Steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave
阅读说明：本技术 基于前缘线等激波强度楔导乘波舵机鼓包设计方法 (Steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave ) 是由 丁峰 柳军 金亮 李洁 肖婷 郭善广 于 2021-09-23 设计创作，主要内容包括：基于前缘线等激波强度楔导乘波舵机鼓包设计方法,以鼓包前缘线水平投影型线作为设计输入,通过在鼓包迎风面各个纵向截面设置相同的楔角,实现各个纵向截面激波强度相同的设计构想,即实现舵机鼓包迎风面纵向激波沿横向等激波强度设计,与此同时,在楔形流场进行流线追踪生成各条鼓包迎风面流线,楔形流场流线放样生成的鼓包迎风面可以实现激波附体,从而减小气动阻力。本发明能够生成一种各个纵向截面激波强度相同、力热载荷特性分布均匀、迎风面激波附体的楔导乘波舵机鼓包,并将楔导乘波舵机鼓包与乘波体机身进行了一体化设计,从而进一步减小了舵机鼓包与乘波体机身组合体的阻力。(A bulge design method of a steering engine based on leading edge line equal shock wave intensity wedge guided wave is characterized in that a bulge leading edge line horizontal projection molded line is used as design input, the same wedge angle is arranged on each longitudinal section of the windward side of the bulge, the design conception that the shock wave intensity of each longitudinal section is the same is realized, namely the design of the longitudinal shock wave of the windward side of the bulge of the steering engine along the transverse equal shock wave intensity is realized, meanwhile, the flow line tracking is carried out in a wedge-shaped flow field to generate each bulge windward side flow line, and the bulge windward side generated by lofting of the wedge-shaped flow field flow line can realize shock wave attachment, so that the aerodynamic resistance is reduced. The wedge guided wave rider bulge with the same longitudinal section shock wave strength, uniform force and heat load characteristic distribution and attached shock waves on the windward side can be generated, and the wedge guided wave rider bulge and the rider body are integrally designed, so that the resistance of a combination of the steering engine bulge and the rider body is further reduced.)
1. A steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication is characterized by comprising the following steps:
generating a wave-rider fuselage;
under the condition that the width constraint condition of a steering engine bulge along the Z direction is met, designing a horizontal projection molded line of a front edge line of a windward side of the bulge, obtaining a series of front edge points of the windward side of the bulge by the horizontal projection molded line of the front edge line of the windward side of the bulge, and smoothly connecting the front edge points of the windward side of the bulge to form a front edge line of the windward side of the bulge;
under the condition of satisfying the height constraint condition of the steering engine bulge along the Y direction, designing a Y-direction coordinate value of a horizontal section where a rear edge line of a windward side of the bulge is located;
setting a wedge angle delta of a wedge on a longitudinal section corresponding to a front edge point of each bump windward side, generating a wedge shock wave and a wedge flow field by the wedge, and solving flow parameters of the wedge shock wave angle and the wedge flow field;
taking the front edge point of each windward side of the bulge as a starting point, performing streamline tracking in a wedge-shaped flow field until the horizontal section of the rear edge line of the windward side of the bulge is located, so as to generate a windward side streamline of the bulge corresponding to the front edge point of each windward side of the bulge, wherein the tail end point of each windward side streamline of the bulge is the rear edge point of the windward side of the bulge, and lofting all the windward side streamlines of the bulge to generate a wedge-guided ride wave;
according to the length of a wing root of an air rudder, wedge-guided wave-rider bulge, contour lines of a windward side of a bulge and a wave rider body, determining a rear edge line of a bulge upper surface, a left side contour line of the bulge upper surface, a right side contour line of the bulge upper surface, a lower edge contour line of the bulge left side surface, a lower edge contour line of a bulge forming right side surface, a left side contour line of a bulge bottom surface, a right side contour line of the bulge bottom surface and a lower edge contour line of the bulge bottom surface, and further determining and generating a bulge upper surface, a bulge left side surface, a bulge right side surface and a bulge bottom surface, wherein the bulge windward side surface, the bulge upper surface, the bulge left side surface, the bulge right side surface and the bulge bottom surface jointly form a steering engine bulge, and the steering engine body jointly form an integrated design configuration.
2. The steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication according to claim 1, characterized in that: and generating a waverider body by using a osculating axisymmetric von Karman waverider design method according to the flight condition and the size of the aircraft.
3. The steering engine bulge design method based on the leading edge line isoshock intensity wedge-guided wave-rider is characterized in that: uniformly dispersing the horizontal projection molded line of the leading edge line of the windward side of the bump from left to right to obtain N1The horizontal projection type line discrete points of the front edge line of the windward side of each bump; projecting the horizontal projection type line discrete points of the leading edge line of each bump windward side to the upper surface of the wave rider body along the longitudinal section of each bump windward side to obtain N1Front edge point of windward side of each bump, N1The front edge points of the windward sides of the bulges are smoothly connected to form a front edge line of the windward sides of the bulges.
4. The steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication according to claim 3, characterized in that: the wave rider body is composed of a family of discrete points and is divided into a plurality of triangular grid units, each triangular grid unit is composed of three adjacent discrete points, and the upper surface of the wave rider body is composed of M triangular grid units.
5. The steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication according to claim 4, characterized in that: sequentially solving horizontal projection type of leading edge line passing through ith bulge windward sideLine discrete point PL,iAnd the intersection point P of the straight line parallel to the Y axis and the plane where the jth triangular grid unit on the upper surface of the wave-rider body is locatedc,j，i＝1,2...N1J is 1,2.. M, and the intersection point P is determinedc,jWhether the wave-rider body is positioned in the jth triangular grid unit on the upper surface of the wave-rider body or not until the intersection point P is judgedc,jIs arranged inside the jth triangular grid unit on the upper surface of the wave-rider body, and the intersection point Pc,jNamely the leading edge point of the windward side of the ith bulge.
6. The steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication according to claim 3, characterized in that: a longitudinal section corresponding to the leading edge point of the ith bulge on the windward side, wherein i is 1,21The wedge starting point with the wedge angle delta is arranged at the front edge point of the i-th bump windward side, the lower wall surface of the wedge is parallel to the X axis, the wedge shock wave angle beta and wedge flow field flow parameters are solved by utilizing the oblique shock wave theory, and the wedge flow field flow parameters comprise Mach number, static temperature and static pressure.
