An airfoil leading edge for an aircraft and an aircraft

Abstract

The application discloses an air wing leading edge for an aircraft and the aircraft, and relates to the technical field of aircrafts, which comprises an air wing leading edge body, the cross-sectional shape of which is parallelogram, the leeward side of the air wing leading edge body is used for being connected with an air wing, one of the two sides adjacent to the leeward side is a slight chord, the other side is a root chord, the length of the slight chord and the root chord is smaller than the length of the leeward side, the windward surface of the slight chord is determined according to a slight chord front end curve, and the windward surface of the root chord is determined according to a root chord front end curve. Since the windward surface of the slight chord is determined according to the slight chord front end curve, and the windward surface of the root chord is determined according to the root chord front end curve, hot air flow can quickly pass through the air wing leading edge body, the time of aerodynamic heat and leading edge heat exchange is reduced, the influence of the hot air flow on the air wing leading edge body is reduced, and the problem that the air wing is damaged due to poor cooling effect in the prior art is solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to an air wing leading edge for an aircraft and the aircraft. BACKGROUND

[0002] When a hypersonic aircraft flies at supersonic speed in the atmosphere, the severe aerodynamic heating can cause the temperature of the air wing / rudder to rise sharply, especially the leading edge, which has an extremely harsh thermal environment. The resulting thermal barrier problem may cause the entire rudder to lose stability, affecting the safety of the entire flight system.

[0003] Thermal protection technology can be divided into three categories: 1. Passive thermal protection; 2. Semi-passive thermal protection; 3. Active thermal protection. First, passive thermal protection technology mainly protects aircraft by absorbing, radiating heat to the surrounding environment, and isolating heat transfer. However, the thermal protection performance of this technology is limited by the temperature resistance of the material, making it difficult to meet the needs of higher flight speeds and higher heat flux densities. Second, semi-passive thermal protection technology uses the latent heat of phase change of the working material and the sensible heat of temperature rise to absorb or transfer aerodynamic heat to a low-temperature area. This technology is limited by the working material and may change the aerodynamic shape of the aircraft. Finally, active thermal protection technology uses external gas or fuel as a coolant to cover the wall surface to be protected or through the cooling channel inside the wall surface to be protected, reducing or removing the aerodynamic heating received by the wall surface.

[0004] In the prior art, the leading edge of the rudder / air wing uses ablation-type quartz fiber composite materials or silicon carbide ceramic matrix composite materials, and then uses thermal protection technology to cool the leading edge, which may cause damage to the air wing due to poor cooling effect. SUMMARY

[0005] In view of the defects in the prior art, the purpose of the present application is to provide an air wing leading edge for an aircraft and an aircraft, which can solve the problem of damage to the air wing due to poor cooling effect caused by the use of ablation-type quartz fiber composite materials or silicon carbide ceramic matrix composite materials for the leading edge of the rudder / air wing and then cooling the leading edge by thermal protection technology.

[0006] To achieve the above purpose, the technical solution adopted by the present application is:

[0007] On the one hand, the present application provides an air wing leading edge for an aircraft, which comprises:

[0008] An airfoil leading edge body has a parallelogram cross-sectional shape, a leeward edge of the airfoil leading edge body is used to connect with an airfoil, one of the two edges adjacent to the leeward edge is a chord, and the other is a root chord, the lengths of the chord and the root chord are both less than the length of the leeward edge, the windward surface of the chord is determined according to a chord leading end curve, and the windward surface of the root chord is determined according to a root chord leading end curve.

[0009] On the basis of the above technical solutions,

[0010] In some optional solutions, the chord leading end curve is: wherein x is the horizontal coordinate of any point on the chord leading end curve, y is the vertical coordinate of any point on the chord leading end curve, t is the parameter variable of the chord leading end curve, k1 is the first thickness coefficient of the chord, and k2 is the second thickness coefficient of the chord.

[0011] In some optional solutions, the value range of k1 is 1.2-4, and the value of k2 is 1-4 times the value of k1.

[0012] In some optional solutions, the root chord leading end curve is: wherein x is the horizontal coordinate of any point on the root chord leading end curve, y is the vertical coordinate of any point on the root chord leading end curve, t is the parameter variable of the root chord leading end curve, k3 is the first thickness coefficient of the root chord, and k4 is the second thickness coefficient of the root chord.

[0013] In some optional solutions, the value of k3 is 1-5 times the value of k1, and the value of k4 is 1-4 times the value of k3.

[0014] In some optional solutions, a cooling flow channel is arranged in the airfoil leading edge body, and a cooling material is arranged in the cooling flow channel to cool the airfoil leading edge body.

