A high-maneuverability wave glider vehicle and a design method thereof

Abstract

The application discloses a design method of a high-maneuverability control characteristic gliding wave-riding aircraft, and the design method comprises the following steps: step one, selecting a conical wave-riding body as a basic configuration of the aircraft, wherein the wave-riding body comprises a fixed section aircraft body and variable side front edges located on the left and right sides of the fixed section aircraft body, the variable side front edges can be rotated into the fixed section aircraft body, the left and right variable side front edges are respectively denoted as a left variable side front edge and a right variable side front edge; step two, determining a front edge line of the wave-riding body; step three, determining the height and curvature of the upper surface of the wave-riding body; step four, determining the maximum distance from the upper surface of the wave-riding body to the lower surface of the fixed section aircraft body; and step five, designing the variable side front edges; the application greatly adjusts the lift-drag ratio of the wave-riding aircraft body, improves the utilization rate of the internal volume of the aircraft, and makes the wave-riding aircraft have comprehensive maneuvering characteristics of pitching, yawing and rolling by using a simple rotating deformation mechanism.

Description

Technical Field

[0001] This invention patent belongs to the category of high Mach number gliding waverider aircraft, and relates to a gliding waverider aircraft with high maneuverability. Background Technology

[0002] Due to the existence of the lift-to-drag ratio limit formula, conventional aircraft face a lift-to-drag ratio barrier during hypersonic flight, limiting the achievable lift-to-drag ratio. To achieve a higher lift-to-drag ratio, the waverider configuration was developed. This type of lifting body has an appendage shock wave at its leading edge. Because the high-pressure airflow behind the wave below the waverider is constrained between the lower surface and the appendage shock wave, preventing communication with the low-pressure airflow above, a high pressure difference can be maintained between the upper and lower surfaces of the waverider, greatly improving the lift-to-drag ratio, hence the term "waveriding" flight. The earliest "Λ" waverider was proposed by Nonweiler in 1959. However, because it is based on a two-dimensional planar shock wave flow field, its space utilization is low, limiting its application potential in practical aircraft. To improve the space utilization of waveriders, many waveriders based on three-dimensional reference flow fields have emerged, among which the conical waverider is the most widely used.

[0003] Glide-wave-rider aircraft operate without power. During the gliding phase, a high lift-to-drag ratio is required to increase range, while a low lift-to-drag ratio is needed for rapid and precise strikes during the terminal dive phase. After booster separation, the aircraft can further adjust its trajectory by changing its lift-to-drag ratio, resulting in excellent maneuverability and significantly increasing the difficulty of interception. Therefore, variable lift-to-drag ratio technology is a crucial development requirement for achieving highly maneuverable aircraft control characteristics.

[0004] Traditional glider waverider aircraft typically lack deformable structures, exhibiting only fixed motion patterns and trajectories. This makes it difficult to meet the high maneuverability requirements of modern hypersonic vehicles and the multi-mission, multi-environment design needs of next-generation aerospace vehicles. While some glider aircraft can perform maneuvers such as yaw, pitch, and roll using aerodynamic rudders, the presence of these rudders not only increases the aircraft's size but also makes it difficult to significantly alter the lift-to-drag ratio of the waverider. Summary of the Invention

[0005] Purpose of the invention: To address the problems of limited lift-to-drag ratio, low maneuverability, and low internal volume utilization in existing gliding waverider aircraft, this invention provides a gliding waverider aircraft with high maneuverability and a design method.

[0006] This invention proposes a gliding waverider with high maneuverability to replace the traditional fixed-geometry, fixed-trajectory gliding waverider. The core of this invention lies in significantly adjusting the lift-to-drag ratio of the waverider airframe and improving the internal volume utilization by designing the deformable profile of the leading edge of the variant. Utilizing a simple rotational deformation mechanism, the waverider exhibits integrated pitch, yaw, and roll maneuverability, making the flight trajectory of the new waverider gliding unpredictable and achieving the required high maneuverability. During the leading edge deformation process, the airframe remains strictly enclosed, with no interference between components, ensuring a certain level of stability and reliability.