7. The steering engine bulge design method based on leading edge line iso-shock intensity wedge guided wave multiplication according to claim 6, characterized in that: the wedge angle delta is smaller than the maximum wedge angle delta of the accessory shock wave generated by wedge splittingmI.e. delta < deltam。
8. The steering engine bulge design method based on leading edge line iso-shock intensity wedge guided wave multiplication according to claim 7, characterized in that: according to the oblique shock wave theory, solving to obtain the maximum shock wave angle beta corresponding to the incoming flow Mach number Mam：
Wherein γ represents the specific heat ratio;
the maximum wedge angle delta of the attached shock wave generated by the wedge under the condition of the incoming flow Mach number Ma can be ensuredmThe following equation is used to obtain:
9. the steering engine bulge design method based on leading edge line isoshock intensity wedge guided wave multiplication according to claim 1,2, 4, 5, 6, 7 or 8, characterized in that: according to the length of the wing root of the air rudder, the positions of the rear edge cross sections of the upper surfaces of the bulges are set, the rear edge points of the windward surfaces of the bulges are projected onto the rear edge cross sections of the upper surfaces of the bulges at the corresponding longitudinal sections of the rear edge points of the windward surfaces of the bulges, the corresponding rear edge points of the upper surfaces of the bulges are generated, and the rear edge points of the upper surfaces of the bulges are smoothly connected to form a rear edge line of the upper surfaces of the bulges.
10. The steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication according to claim 9, characterized in that: a straight line section formed by connecting the trailing edge point of the windward side of the 1 st bulge positioned at the leftmost side with the corresponding trailing edge point of the upper surface of the 1 st bulge is used as the left side contour line of the upper surface of the bulge, and the Nth bulge positioned at the rightmost side1The trailing edge point of the windward side of each bulge corresponds to the Nth point1And a straight line segment formed by connecting the rear edge points of the upper surface of each bulge is used as the right contour line of the upper surface of each bulge.
11. The steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication according to claim 10, characterized in that: the left side contour line of the upper surface of the bulge is equidistantly dispersed to generate N3The discrete points are called bulge upper surface left side contour points, and the bulge upper surface right side contour lines are equidistantly and discretely generated into N3The discrete points are called contour points on the right side of the upper surface of the bulge;
projecting discrete points on the 1 st bulge windward side flow direction molded line on the leftmost bulge and the bulge upper surface left side contour point to the upper surface of the wave rider body along the longitudinal section to generate bulge left side surface lower edge contour points, and smoothly connecting all bulge left side surface lower edge contour points to form a bulge left side surface lower edge contour line; will be located at the rightmost positionSide N1And projecting the discrete points on the windward side flow direction molded line of the strip bulge and the right side contour point of the upper surface of the bulge to the upper surface of the wave rider body along the longitudinal section to generate lower edge contour points of the right side surface of the bulge, and smoothly connecting the lower edge contour points of the right side surface of the bulge to form a lower edge contour line of the right side surface of the bulge.
12. The steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication according to claim 11, characterized in that: will be N3Left side contour line and Nth contour line of upper surface of each bump3The straight line segment formed by connecting the contour points of the lower edge of the left side surface of each bulge is used as the left side contour line of the bottom surface of the bulge, and the Nth bulge is connected with the contour points of the lower edge of the left side surface of the bulge3The contour point on the right side of the upper surface of each bulge and the Nth point3And a straight line segment formed by connecting contour points of the lower edge of the right side surface of each bulge is used as a right side contour line of the bottom surface of the bulge.
13. The steering engine bulge design method based on leading edge line iso-shock intensity wedge-guided wave multiplication according to claim 10, 11 or 12, characterized in that: and projecting the rear edge points of the upper surface of the bulge to the upper surface of the wave-rider body along the cross section to generate bulge bottom surface lower edge contour points, and smoothly connecting all bulge bottom surface lower edge contour points to form a bulge bottom surface lower edge contour line.
14. The steering engine bulge design method based on leading edge line isoshock intensity wedge-guided wave multiplication based on claim 1,2, 4, 5, 6, 7, 8, 10, 11 or 12, characterized in that:
a closed plane consisting of a rear edge line of the windward side of the bulge, a left side contour line of the upper surface of the bulge, a right side contour line of the upper surface of the bulge and a rear edge line of the upper surface of the bulge is used as the upper surface of the bulge; a closed plane formed by the flow direction line of the windward side of the leftmost bulge, the left side contour line of the upper surface of the bulge, the lower edge line of the left side surface of the bulge and the left side contour line of the bottom surface of the bulge is used as the left side surface of the bulge; a closed plane formed by the flow direction molded line of the windward side of the most right bulge, the right side contour line of the upper surface of the bulge, the lower edge line of the right side surface of the bulge and the right side contour line of the bottom surface of the bulge is used as the right side surface of the bulge; and a closed plane consisting of the rear edge line of the upper surface of the bulge, the left side contour line of the bottom surface of the bulge, the right side contour line of the bottom surface of the bulge and the lower edge contour line of the bottom surface of the bulge is used as the bottom surface of the bulge.
Technical Field
The invention relates to the technical field of aerodynamic shape design of hypersonic aircrafts, in particular to a steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication.
Background
The hypersonic aerocraft is an aerocraft which has a flight Mach number of more than 5, takes an air suction type engine or a combined engine thereof as main power or is unpowered, can remotely fly in an atmosphere and a trans-atmosphere, and can be applied in various forms, such as a hypersonic cruise missile, a hypersonic gliding aerocraft, a hypersonic manned/unmanned airplane, an aerospace plane, a hypersonic wide-speed-range aerocraft and the like.
The wave rider configuration utilizes a shock wave compression principle (wave rider principle) to realize the pneumatic requirement of high lift-drag ratio under the condition of hypersonic flight, so that the wave rider becomes an ideal configuration of the hypersonic flight vehicle.
The wave carrier is usually selected an air rudder to realize aircraft control when being used as an aircraft body, when the air rudder is installed on the wave carrier body, in order to control the gap heat flow between the air rudder and the wave carrier body, thereby avoiding the ablation of a rudder shaft, satisfying the requirements of installation spaces of structural members such as a steering engine, and improving the problem that the rudder effect of the air rudder is reduced because of the flow of the surface layer attached to the wall surface of the wave carrier body, usually, the steering engine bulge mode is selected to reduce the gap heat flow of the rudder shaft, the installation spaces of the structural members such as the steering engine are improved, and the problem of the rudder effect of the air rudder is improved. Meanwhile, the addition of the steering engine bulge increases the resistance of the wave rider body, and in order to reduce the increase in the resistance of the wave rider body caused by the addition of the steering engine bulge, the steering engine bulge needs to be designed in a rectifying manner.