[0015] In some optional solutions, the shape of the cooling flow channel is S-shaped, the diameter of the cooling flow channel is 2-8 mm, and the circular arc radius is 10-30 mm.

[0016] In some optional solutions, a phase change material is arranged in the airfoil leading edge body, and the phase change material is used to cool the airfoil leading edge body.

[0017] In some optional solutions, the airfoil leading edge body is made of titanium alloy, alloy steel, high-temperature alloy, and quartz fiber resin matrix composite material.

[0018] In another aspect, the application further provides a flying vehicle comprising the above-mentioned airfoil leading edge for a flying vehicle.

[0019] Compared with the prior art, the air wing leading edge for the aircraft has the advantages that:

[0020] In the use of the air wing leading edge for the aircraft, the air wing leading edge body section is a parallelogram, the leeward edge of the air wing leading edge body is used to connect with the air wing, the length of the chord and the root chord is less than the length of the leeward edge, the windward surface of the chord is determined according to the chord front curve, and the windward surface of the root chord is determined according to the root chord front curve. Since the windward surface of the chord is determined according to the chord front curve, and the windward surface of the root chord is determined according to the root chord front curve, the hot gas flow quickly passes through the air wing leading edge body, the time of aerodynamic heat exchange with the leading edge is reduced, the influence of the hot gas flow on the air wing leading edge body is reduced, and the problem that the ablation type quartz fiber composite material or the silicon carbide ceramic matrix composite material is used for the leading edge of the rudder / air wing in the prior art, and then the leading edge is cooled through the heat protection technology, and the air wing is damaged due to the poor cooling effect is solved. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0022] Figure 1 The figure is a cross-sectional structure schematic diagram of an embodiment of the air wing leading edge for the aircraft of the present application.

[0023] Figure 2 The figure is a top view structure schematic diagram of an embodiment of the air wing leading edge for the aircraft of the present application.

[0024] Figure 3 The figure is a structure schematic diagram of an embodiment of the air wing leading edge for the aircraft of the present application.

[0025] In the figure: 1, air wing leading edge body; 11, chord; 12, root chord; 2, cooling flow channel; 3, phase change material; 4, sealing cover plate; 5, mounting surface; 6, first connecting hole; 7, second connecting hole. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the present application.

[0027] Embodiments of an airfoil leading edge for an aircraft and an aircraft are described in further detail below with reference to the accompanying drawings.

[0028] As shown in Figure 1 and Figure 2 , in one aspect, the present application provides an airfoil leading edge for an aircraft, comprising:

[0029] an airfoil leading edge body 1, a cross-sectional shape of the airfoil leading edge body 1 is a parallelogram, a leeward edge of the airfoil leading edge body 1 is used to connect with an airfoil, one of the two edges adjacent to the leeward edge is a chord 11, and the other is a root chord 12, lengths of the chord 11 and the root chord 12 are both less than a length of the leeward edge, a windward surface of the chord 11 is determined according to a chord leading end curve, and a windward surface of the root chord 12 is determined according to a root chord leading end curve.

[0030] In use of the airfoil leading edge for an aircraft, the cross section of the airfoil leading edge body 1 is set as a parallelogram, the leeward edge of the airfoil leading edge body 1 is used to connect with the airfoil, lengths of the chord 11 and the root chord 12 are both less than the length of the leeward edge, the windward surface of the chord 11 is determined according to the chord leading end curve, and the windward surface of the root chord 12 is determined according to the root chord leading end curve. Since the windward surface of the chord 11 is determined according to the chord leading end curve, and the windward surface of the root chord 12 is determined according to the root chord leading end curve, the hot airflow passes through the airfoil leading edge body 1 quickly, the time of heat exchange between the aerodynamic heat and the leading edge is reduced, the influence of the hot airflow on the airfoil leading edge body 1 is reduced, and the problem that the existing art uses the ablation type quartz fiber composite material or the silicon carbide ceramic matrix composite material for the rudder / wing leading edge, and then cools the leading edge through the heat protection technology, and the airfoil may be damaged due to the poor cooling effect is solved.

[0031] In this example, an included angle between the leeward edge and a flight direction of the aircraft is an acute angle.

[0032] In some optional embodiments, the chord leading end curve is: wherein x is a horizontal coordinate of any point on the chord leading end curve, y is a vertical coordinate of any point on the chord leading end curve, t is a parameter variable of the chord leading end curve, k1 is a first thickness coefficient of the chord 11, and k2 is a second thickness coefficient of the chord 11.