[0007] Technical solution: A design method for a gliding waverider with high maneuverability, the design method comprising the following steps:

[0008] Step 1: Select a conical waverider as the basic configuration of the aircraft. The waverider includes a fixed section fuselage and variant leading edges located on the left and right sides of the fixed section fuselage. The variant leading edges can be rotated into the fixed section fuselage. The variant leading edges on the left and right sides are respectively referred to as the left variant leading edge and the right variant leading edge.

[0009] Step 2: Determine the leading edge of the waverider;

[0010] Step 3: Determine the height and curvature of the upper surface of the waverider;

[0011] Step 4: Determine the maximum distance from the upper surface of the waverider to the lower surface of the fixed section of the waverider body;

[0012] Step 5: Design the variant side leading edge. The design methods for the left and right variant side leading edges are the same. The design steps for the left variant side leading edge are as follows:

[0013] Step 1) Initially determine the shapes of the upper and lower surfaces of the left variant's leading edge;

[0014] Step 2) Determine the axis of rotation of the leading edge of the left variant side;

[0015] Step 3) Based on the lift-to-drag ratio improvement requirements, design the vertical projection dimensions of the variant side leading edge;

[0016] Step 4) Determine the position of the rotation axis on the fuselage based on the vertical projection dimensions of the left variant side leading edge;

[0017] Step 5) Constrain the relationship between the lengths of the leading edges of the left variant side;

[0018] Step 6) Determine the rotation range of the left variant side leading edge.

[0019] Furthermore, the method for determining the leading edge line of the waverider in step two is as follows:

[0020] Given the reference cone angle, angle of attack, and generatrix profile of the waverider, a Cartesian coordinate system is used, with x representing the flow direction, y representing the vertical direction, and z representing the transverse direction, to obtain the conical reference flow field and generate a conical shock surface. The conical shock surface is transversely cut by a cutting plane parallel to the incoming flow direction, and the intersection of the two planes is the leading edge line CMI of the waverider, where M is the leading edge point, and C and I are the trailing edge points, respectively. The straight-line distance of CI is the width W of the waverider.

[0021] Furthermore, the method for determining the height and curvature of the upper surface of the waverider in step three is as follows:

[0022] The upper surface of the waverider is designed using a geometric transition. Given the leading edge line, the height and curvature of the upper surface are set according to the internal loading requirements of the waverider, while ensuring that the upper surface is smooth and continuous. Assuming that point E is the highest point of the upper surface of the waverider, the upper surface of the waverider is denoted as CMIE. Here, ME is an outwardly convex spline curve, and the tangent direction of point E along the incoming flow direction is parallel to the X-axis. CEI is the trailing edge line of the upper surface of the waverider. CEI is an outwardly convex spline curve that is continuous and smooth. The tangent direction of point E is parallel to the transverse Z-axis, and the slope is 0. The distance from point E to the line containing CI is the height H of the upper surface of the waverider, where H is the height of the waverider.

[0023] Furthermore, the method for determining the maximum distance from the upper surface of the waverider to the lower surface of the fixed section of the waverider body in step four is as follows:

[0024] Assume the lower surface of the fixed section of the body is surface DMGF, which is obtained by streamline tracing the leading edge in the reference flow field; where DG is the trailing edge of the lower surface of the fixed section of the body, DG is approximately a straight line, and F is the midpoint of DG; the distance from point E to point F is the maximum distance h from the upper surface of the waverider to the lower surface of the fixed section of the waverider body; the straight-line distance from point M to F is the length L of the waverider.

[0025] Furthermore, the design steps for the left variant's leading edge are as follows:

[0026] Step 1) Initially determine the shapes of the upper and lower surfaces of the variant's leading edge;

[0027] The leading edge of the variant side is designed as a conical structure. Assuming the upper surface of the left variant side leading edge is CAB, in order to ensure the closure of the entire upper surface of the waverider, point A is on the leading edge line CM on the left side of the waverider, and point B is on the trailing edge line CEI on the upper surface of the waverider.

