed on the front edge and top of the rudder surface.

[0007] The rudder shaft passes through the aircraft shell and is connected to the rudder surface to bear / transmit force and heat;

[0008] The channel is designed as an integral part of the rudder surface and the rudder shaft, passes through the rudder shaft, and is arranged at a certain distance inside the rudder surface. As a flow channel for the working medium, the channel spacing can be appropriately increased or decreased according to the heating conditions of the rudder surface. The channel cross-sectional shape is usually a regular shape such as a circle, triangle, quadrilateral or ellipse; when the channel cross-sectional shape is a triangle or a quadrilateral, the adjacent surfaces of the channel are chamfered or non-chamfered.

[0009] The small holes are designed as a whole with the rudder surface, distributed on the front edge and top of the rudder surface, and are connected to the internal channel of the rudder surface, serving as the outlet for the working fluid to be ejected. The axis of the small holes forms a certain angle with the front edge and top of the rudder surface, and the angle is between 0° and 180°, which can be adjusted according to actual needs. The number, aperture and spacing of the small holes are comprehensively considered based on the rudder surface and the thermal environment. The shape of the small holes 3 is usually a regular shape such as a circle, triangle, quadrilateral or ellipse;

[0010] The storage box is inside the aircraft and is used to store working fluids. It can be designed according to the effective space inside the aircraft.

[0011] The pump is used to provide working medium flow power, transporting the working medium from the storage box along the channel to the rudder shaft and the rudder surface, and can adjust the working medium flow rate, and the temperature of the rudder surface can be controlled by adjusting the flow rate;

[0012] The working fluid is a substance that can take away the heat from the heated parts. After the rudder shaft and the rudder surface fully absorb the heat, it is finally ejected from the small holes at the front edge and the top of the rudder surface, forming an air film on the outer surface of the rudder to separate the rudder surface from the high-temperature gas; at the same time, the ejected working fluid changes the flow field structure around the front edge and the top of the rudder surface, forming a pressure enhancement area on the rudder surface, thereby increasing the effective force load on the rudder surface and improving the control effect of the rudder.

[0013] The core of the present invention is to propose an integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement, which adopts an autonomous cooling thermal protection method. After the working fluid cools the rudder surface and rudder shaft, it is sprayed out from the small holes on the front edge and top of the rudder surface, ensuring the temperature control of the rudder surface during long-duration flight missions, solving the problems of thermal protection and thermal deformation in high heat flow areas, and improving the control rudder efficiency.

[0014] The technical method principle of the present invention is as follows:

[0015] First, in the incoming flow, the rudder surface is aerodynamically heated, and the heat gradually accumulates;

[0016] Secondly, the pump works, and the working fluid in the storage tank flows in the channels of the rudder shaft and the rudder surface, taking away the heat of the rudder shaft and the rudder surface, controlling the temperature of the rudder surface and reducing the heat transfer to the interior of the aircraft;

[0017] Finally, the working fluid that absorbs superheat is ejected from the small holes at the front edge and top of the rudder surface, forming an air film on the outer surface of the rudder, separating the rudder surface from the high-temperature gas; at the same time, the ejected working fluid changes the flow field structure around the front edge and top of the rudder surface, forming a pressure enhancement area on the rudder surface, thereby increasing the effective force load on the rudder surface and improving the control efficiency of the rudder.

[0018] The beneficial effects of the present invention are as follows: the present invention provides an integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement, which has a simple structure and adopts an autonomous cooling thermal protection method. After the working fluid cools the rudder surface and the rudder shaft, it is sprayed out from the small holes on the front edge and top of the rudder surface, thereby ensuring the temperature control of the rudder surface during long-duration flight missions, solving the problems of thermal protection and thermal deformation in high heat flow areas, and improving the control rudder efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of an integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement provided by an embodiment of the present invention.

[0020] Figure 2 It is a top view of a rudder surface according to an integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement provided by an embodiment of the present invention.

[0021] Figure 3 It is a schematic diagram of a rudder effect enhancement method for an integrated design of rudder surface cooling, heat protection and rudder effect enhancement provided by an embodiment of the present invention.

[0022] In the figure: 1-rudder surface, 2-channel, 3-small hole, 4-incoming flow, 5-outer casing, 6-storage tank, 7-working fluid, 8-pump, 9-rudder shaft, 10-aerodynamic interference area, 11-pressure enhancement area. DETAILED DESCRIPTION

[0023] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0024] The present invention relates to the technical field related to high-speed aircraft, and specifically introduces a design method for integrated cooling, heat protection and rudder efficiency enhancement of rudder surfaces. The temperature control of the aircraft rudder surface is achieved by adopting an autonomous cooling heat protection method and making full use of the working fluid that absorbs heat, solving the problems of heat protection and thermal deformation in high heat flux areas, and improving the rudder efficiency of the control rudder.

[0025] Arrangement as Figure 1 and Figure 2 As shown, specifically, the rudder surface 1 is connected to the rudder shaft 9, and the rudder surface 1 is vertically arranged outside the aircraft, and is a heated body for aerodynamic heating, and is provided with a channel 2 inside, and small holes 3 are evenly distributed at a certain distance on the leading edge and the top of the rudder surface 1;

[0026] Specifically, after the rudder shaft 9 passes through the aircraft shell 5, it is connected to the rudder surface 1 to play the role of bearing / transmitting force and heat;

[0027] Specifically, the channel 2 is designed as an integral unit with the rudder surface 1 and the rudder shaft 9. The channel 2 passes through the rudder shaft 9 and is arranged at a certain distance in the rudder surface 1 as a flow channel for the working medium 7. The spacing between the channels 2 can be appropriately increased or decreased according to the heating conditions of the rudder surface. The cross-sectional shape of the channel 2 is usually a regular shape such as a circle, triangle, quadrilateral or ellipse. When the cross-sectional shape of the channel is a triangle or a quadrilateral, the adjacent surfaces of the channel are chamfered or non-chamfered.