[0033] In this example, the chord leading end curve is: wherein x and y are horizontal and vertical coordinates of any point on the chord leading end curve, t is a parameter variable of the chord leading end curve, k1 and k2 increase with the thickness of the chord 11, t takes a plurality of different numbers, the horizontal and vertical coordinates of a plurality of points can be obtained, and then the chord leading end curve is connected, when the windward surface of the chord 11 is determined according to the chord leading end curve, the hot airflow passes through the airfoil leading edge body 1 quickly, the time of heat exchange between the aerodynamic heat and the leading edge is reduced, and the influence of the hot airflow on the airfoil leading edge body 1 is reduced.

[0034] In some optional embodiments, k1 takes the value of 1.2-4, and k2 is 1-4 times the value of k1.

[0035] In this embodiment, the value of k1 is limited to 1.2-4, and the value of k2 is 1-4 times the value of k1. This can minimize the time that the hot airflow passes through the leading edge body 1 of the air wing and reduce the impact of the hot airflow on the leading edge body 1 of the air wing as much as possible.

[0036] In some optional embodiments, the root chord front end curve is: Where x is the abscissa of any point on the front curve of the root chord, y is the ordinate of any point on the front curve of the root chord, t is the parameter of the front curve of the root chord, k3 is the first thickness coefficient of root chord 12, and k4 is the second thickness coefficient of root chord 12.

[0037] In this embodiment, x and y are the horizontal and vertical coordinates of any point on the root chord leading edge curve, t is the parameter of the root chord leading edge curve, k3 is the first thickness coefficient of root chord 12, k4 is the second thickness coefficient of root chord 12, k3 and k4 increase as the thickness of root chord 12 increases, and t takes multiple different values ​​to obtain the horizontal and vertical coordinates of multiple points, which are then connected to form the root chord leading edge curve. When the windward surface of root chord 12 is determined by the root chord leading edge curve, the hot airflow can pass through the air wing leading edge body 1 quickly, reducing the time for aerodynamic heat exchange with the leading edge heat and reducing the impact of hot airflow on the air wing leading edge body 1.

[0038] In some alternative embodiments, the value of k3 is 1 to 5 times the value of k1, and the value of k4 is 1 to 4 times the value of k3.

[0039] In this embodiment, the value of k3 is 1-5 times the value of k1, and the value of k4 is 1-4 times the value of k3. This can minimize the time that the hot airflow passes through the leading edge body 1 of the air wing and reduce the impact of the hot airflow on the leading edge body 1 of the air wing as much as possible.

[0040] like Figure 1 As shown, in some optional embodiments, the air wing leading edge body 1 is provided with a cooling channel 2, and the cooling channel 2 is provided with a cooling material for cooling the air wing leading edge body 1.

[0041] In this embodiment, a cooling channel 2 is provided inside the air wing leading edge body 1, and a cooling material is provided inside the cooling channel 2 to cool the air wing leading edge body 1. Active thermal protection technology is adopted, using external gas as a coolant. The coolant is passed through the cooling channel inside the wall to be protected to reduce or remove the aerodynamic heating of the wall, improve the cooling effect, and reduce the impact of hot airflow on the air wing leading edge body 1.

[0042] like Figure 1 As shown, in some optional embodiments, the cooling channel 2 is S-shaped, with a diameter of 2-8 mm and an arc radius of 10-30 mm.

[0043] In this embodiment, the cooling channel 2 is S-shaped, with a diameter of 2-8mm and an arc radius of 10-30mm. This can increase the cooling area of ​​the cooling channel 2 on the air wing leading edge body 1, improve the cooling effect, and reduce the impact of hot airflow on the air wing leading edge body 1.

[0044] like Figure 1 and Figure 3 As shown, in some optional embodiments, a phase change material 3 is provided in the air wing leading edge body 1, which is used to cool the air wing leading edge body 1.

[0045] In this embodiment, a phase change material 3 is provided in the air wing leading edge body 1. The phase change material 3 is used to cool the air wing leading edge body 1. A semi-passive thermal protection technology is adopted, which utilizes the latent heat of the phase change of the phase change material 3 and the sensible heat of the temperature rise to absorb or transfer aerodynamic heat to the low temperature region, thereby improving the cooling effect and reducing the impact of hot airflow on the air wing leading edge body 1.

[0046] In this example, phase change material 3 is paraffin, stearic acid, or n-tetradecyl alcohol.

[0047] In this example, the airfoil leading edge body 1 includes a mounting surface 5 and a sealing cover 4. The mounting surface 5 is used to house the cooling channel 2 and the phase change material 3. The sealing cover 4 covers the mounting surface 5 and is detachably connected to it, allowing for easy replacement of the phase change material 3. The mounting surface 5 has multiple first connection holes 6, and the sealing cover 4 has second connection holes 7 corresponding to the first connection holes 6. Bolts pass through the corresponding first connection holes 6 and second connection holes 7, and are used to connect the sealing cover 4, the mounting surface 5, and the airfoil. The sealing cover 4 is made of aluminum alloy, titanium alloy, alloy steel, or high-temperature alloy.