The invention patent application with the publication number of CN112199853A, 1/8/2021 discloses a winged missile with a steering engine bulge and an optimization design method of the bulge, and the design method of the windward side of the steering engine bulge of the invention patent is that a first leading edge line 1, a second leading edge line 2, a third leading edge line 3 and a fourth leading edge line 4 shown in figure 1 are combined to generate a first side surface 5, then a second side surface 6 is generated by the same method, and the windward side of the steering engine bulge is formed by the first side surface and the second side surface: on one hand, the design problem that longitudinal shock wave intensity is distributed in the spanwise direction is not considered on the windward side of the steering engine bulge constructed by the method, so that the shock wave intensity of the longitudinal section of the bulge is gradually increased from the symmetrical surface to two sides, and the problem that the distribution of aerodynamic heat load characteristics of the bulge on different longitudinal sections is uneven is caused; on the other hand, the power curve or the Von Karman curve is adopted as the leading edge line of the windward side of the steering engine bulge, and because the initial inclination angles of the power curve or the Von Karman curve are both 90 degrees, the steering engine bulge generated by designing the curves has good volumetric efficiency and the stagnation point thermal protection performance of the leading edge line of the windward side, but the initial compression angle of the windward side of the steering engine bulge generated by designing the curves is 90 degrees, so that the shock wave is caused to have the problem of separation; the problems in the two aspects are not beneficial to reducing the problem of aircraft resistance increase caused by the additional installation of the steering engine bulge; meanwhile, the steering engine bulge is arranged on the aircraft body and is positioned in the low-energy flow of the boundary layer of the aircraft body, the front edge line of the windward side of the steering engine bulge has low heat protection requirement, and the steering engine bulge has low volume efficiency requirement, so that the front edge line of the windward side of the bulge can be designed by adopting a molded line with lower resistance. For the convenience of the following description, the invention patent design method with the publication number of CN112199853A, which is published as 1 month and 8 days 2021, is simply referred to as the original steering engine bulge design method.
Disclosure of Invention
On one hand, the original steering engine bulge design method does not consider the design problem that the longitudinal shock wave strength is distributed along the transverse direction, so that the shock wave strength of the longitudinal section of the bulge is gradually increased from the symmetrical surface to two sides, the aerodynamic heat load characteristic distribution of the bulge on different longitudinal sections is uneven, and on the other hand, the steering engine bulge in the original steering engine bulge design method has the problem that the shock wave is separated from the body because the initial compression angle of the windward side of the steering engine bulge is 90 degrees. Aiming at the defects of the original steering engine bulge design method, the invention aims to provide a steering engine bulge design method based on leading edge line and other shock wave intensity wedge guided wave multiplication. The wedge guided wave rider bulge with the same longitudinal section shock wave strength, uniform force and heat load characteristic distribution and attached shock waves on the windward side can be generated through the wedge guided wave rider steering engine bulge, and the wedge guided wave rider steering engine bulge and the rider body are integrally designed, so that the resistance of a steering engine bulge and rider body assembly is further reduced.
In order to realize the technical purpose of the invention, the following technical scheme is adopted:
a steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave comprises the following steps:
generating a wave-rider fuselage;
under the condition that the width constraint condition of a steering engine bulge along the Z direction is met, designing a horizontal projection molded line of a front edge line of a windward side of the bulge, obtaining a series of front edge points of the windward side of the bulge by the horizontal projection molded line of the front edge line of the windward side of the bulge, and smoothly connecting the front edge points of the windward side of the bulge to form a front edge line of the windward side of the bulge;
under the condition of satisfying the height constraint condition of the steering engine bulge along the Y direction, designing a Y-direction coordinate value of a horizontal section where a rear edge line of a windward side of the bulge is located;
setting a wedge angle delta of a wedge on a longitudinal section corresponding to a front edge point of each bump windward side, generating a wedge shock wave and a wedge flow field by the wedge, and solving flow parameters of the wedge shock wave angle and the wedge flow field;
taking the front edge point of each windward side of the bulge as a starting point, performing streamline tracking in a wedge-shaped flow field until the horizontal section of the rear edge line of the windward side of the bulge is located, so as to generate a windward side streamline of the bulge corresponding to the front edge point of each windward side of the bulge, wherein the tail end point of each windward side streamline of the bulge is the rear edge point of the windward side of the bulge, and lofting all the windward side streamlines of the bulge to generate a wedge-guided ride wave;
according to the length of a wing root of an air rudder, wedge-guided wave-rider bulge, contour lines of a windward side of a bulge and a wave rider body, determining a rear edge line of a bulge upper surface, a left side contour line of the bulge upper surface, a right side contour line of the bulge upper surface, a lower edge contour line of the bulge left side surface, a lower edge contour line of a bulge forming right side surface, a left side contour line of a bulge bottom surface, a right side contour line of the bulge bottom surface and a lower edge contour line of the bulge bottom surface, and further determining and generating a bulge upper surface, a bulge left side surface, a bulge right side surface and a bulge bottom surface, wherein the bulge windward side surface, the bulge upper surface, the bulge left side surface, the bulge right side surface and the bulge bottom surface jointly form a steering engine bulge, and the steering engine body jointly form an integrated design configuration.
Furthermore, according to the flight condition and the size of the aircraft, the invention utilizes a design method of a osculating axisymmetric von Karman waverider to generate the waverider fuselage. The flight conditions of the aircraft comprise incoming flow Mach number, incoming flow static pressure and incoming flow static temperature, and the size of the aircraft body comprises the length and the width of the aircraft body. The invention discloses a method for designing an osculating axisymmetric von Karman waverider, which is disclosed by CN109573092B from the invention of patent application No. 6/30 of 2020.
Furthermore, the wave rider body generated by the invention is composed of a family of discrete points (namely point clouds), the wave rider body is divided into a plurality of triangular mesh units, each triangular mesh unit is composed of three adjacent discrete points, and the upper surface of the wave rider body is composed of M triangular mesh units.
Further, the horizontal projection molded lines of the front edge line of the windward side of the bump are uniformly dispersed from left to right to obtain N1The horizontal projection type line discrete points of the front edge line of the windward side of each bump; projecting the horizontal projection type line discrete points of the leading edge line of each bump windward side to the upper surface of the wave rider body along the longitudinal section of each bump windward side to obtain N1Front edge point of windward side of each bump, N1The front edge points of the windward sides of the bulges are smoothly connected to form a front edge line of the windward sides of the bulges.