[0028] To ensure the closure of the lower surface of the waverider, the lower surface of the left variant side leading edge is a surface CAD, and the lower surface CAD is a conical surface. The trailing edge curve CD is an arc with B as the center and BC as the radius.

[0029] Step 2) Select AB as the axis of rotation for the leading edge of the left variant side;

[0030] Step 3) Based on the lift-to-drag ratio improvement requirements, design the vertical projection dimensions of the variant's leading edge; the specific steps are as follows:

[0031] ① Given that the overall length of the body is L, the width is W, and the height is H, the slenderness ratio (L / W) of the body is controlled between 1.8 and 3.0; the vertical projection width of the variant's leading edge changes by w in both the extended and retracted states. d w d Let be the distance between points B and C along the horizontal Z-axis; the vertical projection length is l, where l is the distance from point A to the bottom profile surface BCD of the left variant side leading edge;

[0032] ②Based on the lift-to-drag ratio adjustment rate requirement, the change in vertical projected area ΔS before and after rotation of the leading edge of the variant sides can be determined. ΔS = 2 * 0.5 * l * w d Then according to w d From the proportional relationship with l, we can know w d / W and l / L;

[0033] ③ Given L, W, w d / W and l / L, calculate w d and l;

[0034] Step 4) Determine the position of the rotation axis on the fuselage based on the vertical projection dimensions of the left variant side leading edge;

[0035] Given the vertical projection length l and vertical projection width w of the left variant's leading edge. d Given that the angle between line BC and the horizontal Z-axis is 45° < θ < 90°, we can know the specific position of point A on the leading edge line, the specific position of point B on the trailing edge line of the upper surface, and the specific vertical distance of point B from the trailing end point C of the leading edge line is h1.

[0036] Step 5) Constrain the relationship between the lengths of the leading edges of the left variant side;

[0037] The trailing edge curve CD is an arc with B as the center and BC as the radius. Then the straight line BC and BD are of equal length. The straight lines AC and AD are designed to be of equal length. At the same time, in order to avoid interference between the variant side leading edge and the upper surface when it is fully retracted, when the BC side rotates to the position of the BD side, then ∠CBD < 90°. Under the above conditions, the position of point D is determined.

[0038] Step 6) Determine the rotation range of the left variant's leading edge;

[0039] The angle at which the leading edge of the left variant rotates inward from the unfolded state. To ensure that the leading edge of the left variant does not interfere with the upper surface when it rotates into the body, and to maintain the body's sealing properties, then

[0040] Furthermore, in step 5), ∠CBD is taken as 70°~80°.

[0041] Beneficial effects:

[0042] (1) The present invention improves the structure of the traditional conical waverider by making the side leading edge of the waverider into a variant structure and adopting a simple rotational deformation mechanism. Without increasing the size of the aircraft or sacrificing the internal loading space, the narrow unloading space at the edge of the waverider is fully utilized, thereby improving the utilization rate of the internal space of the aircraft.

[0043] (2) At the same time, the new type of gliding waverider can change its configuration. When the variant side leading edge is deployed, the high pressure area on the lower surface and the low pressure area on the upper surface are closed, and the aircraft has a large lift-to-drag ratio. After the variant side leading edge rotates into the body, the high and low pressure areas on the upper and lower surfaces generate overflow, which greatly reduces the lift-to-drag ratio of the body.

[0044] (3) By adjusting the degree of rotation of the leading edge of the two variant sides into the fuselage, the aircraft can have comprehensive maneuverability of pitch, yaw and roll. The entire fuselage is closed and complete, without structural interference, and can achieve stepless adjustment of lift-to-drag ratio, with high maneuverability characteristics. Attached Figure Description

[0045] Figure 1 This is a schematic diagram of a gliding waverider aircraft. The dotted lines in the diagram represent the leading edge of a variant of the waverider aircraft.

[0046] Figure 2 This is a schematic diagram of the leading edge line generated by the waverider.

[0047] Figure 3 This is a side view illustration of the reference cone.

[0048] Figure 4 This is a top-view diagram showing the dimensions of a gliding waverider.