[0048] In some alternative embodiments, the airfoil leading edge body 1 is made of titanium alloy, alloy steel, high-temperature alloy and quartz fiber resin matrix composite material.

[0049] In this embodiment, the air wing leading edge body 1 is made of titanium alloy, alloy steel, high-temperature alloy and quartz fiber resin matrix composite material to improve the heat resistance of the air wing leading edge body 1 and improve the resistance of the air wing leading edge body 1 to the influence of hot airflow.

[0050] like Figure 1 and Figure 2 As shown, on the other hand, this application also provides an aircraft that includes the aforementioned air wing leading edge for an aircraft.

[0051] In use of the air wing leading edge for aircraft, the air wing leading edge body 1 is set as a parallelogram, the leeward side of the air wing leading edge body 1 is used to connect with the air wing, the length of the chord 11 and the root chord 12 are both less than the length of the leeward side, the windward surface of the chord 11 is determined according to the chord front curve, and the windward surface of the root chord 12 is determined according to the root chord front curve. Since the windward surface of the chord 11 is determined according to the chord front curve, and the windward surface of the root chord 12 is determined according to the root chord front curve, the hot gas flow quickly passes through the air wing leading edge body 1, the time of aerodynamic heat and leading edge heat exchange is reduced, the influence of the hot gas flow on the air wing leading edge body 1 is reduced, and the problem that the existing technology uses ablation type quartz fiber composite material or silicon carbide ceramic matrix composite material for the rudder / air wing leading edge, and then cools the leading edge through heat protection technology, which may cause damage to the air wing due to poor cooling effect, is solved.

[0052] In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise expressly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be connected inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0053] It should be noted that in the present application, relational terms such as "first" and "second" and the like are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is any such actual relationship or order between these entities or operations. Moreover, the terms "include", "contain" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or device. Without more limitations, the element defined by the statement "including a" does not exclude the presence of additional identical elements in the process, method, article or device including the element.

[0054] The foregoing detailed description of the application has been presented for purposes of illustration and description. Various modifications and changes can be made to these embodiments without departing from the spirit and scope of the application. It is intended that the scope of the application should not be limited by the particular representative embodiments described above.

Claims

1. An airfoil leading edge for an aircraft, characterized by, The application relates to an airfoil leading edge body (1) with a parallelogram cross section, wherein the leeward side of the airfoil leading edge body (1) is used to be connected with an airfoil, one of the two sides adjacent to the leeward side is a chord (11), and the other side is a root chord (12), the length of the chord (11) and the root chord (12) is smaller than the length of the leeward side, the windward surface of the chord (11) is determined according to a chord front end curve, and the windward surface of the root chord (12) is determined according to a root chord front end curve. A cooling flow channel (2) is arranged in the airfoil leading edge body (1), and cooling material is arranged in the cooling flow channel (2) to cool the airfoil leading edge body (1). The slightly string front end curve is: Wherein, x is the horizontal coordinate of any point on the slightly string front end curve, y is the vertical coordinate of any point on the slightly string front end curve, t is the parameter variable of the slightly string front end curve, The first thickness coefficient of the slightly string (11), The second thickness coefficient of the slightly string (11); The The value range is 1.2-4, the The value of the The value of the The root chord front end curve is: wherein x is the horizontal coordinate of any point on the root chord front end curve, y is the vertical coordinate of any point on the root chord front end curve, and t is the parametric variable of the root chord front end curve, is a first thickness coefficient of the root chord (12), is a second thickness coefficient of the root chord (12). The shape of the cooling flow channel (2) is S-shaped, the diameter of the cooling flow channel (2) is 2-8 mm, and the circular arc radius is 10-30 mm.

2. An airfoil leading edge for an aircraft as in claim 1, wherein, The value is 1-5 times the value of the value is 1-5 times the value of the value is 1-4 times the value of the value is 1-4 times the value of the 3. An airfoil leading edge for an aircraft as recited in claim 1, characterized in that, Phase change material (3) is arranged in the airfoil leading edge body (1), and the phase change material (3) is used to cool the airfoil leading edge body (1).

4. An airfoil leading edge for an aircraft as recited in claim 1, characterized in that, The airfoil leading edge body (1) is made of titanium alloy, alloy steel, high-temperature alloy and quartz fiber resin matrix composite material.

5. An airfoil leading edge for an aircraft as recited in claim 1, characterized in that, The application further relates to an airfoil leading edge for an aircraft, comprising an airfoil leading edge body according to any one of claims 1-5.

6. An aircraft, characterized in that ​

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