The method for determining the leading edge point of the windward side of the bump comprises the following steps: sequentially solving the horizontal projection type line discrete points P passing through the ith bulge windward side leading edge lineL,iAnd the intersection point P of the straight line parallel to the Y axis and the plane where the jth triangular grid unit on the upper surface of the wave-rider body is locatedc,j，i＝1,2...N1J is 1,2.. M, and the intersection point P is determinedc,jWhether the wave-rider body is positioned in the jth triangular grid unit on the upper surface of the wave-rider body or not until the intersection point P is judgedc,jIs arranged inside the jth triangular grid unit on the upper surface of the wave-rider body, and the intersection point Pc,jI.e. the ith bulge windward sideFront edge point PL,i′。
Furthermore, the invention relates to a longitudinal section corresponding to the leading edge point of the ith bulge on the windward side, wherein i is 1,21The wedge starting point with the wedge angle delta is arranged at the front edge point of the i-th bump windward side, the lower wall surface of the wedge is parallel to the X axis, the wedge shock wave angle beta and wedge flow field flow parameters are solved by utilizing the oblique shock wave theory, and the wedge flow field flow parameters comprise Mach number, static temperature and static pressure. In order to ensure that the wedge-shaped shock wave is the attached shock wave under the condition of the incoming current Mach number Ma, the wedge angle delta must be smaller than the maximum wedge angle delta of the attached shock wave generated by wedge splittingmI.e. delta < deltam。
According to the oblique shock wave theory, solving to obtain the maximum shock wave angle beta corresponding to the incoming flow Mach number Mam：
Wherein γ represents the specific heat ratio.
The maximum wedge angle delta of the attached shock wave generated by the wedge under the condition of the incoming flow Mach number Ma can be ensuredmThe following equation is used to obtain:
furthermore, the method takes the leading edge point of the windward side of the ith bulge as a starting point, and carries out streamline tracking in the wedge-shaped flow field until the horizontal section where the trailing edge line of the windward side of the bulge is located, so as to generate a cluster of N2Discrete points consisting of points, the family of discrete points being referred to as i-th bump windward streamline discrete points, N2The discrete points of the ith bulge windward side streamline are smoothly connected to form the ith bulge windward side streamline, i is 1,21. The tail end point of the streamline of the windward side of the ith bulge is the rear edge point of the windward side of the ith bulge, N1The rear edge points of the windward side of the bulges are smoothly connected to form a rear edge line of the windward side of the bulges. N is a radical of1And (4) lofting the streamline of the windward side of the strip bulge to generate the windward side of the bulge. The streamline tracing method is from' T peak absorptionResearch on pneumatic design theory and method of integrated inner and outer flow of air-type hypersonic aerocraft]Long sand: national defense science and technology university (Ph.D.),2016: p68-69, "pneumatic design theory and methodology research.
Furthermore, according to the length of the wing root of the air rudder, the rear edge cross section position of the upper surface of the bulge is set, the rear edge point of the windward surface of the bulge is projected onto the rear edge cross section of the upper surface of the bulge at the corresponding longitudinal section of the rear edge point of the windward surface of each bulge, corresponding rear edge points of the upper surface of the bulge are generated, and the rear edge points of the upper surface of the bulge are smoothly connected to form a rear edge line of the upper surface of the bulge.
Furthermore, a straight line segment formed by connecting the trailing edge point of the windward surface of the leftmost bulge 1 and the corresponding trailing edge point of the upper surface of the leftmost bulge 1 is used as the left side contour line of the upper surface of the bulge, and the Nth bulge located at the rightmost side is used as the Nth contour line of the upper surface of the rightmost bulge1The trailing edge point of the windward side of each bulge corresponds to the Nth point1And a straight line segment formed by connecting the rear edge points of the upper surface of each bulge is used as the right contour line of the upper surface of each bulge.
Furthermore, the invention generates N by equidistantly and discretely generating the left contour line of the upper surface of the bulge3The discrete points are called bulge upper surface left side contour points, and the bulge upper surface right side contour lines are equidistantly and discretely generated into N3The discrete points are called contour points on the right side of the upper surface of the bulge;
projecting discrete points on the 1 st bulge windward side flow direction molded line on the leftmost bulge and the bulge upper surface left side contour point to the upper surface of the wave rider body along the longitudinal section to generate bulge left side surface lower edge contour points, and smoothly connecting all bulge left side surface lower edge contour points to form a bulge left side surface lower edge contour line; will be located at the rightmost N1And projecting the discrete points on the windward side flow direction molded line of the strip bulge and the right side contour point of the upper surface of the bulge to the upper surface of the wave rider body along the longitudinal section to generate lower edge contour points of the right side surface of the bulge, and smoothly connecting the lower edge contour points of the right side surface of the bulge to form a lower edge contour line of the right side surface of the bulge.
Further, the present invention will be described in detail with reference to the N3Left side contour line and Nth contour line of upper surface of each bump3Lower edge of left side surface of each bulgeTaking a straight line segment formed by connecting edge contour points as the left contour line of the bottom surface of the bulge, and connecting the Nth contour line3The contour point on the right side of the upper surface of each bulge and the Nth point3And a straight line segment formed by connecting contour points of the lower edge of the right side surface of each bulge is used as a right side contour line of the bottom surface of the bulge.
Furthermore, the rear edge points of the upper surface of the bulge are projected to the upper surface of the wave rider body along the cross section to generate bulge bottom surface lower edge contour points, and all bulge bottom surface lower edge contour points are smoothly connected to form a bulge bottom surface lower edge contour line.
Furthermore, a closed plane formed by a rear edge line of the windward side of the bulge, a left side contour line of the upper surface of the bulge, a right side contour line of the upper surface of the bulge and a rear edge line of the upper surface of the bulge is used as the upper surface of the bulge; a closed plane formed by the flow direction line of the windward side of the leftmost bulge, the left side contour line of the upper surface of the bulge, the lower edge line of the left side surface of the bulge and the left side contour line of the bottom surface of the bulge is used as the left side surface of the bulge; a closed plane formed by the flow direction molded line of the windward side of the most right bulge, the right side contour line of the upper surface of the bulge, the lower edge line of the right side surface of the bulge and the right side contour line of the bottom surface of the bulge is used as the right side surface of the bulge; and a closed plane consisting of the rear edge line of the upper surface of the bulge, the left side contour line of the bottom surface of the bulge, the right side contour line of the bottom surface of the bulge and the lower edge contour line of the bottom surface of the bulge is used as the bottom surface of the bulge.