[0049] Figure 5 This is a rear-view dimension diagram of a gliding waverider.

[0050] Figure 6a A schematic diagram showing the full extension of the leading edge of the variant;

[0051] Figure 6b A schematic diagram of pitch adjustment for symmetrical rotation of the variant's leading edge (hollow arrows indicate the rotation direction of the variant's leading edge, and solid arrows indicate the adjustment direction of the fuselage);

[0052] Figure 6c A schematic diagram of yaw and roll integrated adjustment for asymmetric rotation of the variant's leading edge;

[0053] Figure 6d This is a schematic diagram showing the complete contraction of the anterior edge of the variant. Detailed Implementation

[0054] The technical solution of the present invention will be described in detail below with reference to the accompanying drawings; however, the scope of protection of the present invention is not limited to the embodiments described.

[0055] This invention discloses a gliding waverider with high maneuverability and its design method, the design method comprising the following steps:

[0056] Step 1: Select a conical waverider as the basic configuration of the aircraft. The waverider includes a fixed section fuselage and variant leading edges located on the left and right sides of the fixed section fuselage. The variant leading edges can be rotated into the fixed section fuselage. The variant leading edges on the left and right sides are respectively referred to as the left variant leading edge and the right variant leading edge.

[0057] like Figure 1 As shown, when the two variant leading edges unfold, the upper surface BAMNH of the fixed section body, the upper surface CAB of the left variant leading edge, and the upper surface INH of the right variant leading edge constitute the upper surface of the entire waverider; the lower surface DAMNG of the fixed section body, the lower surface CAD of the left variant leading edge, and the lower surface ING of the right variant leading edge constitute the lower surface of the entire waverider.

[0058] Step 2: Determine the leading edge of the waverider;

[0059] In the design process of a waverider, the reference cone on which the waverider is located is solved. Given the cone angle, angle of attack and generatrix profile of the reference cone, the cone-shaped reference flow field is obtained, and a conical shock surface is generated. The conical shock surface is transversely cut by a cutting plane parallel to the incoming flow direction, and the intersection of the two surfaces is the leading edge line of the waverider.

[0060] like Figure 1 , Figure 2 , Figure 3 , Figure 4 As shown, the angle of attack of the reference cone (the angle between the reference cone and the direction of the incoming flow), the cone angle, and the generatrix profile are known. A Cartesian coordinate system is used, with x representing the flow direction, y representing the vertical direction, and z representing the transverse direction. A conical shock surface is generated from the reference cone. This conical shock surface is transversely cut by a plane parallel to the direction of the incoming flow. The intersection line CMI of the two planes is the leading edge line of the waverider, where M is the leading edge point, and C and I are the trailing edge points. The straight-line distance of CI is the width W of the waverider.

[0061] The leading edge line (CMI) is also the intersection of the upper and lower surfaces of the waverider. The leading edge line can separate the high-pressure region after the shock wave on the lower surface from the low-pressure region on the upper surface, thereby generating greater lift. Different conical flow fields can be obtained by changing the cone angle, generatrix curvature, and angle of attack of the reference cone, resulting in a variety of leading edge lines. The leading edge line in this embodiment is only one example.

[0062] Step 3: Determine the height and curvature of the upper surface of the waverider;

[0063] The upper surface of the waverider is designed using a geometric transition. Given the leading edge line, the height and curvature of the upper surface are set according to the internal loading requirements of the waverider. At the same time, it is necessary to ensure that the upper surface of the aircraft is smooth and continuous.

[0064] In this embodiment, the upper surface of the waverider is designed as follows: Figure 1 , Figure 5 As shown in the diagram, assuming point E is the highest point on the upper surface of the waverider, the upper surface of the waverider is denoted as CMIE, where ME is an outwardly convex spline curve, and the tangent direction of point E in the direction of the incoming flow (i.e., the X-axis direction) is parallel to the X-axis; CEI is the trailing edge line of the upper surface of the waverider, and CEI is an outwardly convex spline curve that is continuous and smooth, where the tangent direction of point E is parallel to the transverse Z-axis and has a slope of 0; the distance from point E to the line containing CI is the height of the upper surface of the waverider, which is H, and H is also the height of the waverider.