[0028] Specifically, the small holes 3 are designed as a whole with the rudder surface 1, and are distributed at the leading edge and the top of the rudder surface 1. The axis of each small hole 3 forms a certain angle with the leading edge and the top of the rudder surface 1, and the angle is between 0° and 180°. The small holes 3 are connected to the internal channel 2 of the rudder surface 1, and serve as the outlet for the working medium 7 to be ejected. The number, diameter and spacing of the small holes 3 are comprehensively considered based on the rudder surface 1 and the thermal environment. The shape of the small holes 3 is usually a regular shape such as a circle, a triangle, a quadrilateral or an ellipse.

[0029] Specifically, the storage box 6 is arranged in the aircraft to store the working medium 7, and can also be designed according to the effective space in the aircraft;

[0030] Specifically, the pump 8 is used to provide the working medium 7 with flow power, so that the working medium 7 flows from the storage box 6 along the channel 2 to the rudder shaft 9 and the rudder surface 1, and can adjust the flow of the working medium 7, and the temperature of the rudder surface 1 can be controlled by adjusting the flow;

[0031] Specifically, the working medium 7 is a substance that can take away the heat from the heated part;

[0032] For details, see Figure 1 and Figure 3 , the principles of cooling, heat protection and rudder efficiency enhancement are as follows:

[0033] Under flight conditions, the rudder surface 1 accumulates heat under the action of the incoming flow 4; the pump 8 adjusts the flow rate of the working medium 7, so that the working medium 7 in the storage box 6 flows along the channel 2 to the rudder shaft 9 and the rudder surface 1, taking away the heat of the rudder shaft 9 and the rudder surface 1, controlling the temperature of the rudder surface 1, and reducing the heat transfer to the interior of the aircraft; finally, the working medium 7 that has absorbed the excess heat is ejected from the small holes 3 at the leading edge and the top of the rudder surface 1, forming a layer of air film on the outer surface of the rudder surface 1, isolating the rudder surface 1 from the high-temperature gas; at the same time, the ejected working medium forms an airflow interference zone 10 in front of the leading edge and above the top of the rudder surface 1, changing the flow field structure around the leading edge and the top of the rudder surface, and forming a pressure enhancement zone 11 on the rudder surface, thereby increasing the effective force load on the rudder surface and improving the control rudder effect.

[0034] The rudder force can be obtained by integrating the pressure on the rudder surface:

[0035]

[0036] Where F is the rudder force (N);

[0037] P is the pressure on the rudder surface (Pa);

[0038] S is the rudder surface area (m 2 ).

[0039] It can be seen from the formula that when the pressure on the rudder surface increases, the rudder force under the same rudder surface increases, thereby improving the control rudder efficiency.

[0040] An integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement provided by an embodiment of the present invention solves the problems of thermal protection and thermal deformation in high heat flux areas, and adopts an autonomous cooling method to ensure the temperature control of the rudder surface during long-duration flight missions. At the same time, a rudder efficiency enhancement area is formed by spraying the working fluid from the small holes on the front edge and top of the rudder surface, thereby improving the control rudder efficiency.

[0041] The above examples are only used to illustrate the technical method of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the best embodiment, a person skilled in the art should understand that the technical method of the present invention can still be modified or replaced by equivalents, and these modifications or equivalent replacements cannot cause the modified technical method to deviate from the spirit and scope of the technical method of the present invention.

Claims

1. A method for integrated design of rudder surface cooling, heat protection and rudder efficiency enhancement, characterized in that: include: The channel 2 passes through the rudder shaft 9 and is arranged at a certain distance in the rudder surface 1 to serve as a flow channel for the working medium 7; A plurality of small holes 3 are evenly arranged at the leading edge and the top of the rudder surface 1, the axis of each small hole 3 forms a certain angle with the leading edge and the top of the rudder surface 1, the angle being between 0° and 180°, the small hole 3 is connected with the internal channel 2 of the rudder surface 1, and serves as an outlet for the ejection of the working fluid 7; a storage box 6 is arranged in the aircraft, and is used for storing the working fluid 7; a pump 8 is arranged on the channel 2 connected to the storage box 6; the pump 8 adjusts the flow rate of the working fluid 7, so that the working fluid 7 in the storage box 6 flows along the channel 2 to the rudder shaft 9 and the rudder surface 1, and takes away the heat of the rudder shaft 9 and the rudder surface 1; the working fluid 7 that absorbs the overheat is ejected from the small holes 3 at the leading edge and the top of the rudder surface 1, and forms a layer of air film on the outer surface of the rudder surface 1, which separates the rudder surface 1 from the high-temperature gas.

2. The integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement according to claim 1, characterized in that: The storage box 6 can be designed according to the shape of the effective space in the aircraft.

3. The integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement according to claim 1, characterized in that: The number, diameter and spacing of the small holes are considered comprehensively based on the rudder surface and thermal environment.

4. The integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement according to claim 1, characterized in that: The cross-sectional shape of the channel is a regular circular, triangular, quadrilateral or elliptical shape.

5. The integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement as claimed in claim 4, characterized in that: When the cross-sectional shape of the channel is a triangle or a quadrilateral, adjacent surfaces of the channel are designed with chamfers or without chamfers.

6. The integrated design method for rudder surface cooling, heat protection and rudder efficiency enhancement as claimed in claim 1, characterized in that: The shape of the small hole is regular, circular, triangular, quadrilateral or elliptical.

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