The invention provides computer equipment, which comprises a memory and a processor, wherein the memory stores a computer program, and the processor realizes the following steps when executing the computer program:
generating a wave-rider fuselage;
under the condition that the width constraint condition of a steering engine bulge along the Z direction is met, designing a horizontal projection molded line of a front edge line of a windward side of the bulge, obtaining a series of front edge points of the windward side of the bulge by the horizontal projection molded line of the front edge line of the windward side of the bulge, and smoothly connecting the front edge points of the windward side of the bulge to form a front edge line of the windward side of the bulge;
under the condition of satisfying the height constraint condition of the steering engine bulge along the Y direction, designing a Y-direction coordinate value of a horizontal section where a rear edge line of a windward side of the bulge is located;
setting a wedge angle of a wedge on a longitudinal section corresponding to a front edge point of each bump windward side, generating a wedge shock wave and a wedge flow field by the wedge, and solving flow parameters of the wedge shock wave angle and the wedge flow field;
taking the front edge point of each windward side of the bulge as a starting point, performing streamline tracking in a wedge-shaped flow field until the horizontal section of the rear edge line of the windward side of the bulge is located, so as to generate a windward side streamline of the bulge corresponding to the front edge point of each windward side of the bulge, wherein the tail end point of each windward side streamline of the bulge is the rear edge point of the windward side of the bulge, and lofting all the windward side streamlines of the bulge to generate a wedge-guided ride wave;
according to the length of a wing root of an air rudder, wedge-guided wave-rider bulge, contour lines of a windward side of a bulge and a wave rider body, determining a rear edge line of a bulge upper surface, a left side contour line of the bulge upper surface, a right side contour line of the bulge upper surface, a lower edge contour line of the bulge left side surface, a lower edge contour line of a bulge forming right side surface, a left side contour line of a bulge bottom surface, a right side contour line of the bulge bottom surface and a lower edge contour line of the bulge bottom surface, and further determining and generating a bulge upper surface, a bulge left side surface, a bulge right side surface and a bulge bottom surface, wherein the bulge windward side surface, the bulge upper surface, the bulge left side surface, the bulge right side surface and the bulge bottom surface jointly form a steering engine bulge, and the steering engine body jointly form an integrated design configuration.
The present invention provides a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, performs the steps of:
generating a wave-rider fuselage;
under the condition that the width constraint condition of a steering engine bulge along the Z direction is met, designing a horizontal projection molded line of a front edge line of a windward side of the bulge, obtaining a series of front edge points of the windward side of the bulge by the horizontal projection molded line of the front edge line of the windward side of the bulge, and smoothly connecting the front edge points of the windward side of the bulge to form a front edge line of the windward side of the bulge;
under the condition of satisfying the height constraint condition of the steering engine bulge along the Y direction, designing a Y-direction coordinate value of a horizontal section where a rear edge line of a windward side of the bulge is located;
setting a wedge angle of a wedge on a longitudinal section corresponding to a front edge point of each bump windward side, generating a wedge shock wave and a wedge flow field by the wedge, and solving flow parameters of the wedge shock wave angle and the wedge flow field;
taking the front edge point of each windward side of the bulge as a starting point, performing streamline tracking in a wedge-shaped flow field until the horizontal section of the rear edge line of the windward side of the bulge is located, so as to generate a windward side streamline of the bulge corresponding to the front edge point of each windward side of the bulge, wherein the tail end point of each windward side streamline of the bulge is the rear edge point of the windward side of the bulge, and lofting all the windward side streamlines of the bulge to generate a wedge-guided ride wave;
according to the length of a wing root of an air rudder, wedge-guided wave-rider bulge, contour lines of a windward side of a bulge and a wave rider body, determining a rear edge line of a bulge upper surface, a left side contour line of the bulge upper surface, a right side contour line of the bulge upper surface, a lower edge contour line of the bulge left side surface, a lower edge contour line of a bulge forming right side surface, a left side contour line of a bulge bottom surface, a right side contour line of the bulge bottom surface and a lower edge contour line of the bulge bottom surface, and further determining and generating a bulge upper surface, a bulge left side surface, a bulge right side surface and a bulge bottom surface, wherein the bulge windward side surface, the bulge upper surface, the bulge left side surface, the bulge right side surface and the bulge bottom surface jointly form a steering engine bulge, and the steering engine body jointly form an integrated design configuration.
Compared with the prior art, the invention can produce the following technical effects:
the invention takes the horizontal projection molded line of the front edge line of the bulge as the design input, and the same wedge angle is arranged on each longitudinal section of the windward side of the bulge, so that the design idea that the shock wave intensity of each longitudinal section is the same is realized, namely the longitudinal shock wave of the windward side of the bulge of the steering engine is designed along the transverse equal shock wave intensity, meanwhile, the streamlines of the windward side of the bulge are generated by carrying out streamline tracing on the wedge-shaped flow field, and the windward side of the bulge generated by lofting the wedge-shaped flow field streamlines can realize shock wave attachment, thereby reducing the aerodynamic resistance.
The invention solves the problem that the original steering engine bulge design method does not consider that the longitudinal shock wave intensity is distributed along the transverse direction, so that the shock wave intensity of the longitudinal section of the bulge is gradually increased from the symmetrical surface to two sides, and the aerodynamic heat load characteristic distribution of the bulge on different longitudinal sections is not uniform, and simultaneously solves the problem that the shock wave is separated from the body because the initial compression angle of the windward side of the steering engine bulge in the original steering engine bulge design method is 90 degrees. The wedge guided wave rider bulge with the same longitudinal section shock wave strength, uniform force and heat load characteristic distribution and attached shock waves on the windward side is generated, and the wedge guided wave rider bulge and the rider body are integrally designed, so that the resistance of a combination of the steering engine bulge and the rider body is further reduced.
Drawings
FIG. 1 shows a schematic diagram of a design method of a windward side of an original steering engine bulge;
FIG. 2 illustrates aircraft flight conditions and fuselage dimensions;
FIG. 3 shows an isometric view of a waverider body and a rectangular coordinate system definition;
FIG. 4 shows a side view of a waverider body and a rectangular coordinate system definition;
FIG. 5 shows a top view of a waverider fuselage and a rectangular coordinate system definition;
FIG. 6 shows a family of discrete points (i.e., point clouds), triangular mesh cells, and a partial magnified view of a fuselage that constitutes a waverider volume;
FIG. 7 shows the horizontal projected profile of the leading edge line of the windward side of the bulge;
FIG. 8 shows the horizontal projection of the line discrete points of the leading edge line of the windward side of the bump;
FIG. 9 is a schematic diagram showing a process of projecting the discrete points of the horizontal projection profile of the leading edge line of the windward side of the ith bump to the upper surface of the wave-rider fuselage along a longitudinal section;
FIG. 10 is a schematic diagram illustrating the determination of the leading edge point of the windward side of the bulge;
FIG. 11 is a schematic diagram showing the intersection of the leading edge line of the windward side of the bump and the triangular mesh unit on the upper surface of the hull;
FIG. 12 is a schematic diagram of solving for a bulge windward leading edge line from a bulge windward leading edge line horizontal projection profile;
FIG. 13 is a schematic diagram showing the solution of the ith bump leading edge point to the ith bump trailing edge point from the ith bump leading edge point;
FIG. 14 is a schematic view showing a longitudinal cross-section corresponding to the ith bump leading edge point, the longitudinal cross-section being a plane passing through the ith bump leading edge point and being parallel to the XOY plane;
FIG. 15 shows a schematic view of the flow direction profile of the windward side of the bulge with the wave rider fuselage;
FIG. 16 is a schematic view of all of the bulge upwind flow profiles and discrete points on each of the bulge upwind flow profiles;
FIG. 17 shows a schematic of the bulge windward side generated from the lofting of the streamlines of all bulge windward sides;
FIG. 18 is a schematic diagram showing the generation of the contour lines of the upper surface, left side, right side and bottom of the drum;
FIG. 19 is a left and rear perspective view of an integrated design configuration formed by a steering engine bulge and a wave rider body;
FIG. 20 is a front right perspective view of the integrated design configuration formed by the steering engine bulge and the wave rider body;
FIG. 21 illustrates an aircraft configuration in which a steering engine bulge and a waverider fuselage are combined with an air rudder;
FIG. 22 is a grid diagram illustrating numerical simulation of an integrated design configuration of a steering engine bulge and a waverider body on a longitudinal symmetry plane, which is obtained by the method of the present invention in an embodiment of the present invention;
fig. 23 shows numerical simulation results of the steering engine bulge and waverider body integrated design configuration obtained by the method of the present invention in 6 different longitudinal sections, where (a) represents the numerical simulation result of the longitudinal section with Z equal to 0 mm; (b) numerical simulation results representing a longitudinal section of 10 mm; (c) numerical simulation results representing Z20 mm; (d) table Z-numerical simulation results of 30 mm; (e) numerical simulation results representing Z40 mm; (f) numerical simulation results representing Z50 mm.