[0065] Step 4: Determine the maximum distance from the upper surface of the waverider to the lower surface of the fixed section of the waverider body;

[0066] The lower surface of the waverider includes the lower surface of the fixed section body and the lower surfaces of the two variant side leading edges. The lower surface of the fixed section body and the lower surfaces of the two variant side leading edges are closely connected to ensure the sealing of the entire lower surface of the waverider.

[0067] like Figure 1 In this context, it is assumed that the lower surface of the fixed section of the body is a surface DMGF, which is obtained by streamline tracing the leading edge in the reference flow field (Wang Qingwen. Design of a two-stage waverider based on the kissing theory [D]. National University of Defense Technology, 2015). Here, DG is the trailing edge of the lower surface of the fixed section of the body, which is approximately a straight line, and F is the midpoint of DG. The distance from point E to point F is the maximum distance h from the upper surface of the waverider to the lower surface of the fixed section of the body. The straight-line distance from point M to F is the length L of the waverider.

[0068] Step 5: Design the variant side leading edge; the design methods for the left and right variant side leading edges are the same; taking the design of the left variant side leading edge as an example, the specific design steps are as follows:

[0069] Step 1) Initially determine the shapes of the upper and lower surfaces of the left variant's leading edge;

[0070] The present invention designs the variant side leading edge as a conical structure; assuming the upper surface of the left variant side leading edge is CAB, in order to ensure the closure of the entire upper surface of the waverider, point A needs to be on the leading edge line CM on the left side of the waverider, and point B needs to be on the trailing edge line CEI on the upper surface of the waverider.

[0071] To ensure the sealing of the lower surface of the waverider, the lower surface of the left variant side leading edge is CAD, and the trailing edge curve CD is an arc with B as the center and BC as the radius; the lower surface CAD is a conical surface to ensure the sealing of the body when the variant part deforms.

[0072] Step 2) Determine the axis of rotation of the leading edge of the left variant side;

[0073] AB is chosen as the axis of rotation; AB is the edge of the front part of the variant. Using AB as the axis of rotation can ensure the continuity and integrity of the entire body; with AB as the axis, the lower surface ACD of the variant can be rotated, and the entire lower surface is seamlessly connected and strictly sealed.

[0074] Step 3) Based on the lift-to-drag ratio improvement requirements, design the vertical projection dimensions of the variant side leading edge;

[0075] ①Given that the overall length of the body is L, the width is W, and the height is H, the slenderness ratio (L / W) of the body is typically controlled between 1.8 and 3.0; the vertical projection width of the variant's leading edge changes by w in both the extended and retracted states. d The vertical projection length is l; w d Let l be the distance between points B and C in the horizontal Z-axis direction, and l be approximately the distance from point A to the bottom profile surface BCD of the left variant side leading edge;

[0076] The slenderness ratio of an airframe is typically controlled between 1.8 and 3.0. A higher slenderness ratio helps reduce aerodynamic drag during flight and improve lift efficiency. However, an excessively high slenderness ratio increases the difficulty of maneuverability and instability. The illustrated slenderness ratio is around 2.0. Furthermore, the slenderness ratio is closely related to the reference flow field; the slenderness ratio of a waverider airframe is slightly lower than that of a conical flow field. The conical flow field, in turn, is related to the angle of attack, cone angle, generatrix, and incoming flow velocity of the reference cone. Therefore, for the waverider described in this patent, the slenderness ratio is typically controlled between 1.8 and 3.0.

[0077] ②Based on the lift-to-drag ratio adjustment rate requirement, the change in vertical projected area ΔS before and after rotation of the leading edge of the variant sides can be determined (ΔS = 2 * 0.5 * l * w). d ), and then according to w d From the proportional relationship with l, we can know w d / W and l / L;

[0078] ③Because L, W, w dGiven / W and l / L, w can be calculated. d and l.