The reference numbers in the figures illustrate:
1 represents a first front edge line of the windward side of an original steering engine bulge; 2, a second front edge line of the windward side of the original steering engine bulge; 3, a third leading edge line of the windward side of the original steering engine bulge; 4 original steering engine bulge welcomeA fourth leading edge line of the wind surface; 5, a first side surface of the windward side of the original steering engine bulge; 6 represents the second side surface of the windward side of the original steering engine bulge; 7 denotes the fuselage length; 8 denotes the fuselage width; 9, flight conditions including an incoming flow mach number, an incoming flow static temperature and an incoming flow static temperature; x represents a longitudinal coordinate value of the rectangular coordinate system; y represents a normal direction coordinate value of the rectangular coordinate system; z represents a coordinate value in the transverse direction of the rectangular coordinate system; o represents the origin of coordinates of the rectangular coordinate system; 10, a horizontal projection profile of a leading edge line of the windward side of the bump; 11 represents the horizontal projection type line discrete point P of the leading edge line of the windward side of the ith bulgeL,i(ii) a 12 denotes the leading edge point P of the i-th bump on the windward sideL,i'; 13 denotes a horizontal projection type line discrete point P passing through the leading edge line of the i-th bump windward sideL,iAnd a line parallel to the Y axis; 14, a jth triangular grid unit on the upper surface of the wave-rider body is shown, and three vertexes of the jth triangular grid unit are a 1# discrete point 15, a 2# discrete point 16 and a 3# discrete point 17 respectively; 15 denotes the 1# discrete point of the jth triangular mesh unit on the upper surface of the wave-rider body; 16 represents the 2# discrete point of the jth triangular mesh unit on the upper surface of the wave-rider body; 17 denotes a 3# discrete point of the jth triangular mesh unit on the upper surface of the wave-rider body; 18 denotes the leading edge line of the windward side of the bulge; 19 represents the average compression angle of the longitudinal section of the windward side of the bump; 20, a straight line which passes through the leading edge point of the windward side of the ith bulge and has the slope which is the sine value of the average compression angle of the longitudinal section of the windward side of the bulge; 21 represents a horizontal section where the trailing edge line of the windward side of the bump is located, and Y is equal to YT(ii) a 22 denotes the i-th bump windward side trailing edge point; 23 denotes the bulge windward side trailing edge line; 24 denotes a wedge; 25 represents a wedge angle δ of the wedge; 26 denotes a wedge-wedge lower wall surface; 27 denotes a wedge shock; 28 denotes a wedge-shaped shock angle β; 29 denotes a wedge-shaped flow field; 30 represents the flow direction profile of the windward side of the ith bulge; 31 denotes the i-th bump windward side trailing edge point; 32 represents N1The strip bulge is provided with a windward side flow profile; 33 denotes a bump upper surface trailing edge cross-sectional position X ═ XT(ii) a 34 represents the 1 st trailing edge point of the windward side of the bulge; 35 denotes the 1 st bump upper surface trailing point, which also denotes the Nth bump upper surface trailing point3A left side contour point of the upper surface of each bulge; 36 denotes the Nth1The rear edge point of the windward side of each bulge; 37 denotes the Nth1Individual drumThe rear edge point of the upper surface of the bag, which also represents the Nth3The right outline point of the upper surface of each bulge; 38 denotes the 1 st bump leading edge point, which also denotes the 1 st bump left side lower edge contour point; 39 denotes the Nth3The lower edge contour point of the left side surface of each bulge; 40 denotes the Nth1The leading edge point of the windward side of each bulge also represents the lower edge contour point of the right side surface of the 1 st bulge; 41 denotes the Nth3The lower edge contour point of the right side surface of each bulge; 42 denotes a steering engine bump; 43 denotes a wave-rider body; and 44 denotes an air rudder.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention provides a steering engine bulge design method based on leading edge line equal shock wave intensity wedge guided wave multiplication, which comprises the following steps:
and S1, generating a waverider fuselage according to the flight condition and the fuselage size of the aircraft by using a osculating axisymmetric Von Karman waverider design method.
As shown in fig. 2, the flight conditions 9 include an incoming mach number, an incoming static pressure and an incoming static temperature, the size of the fuselage includes a fuselage length 7 and a fuselage width 8, and the osculating axisymmetric von karman wavelet design method is the osculating axisymmetric von karman wavelet design method disclosed in the invention patent CN109573092B, published as 2020, 6, 30.
The isometric view, the side view, the top view and the rectangular coordinate system of the wave-rider body generated in S1 according to an embodiment of the present invention are defined as shown in fig. 3, 4 and 5, wherein X represents the longitudinal coordinate value of the rectangular coordinate system; y represents a normal direction coordinate value of the rectangular coordinate system; z represents a coordinate value in the transverse direction of the rectangular coordinate system; and O represents the origin of coordinates of a rectangular coordinate system.
S2, under the condition that the width constraint condition of the steering engine bulge along the Z direction is met, designing a bulge windward front edge line horizontal projection molded line 10, obtaining a series of bulge windward front edge points through the bulge windward front edge line horizontal projection molded line 10, and smoothly connecting all bulge windward front edge points to form a bulge windward front edge line.
In an embodiment of the present invention, as shown in fig. 6, the wave rider body is formed by a family of discrete points (i.e., point clouds), the wave rider body is divided into a plurality of triangular mesh units, each triangular mesh unit is formed by three adjacent discrete points, and the upper surface of the wave rider body is formed by M triangular mesh units. As shown in fig. 6, the j-th triangular mesh unit 14 on the upper surface of the wave-rider body has three vertices of a # 1 discrete point 15, a # 2 discrete point 16, and a # 3 discrete point 17.