[0079] In this embodiment, the lift-to-drag ratio adjustment range of the waverider before and after deformation is set to 0-10%. Based on this requirement, the change in vertical projected area when the two variant leading edges expand and contract is ΔS, where ΔS = 2 * 0.5 * l * lw d Among them, w d / l×100% is controlled between 3% and 10%. The w in this design d / W×100% should be controlled at 4%–15%, and l / L×100% should be controlled at 50%–80%.

[0080] Step 4) Determine the position of the rotation axis on the fuselage based on the vertical projection dimensions of the left variant side leading edge;

[0081] Given the vertical projection length l and vertical projection width w of the left variant's leading edge. d From this, we can know that point A is located on the leading edge line, point B is located on the trailing edge line of the upper surface, and the vertical distance from point B to the trailing end point C of the leading edge line is h1.

[0082] Specifically, the position of point A on the leading edge line can be determined by the vertical projection length *l* of the left variant's leading edge, and the change in vertical projection width of the variant's leading edge is *w*. d The position of point B on the trailing edge of the upper surface can be determined, and the vertical distance from point B to the trailing endpoint C of the leading edge is h1. Additionally, it must be ensured that the angle between line BC and the transverse Z-axis is 45° < θ < 90° (see...). Figure 5 θ > 45° is to prevent the leading edge of the variant side from interfering with the interior of the body in the fully retracted state, and θ < 90° is to avoid the upper surface profile protruding from the shock wave surface, ensuring the smoothness and low drag characteristics of the body.

[0083] Step 5) Constrain the relationship between the lengths of the leading edges of the left variant side;

[0084] When the variant's leading edge rotates into the body, in order to ensure the body closes well, the trailing edge curve CD is an arc with B as the center and BC as the radius. The straight lines BC and BD need to be of equal length; the straight lines AC and AD also need to be of equal length. At the same time, in order to avoid interference between the variant's leading edge and the upper surface when it is fully retracted, when the BC side rotates to the position of the BD side, it must be ensured that ∠CBD < 90°. Generally, ∠CBD can be taken as 70° to 80°. In this embodiment, ∠CBD = 80° is taken. Under these constraints, the position of point D can be determined.

[0085] Under the condition of ensuring no interference, the larger the ∠CBD angle, the better, which means that the range of rotation adjustment of the variant's leading edge is larger.

[0086] Step 6) Determine the rotation range of the left variant's leading edge;

[0087] The angle at which the leading edge of the left variant rotates inward from the unfolded state. To ensure that the leading edge of the left variant does not interfere with the upper surface when it rotates into the body, and to maintain the body's sealing properties, then

[0088] Figures 6a to 6d This is a schematic diagram of the transformation process of a gliding waverider, showing the angle at which the leading edge of the variant rotates inward from the unfolded state. like Figure 6a and 6d As shown. The aircraft designed using the method of this invention has high maneuverability, such as... Figure 6b As shown, by adjusting the symmetrical angle of the leading edges at both ends, the lift-to-drag ratio of the aircraft can be changed, thus achieving controllable pitch maneuverability. Figure 6c As shown, by adjusting the asymmetric angle of the leading edges at both ends, the lift characteristics of the aircraft on one side can be changed, and the combined yaw and roll maneuverability can be controlled.

[0089] Side leading edge deformation mechanism: By retracting and extending the variant side leading edge around the axis, its relative position with the conical waverider and the corresponding aerodynamic characteristics can be adjusted. This can achieve both wide-range adjustable overall lift characteristics (enhancing pitch maneuverability) and flexible adjustable unilateral lift characteristics (enhancing yaw and roll combined maneuverability). Furthermore, the integrated design concept of the waverider / variant side leading edge in this patent ensures that the movable side leading edge has a good storage effect within the airframe, which can increase the utilization rate of the airframe's internal space.

[0090] The variant leading edge of this invention was verified. The design parameters were selected as Mach 7 and altitude 24 km. The results are as follows: 1) With the variant leading edge deployed, the lift-to-drag ratio of the waverider varies from 0 to 10% within the angle of attack range of 0–8°. The waverider can increase its flight range at a high lift-to-drag ratio and can carry out rapid and precise strikes at a low lift-to-drag ratio. 2) It possesses integrated pitch, yaw, and roll maneuverability, giving the aircraft high maneuverability. 3) The effective volumetric efficiency η of the waverider airframe can reach as high as 49.3%.