As shown in fig. 7, a horizontal projection molded line 10 of a front edge line of a windward side of a bulge is designed according to width constraint of the bulge of the steering engine along the Z direction; as shown in fig. 8, the horizontal projection profile 10 of the leading edge line of the windward side of the bulge is uniformly dispersed, and the dispersion is N1The horizontal projection type line discrete point of the windward leading edge line of each bump 11 represents the horizontal projection type line discrete point P of the windward leading edge line of the ith bumpL,i。
As shown in fig. 9, the ith bulge windward front edge line horizontal projection type line discrete point 11 is projected to the upper surface of the wave-rider body along the longitudinal section thereof to generate the ith bulge windward front edge point PL,i' 12, N was generated by the same method1Front edge point of windward side of each bump, N1The front edge points of the windward sides of the bulges are smoothly connected to form a front edge line of the windward sides of the bulges.
As shown in fig. 10, in S2 according to an embodiment of the present invention, based on the ith bump windward leading edge line horizontal projection type line discrete point 11, the ith bump windward leading edge line horizontal projection type line discrete points P are sequentially solvedL,iAnd the intersection point P of the straight line 13 parallel to the Y axis and the plane where the jth triangular grid cell 14 on the upper surface of the wave-rider body is locatedc,j，i＝1,2...N1J is 1,2.. M, and the intersection point P is determinedc,jWhether the wave-rider body is positioned in the jth triangular grid unit on the upper surface of the wave-rider body or not until the intersection point P is judgedc,jIs arranged inside the jth triangular grid unit on the upper surface of the wave-rider body, and the intersection point Pc,jNamely the leading edge point P of the windward side of the ith bulgeL,i′12。
Referring to fig. 11 and 12, fig. 11 shows a schematic diagram of intersection of a leading edge line of a windward side of a bump and a triangular mesh unit on the upper surface of a wave-rider body; FIG. 12 is a schematic diagram showing a solution of the bulge windward leading edge line from the bulge windward leading edge line horizontal projection profile. From N1The front edge line of the windward side of the bump formed by the discrete points is intersected with the triangular grid unit on the upper surface of the wave-rider body, so that the front edge line 18 of the windward side of the bump is obtained by solving the horizontal projection molded line of the front edge line of the windward side of the bump as shown in fig. 12.
S3, referring to FIG. 13, under the condition that the height constraint condition of the steering engine bulge along the Y direction is met, designing a Y-direction coordinate value Y of a horizontal section 21 where a rear edge line of the windward side of the bulge is locatedT。
And S4, giving a wedge angle delta of the wedge on the longitudinal section corresponding to the front edge point of the windward side of each bump, generating a wedge shock wave and a wedge flow field by the wedge, and solving the flow parameters of the wedge shock wave angle and the wedge flow field.
In an embodiment of the present invention, as shown in fig. 14, a wedge angle 25 of a wedge 24 is given on a longitudinal section corresponding to the leading edge point of the windward side of the ith bulge, the angle of the wedge 25 is δ, and the starting point of the wedge 24 is set at the leading edge point P of the windward side of the ith bulgeL,i' 12, a lower wall surface 26 of the wedge is parallel to the X axis, a wedge 24 with a wedge angle 25 generates a wedge shock wave 27 and a wedge flow field 29, and a wedge shock wave angle beta (marked by 28 in figure 14) and wedge flow field flow parameters are solved by utilizing a wedge shock wave theory, wherein the wedge flow field flow parameters comprise Mach number, static temperature and static pressure. In order to ensure that the wedge-shaped shock wave 27 is an attached shock wave under the condition of the incoming flow Mach number Ma, the wedge angle delta must be smaller than the maximum wedge angle delta of the attached shock wave generated by wedge splittingmI.e. delta < deltam。
In one embodiment of the invention, the wedge angle beta is the maximum wedge angle of the accessory shock wave generated by the wedgemThe following method was used:
solving according to the oblique shock wave theory to obtain the maximum shock wave angle beta corresponding to the incoming flow Mach number Mam，
Wherein γ represents the specific heat ratio.
Solving and obtaining the maximum wedge angle delta of the attached shock wave generated by wedge by utilizing the oblique shock wave theorym，
And S5, taking the front edge point of each windward side of the bulge as a starting point, performing streamline tracking in the wedge-shaped flow field until the horizontal section of the rear edge line of the windward side of the bulge is located, so as to generate a windward side streamline of the bulge corresponding to the front edge point of each windward side of the bulge, wherein the tail end point of each windward side streamline of the bulge is the rear edge point of the windward side of the bulge, and lofting all the windward side streamlines of the bulge to generate the windward side of the bulge with wedge-guided ride wave.
With reference to fig. 14, 15, 16 and 17, with the ith bulge windward leading edge point as a starting point, carrying out streamline tracing on the wedge-shaped flow field until the bulge windward trailing edge line is located on a horizontal section, thereby generating a family of N-H2Discrete points consisting of points, the family of discrete points being referred to as i-th bump windward streamline discrete points, N2The discrete points of the ith bulge windward side flow line are smoothly connected to form the ith bulge windward side flow line, the tail end point of the ith bulge windward side flow line is the ith bulge windward side rear edge point, N1The rear edge points of the windward side of the bulges are smoothly connected to form a rear edge line of the windward side of the bulges. N is a radical of1Strip bulge upwind streamlines 32 and N1The strip bulge upwind streamlines 32 and the waverider fuselage are shown in fig. 15 and 16.
The streamline tracing method in the S4.2 of the invention is from a T-peak, air-breathing hypersonic aerocraft internal and external integrated full waverider pneumatic design theory and method to research [ D ] Changsha: national defense science and technology university (Ph.D.),2016: p68-69, "pneumatic design theory and methodology research.
As shown in FIG. 17, N1And lofting the flow direction molded line 32 of the windward side of the strip bulge to generate the windward side of the bulge.
S6, determining a rear edge line of the upper surface of the bulge, a left side contour line of the upper surface of the bulge, a right side contour line of the upper surface of the bulge, a lower edge contour line of the left side surface of the bulge, a lower edge contour line of the right side surface of the bulge, a left side contour line of the bottom surface of the bulge, a right side contour line of the bottom surface of the bulge and a lower edge contour line of the bottom surface of the bulge according to the length of the wing root of the air rudder, wedge-guided wave-rider bulge, determining the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge, forming the steering engine bulge together by the windward surface of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge, and forming an integrated design configuration together by the steering engine bulge and the wave-rider body.