[0091] This invention improves upon the traditional conical waverider structure by creating a variant structure for the leading edge of the waverider. Employing a simple rotational deformation mechanism, it fully utilizes the narrow, unfillable space at the waverider's edge without increasing the aircraft's size or sacrificing internal loading space, thus enhancing the utilization rate of the aircraft's internal space. Simultaneously, the novel gliding waverider can change its configuration. With the variant leading edge extended, the high-pressure area on the lower surface and the low-pressure area on the upper surface are closed, resulting in a high lift-to-drag ratio. After the variant leading edge rotates and contracts, overflow occurs in the high and low-pressure areas on both surfaces, significantly reducing the lift-to-drag ratio. By adjusting the degree of contraction of the two variant leading edges, the aircraft can achieve integrated pitch, yaw, and roll maneuverability. Furthermore, the entire airframe is completely enclosed and free of structural interference, allowing for stepless adjustment of the lift-to-drag ratio and exhibiting highly maneuverable characteristics.

[0092] As described above, although the invention has been shown and described with reference to specific preferred embodiments, it should not be construed as limiting the invention itself. Various changes in form and detail may be made without departing from the spirit and scope of the invention as defined in the appended claims.

Claims

1. A design method for a gliding waverider aircraft with high maneuverability, characterized in that, The design method includes the following steps: Step 1: Select a conical waverider as the basic configuration of the aircraft. The waverider includes a fixed section fuselage and variant leading edges located on the left and right sides of the fixed section fuselage. The variant leading edges can be rotated into the fixed section fuselage. The variant leading edges on the left and right sides are respectively referred to as the left variant leading edge and the right variant leading edge. Step 2: Determine the leading edge of the waverider; Step 3: Determine the height and curvature of the upper surface of the waverider; Step 4: Determine the maximum distance from the upper surface of the waverider to the lower surface of the fixed section of the waverider body; Step 5: Design the variant side leading edge. The design methods for the left and right variant side leading edges are the same. The design steps for the left variant side leading edge are as follows: Step 1) Initially determine the shapes of the upper and lower surfaces of the left variant's leading edge; Step 2) Determine the axis of rotation of the leading edge of the left variant side; Step 3) Based on the lift-to-drag ratio improvement requirements, design the vertical projection dimensions of the variant side leading edge; Step 4) Determine the position of the rotation axis on the fuselage based on the vertical projection dimensions of the left variant side leading edge; Step 5) Constrain the relationship between the lengths of the leading edges of the left variant side; Step 6) Determine the rotation range of the left variant side leading edge.

2. The design method for a gliding waverider with high maneuverability according to claim 1, characterized in that, The method for determining the leading edge of the waverider in step two is as follows: Given the reference cone angle, angle of attack, and generatrix profile of the conical waverider, a conical reference flow field is obtained using a Cartesian coordinate system, with x representing the flow direction, y representing the vertical direction, and z representing the transverse direction, generating a conical shock surface. The conical shock surface is transversely cut by a cutting plane parallel to the incoming flow direction, and the intersection of the two planes is the leading edge line CMI of the waverider, where M is the leading edge point, and C and I are the trailing edge points, respectively. The straight-line distance CI is the width W of the waverider.

3. The design method for a gliding waverider aircraft with high maneuverability according to claim 2, characterized in that, The method for determining the height and curvature of the upper surface of the waverider in step three is as follows: The upper surface of the waverider is designed with a geometric transition. Given the leading edge line, the height and curvature of the upper surface are set according to the internal loading requirements of the waverider, while ensuring that the upper surface of the aircraft is smooth and continuous. Assuming point E is the highest point on the upper surface of the waverider, the upper surface of the waverider is denoted as CMIE; where ME is an outwardly convex spline curve, and the tangent direction of point E along the incoming flow direction is parallel to the X-axis; CEI is the trailing edge line of the upper surface of the waverider, and CEI is an outwardly convex spline curve that is continuous and smooth, where the tangent direction of point E is parallel to the transverse Z-axis and has a slope of 0; the distance from point E to the line containing CI is the height H of the upper surface of the waverider, where H is the height of the waverider.