In an embodiment of the present invention, S6 is implemented by the following steps:
s6.1, as shown in fig. 18, a cross-sectional position 33 of the trailing edge of the upper surface of the drum is set according to the length of the rudder root, and the coordinate value of the cross-sectional position X is X ═ XTAnd projecting the rear edge point of the windward side of the bulge onto the cross section of the rear edge of the upper surface of the bulge at the corresponding longitudinal section of the rear edge point of the windward side of each bulge, so as to generate the rear edge point of the upper surface of the bulge, wherein the rear edge points of the upper surface of the bulge form a rear edge line of the upper surface of the bulge.
S6.2, taking a straight line segment formed by the 1 st bulge windward side rear edge point 34 and the 1 st bulge upper surface rear edge point 35 as a bulge upper surface left side contour line 34-35, and taking the line segment as the N1Rear edge point 36 and Nth of windward side of each bump1Straight line segments consisting of the rear edge points 37 of the upper surface of each bump serve as the right contour lines 36-37 of the upper surface of the bump.
S6.3, generating N by equidistant generating of left contour lines 34-35 of the upper surface of the bulge3The discrete points are called bulge upper surface left contour points, and N is generated by equidistant generation of the bulge upper surface right contour lines 36-373And the discrete points are called contour points on the right side of the upper surface of the bump.
S6.4, projecting discrete points on the windward side flow direction profile line of the 1 st bulge on the leftmost side and the contour points on the left side of the upper surface of the bulge to the upper surface of the wave rider body along the longitudinal section to generate contour points of the lower edge of the left side surface of the bulge, and smoothly connecting the contour points of the lower edge of the left side surface of the bulge to form a contour line 38-39 of the lower edge of the left side surface of the bulge; will be located at the rightmost sideN of (A)1The discrete points on the windward side flow direction molded lines of the strip bulges and the right side contour points of the upper surfaces of the bulges are projected to the upper surface of the wave rider body along the longitudinal section to generate lower edge contour points of the right side surfaces of the bulges, and the lower edge contour points of the right side surfaces of the bulges are smoothly connected to form lower edge contour lines 40-41 of the right side surfaces of the bulges. In fig. 18, 38 indicates the leading edge point of the 1 st bump on the windward side, and it also indicates the lower edge contour point of the left side face of the 1 st bump; 39 denotes the Nth3The lower edge contour point of the left side surface of each bulge; 40 denotes the Nth1The leading edge point of the windward side of each bulge also represents the lower edge contour point of the right side surface of the 1 st bulge; 41 denotes the Nth3The lower edge contour point of the right side surface of each bulge.
S6.5, adding the N3Left side contour point 35 and Nth of upper surface of each bump3Taking a straight line segment consisting of contour points 39 of the lower edge of the left side surface of each bulge as a left contour line 35-39 of the bottom surface of the bulge, and taking the Nth contour line as the contour line of the bottom surface of the bulge3The right contour point 37 and the Nth contour point of the upper surface of each bump3Straight line segments consisting of the contour points 41 of the lower edge of the right side surface of each bulge are taken as the right contour lines 37-41 of the bottom surface of the bulge.
S6.6, projecting the rear edge points of the upper surface of the bulge to the upper surface of the wave rider body along the cross section to generate bulge bottom surface lower edge contour points, wherein all bulge bottom surface lower edge contour points form bulge bottom surface lower edge contour lines 39-41.
S6.7, taking a closed plane formed by a rear edge line 34-36 of the windward side of the bulge, a left side contour line 34-35 of the upper surface of the bulge, a right side contour line 36-37 of the upper surface of the bulge and a rear edge line 35-37 of the upper surface of the bulge as the upper surface of the bulge, and taking a closed plane formed by a flow direction molded line 38-34 of the windward side of the bulge, a left side contour line 34-35 of the upper surface of the bulge, a lower edge line 38-39 of the left side surface of the bulge and a left side contour line 35-39 of the bottom surface of the bulge as the left side surface of the bulge; will be N1A closed plane formed by a strip bulge windward side flow direction molded line 40-36, a bulge upper surface right side contour line 36-37, a bulge right side surface lower edge line 40-41 and a bulge bottom surface right side contour line 37-41 is used as a bulge right side surface; taking a closed plane consisting of a bulge upper surface rear edge line 35-37, a bulge bottom surface left side contour line 35-39, a bulge bottom surface right side contour line 37-41 and a bulge bottom surface lower edge contour line 39-41 as a closed planeThe bottom surface of the bulge.
S6.8, the windward side of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge form a steering engine bulge, and the steering engine bulge and the wave rider body form an integrated design.
As shown in fig. 19 and 20, the windward side of the bulge, the upper surface of the bulge, the left side surface of the bulge, the right side surface of the bulge and the bottom surface of the bulge form a steering engine bulge, and the steering engine bulge 42 and the wave rider body 43 form an integrated design configuration; the configuration of the aircraft in which the air rudder 44 is installed on the upper surface of the bulge, the steering engine bulge and the wave rider body are integrally designed, and the air rudder 44 is combined with the bulge and the wave rider body is shown in fig. 21.
The application case is as follows:
according to the embodiment, the incoming flow Mach number is 10.0, the incoming flow static pressure is 1197.031Pa, and the incoming flow static temperature is 226.509K, the shape of the embodiment based on the integrated design configuration of the leading edge line isoshock wave intensity wedge-guided wave rider bulge and the wave rider body is generated by adopting the method provided by the embodiment, and the shape of the embodiment is numerically simulated.
Fig. 22 shows a numerical simulation grid of the steering engine bulge and waverider body integrated design configuration in the longitudinal symmetry plane in the present embodiment, and fig. 23 shows numerical simulation results of the steering engine bulge and waverider body integrated design configuration in 6 different longitudinal sections in the present embodiment, where the parameter shown in the figure is the mach number of the flow field. Wherein (a) represents the numerical simulation results of a longitudinal section of Z ═ 0 mm; (b) numerical simulation results representing a longitudinal section of 10 mm; (c) numerical simulation results representing Z20 mm; (d) table Z-numerical simulation results of 30 mm; (e) numerical simulation results representing Z40 mm; (f) numerical simulation results representing Z50 mm.
As can be seen from fig. 23, the shock wave forms of different longitudinal sections are basically the same as the flow field structure, which verifies that the steering engine bulge generated by the invention has the characteristics of the same shock wave intensity of each longitudinal section and the uniform distribution of force-heat load characteristics, and solves the design problem that the longitudinal shock wave intensity is not considered to be distributed along the transverse direction in the original steering engine bulge design method. Meanwhile, the shock waves with different longitudinal sections are appendage shock waves, the fact that the steering engine bulge windward side shock waves generated by the invention are appendage shock waves is verified, and the problem that the original steering engine bulge windward side shock waves are detached is solved.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.