4. The design method for a gliding waverider with high maneuverability according to claim 3, characterized in that, The method for determining the maximum distance from the upper surface of the waverider to the lower surface of the fixed section of the waverider body in step four is as follows: Assume the lower surface of the fixed section of the body is surface DMGF, which is obtained by streamline tracing the leading edge in the reference flow field; where DG is the trailing edge of the lower surface of the fixed section of the body, DG is approximately a straight line, and F is the midpoint of DG; the distance from point E to point F is the maximum distance h from the upper surface of the waverider to the lower surface of the fixed section of the waverider body; the straight-line distance from point M to F is the length L of the waverider.

5. The design method for a gliding waverider with high maneuverability according to claim 4, characterized in that, The design steps for the left variant's leading edge are as follows: Step 1) Initially determine the shapes of the upper and lower surfaces of the variant's leading edge; The leading edge of the variant is designed as a conical structure. Assuming the upper surface of the left variant leading edge is CAB, in order to ensure the closure of the entire upper surface of the waverider, point A is on the leading edge line CM on the left side of the waverider, and point B is on the trailing edge line CEI on the upper surface of the waverider. To ensure the closure of the lower surface of the waverider, the lower surface of the left variant side leading edge is a surface CAD, and the lower surface CAD is a conical surface. The trailing edge curve CD is an arc with B as the center and BC as the radius. Step 2) Select AB as the axis of rotation for the leading edge of the left variant side; Step 3) Based on the lift-to-drag ratio improvement requirements, design the vertical projection dimensions of the variant's leading edge; the specific steps are as follows: ① Given that the overall length of the body is L, the width is W, and the height is H, the slenderness ratio (L / W) of the body is controlled between 1.8 and 3.0; the vertical projection width of the variant's leading edge changes by w in both the extended and retracted states. d w d Let be the distance between points B and C along the horizontal Z-axis; the vertical projection length is l, where l is the distance from point A to the bottom profile surface BCD of the left variant side leading edge; ②Based on the lift-to-drag ratio adjustment rate requirement, the change in vertical projected area ΔS before and after rotation of the leading edge of the variant sides can be determined. ΔS = 2 * 0.5 * l * w d Then according to w d From the proportional relationship with l, we can know w d / W and l / L; ③ Given L, W, w d / W and l / L, calculate w d and l; Step 4) Determine the position of the rotation axis on the fuselage based on the vertical projection dimensions of the left variant side leading edge; Given the vertical projection length l and vertical projection width w of the left variant's leading edge. d Given that the angle between line BC and the horizontal Z-axis is 45° < θ < 90°, we can know the specific position of point A on the leading edge line, the specific position of point B on the trailing edge line of the upper surface, and the specific vertical distance of point B from the trailing end point C of the leading edge line is h1. Step 5) Constrain the relationship between the lengths of the leading edges of the left variant side; The trailing edge curve CD is an arc with B as the center and BC as the radius. Then the straight line BC and BD are of equal length. The straight lines AC and AD are designed to be of equal length. At the same time, in order to avoid interference between the variant side leading edge and the upper surface when it is fully retracted, when the BC side rotates to the position of the BD side, then ∠CBD < 90°. Under the above conditions, the position of point D is determined. Step 6) Determine the rotation range of the left variant's leading edge; The angle at which the leading edge of the left variant rotates inward from the unfolded state. To ensure that the leading edge of the left variant does not interfere with the upper surface when it rotates into the body, and to maintain the body's sealing properties, then 6. The design method for a gliding waverider with high maneuverability according to claim 5, characterized in that, In step 5), ∠CBD is taken as 70°~80°.

7. An aircraft designed using the high maneuverability and control characteristics of a gliding waverider aircraft as described in any one of claims 1-6.

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