CN111152909A - Projection method based double-sweepback waverider design method for determining plane shape - Google Patents
Projection method based double-sweepback waverider design method for determining plane shape Download PDFInfo
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Abstract
The invention provides a projection method-based design method of a double-sweepback waverider with a fixed plane shape. The double-sweepback wave rider generated by the invention has the wave rider characteristic and the large attack angle nonlinear lift force at high speed, the lift force is increased by 22.41% at an attack angle of 20 degrees, the lift-drag ratio reaches 7 at low speed, the vortex effect is realized to improve the lift-drag ratio, and the aerodynamic performance of a wide speed range is realized.
Description
Technical Field
The invention relates to the field of pneumatic design of hypersonic aircraft, in particular to a projection method-based design method of a double-backswept waverider with a fixed plane shape.
Background
In the development history of the aircraft, the lift-drag ratio is one of important comprehensive technical indexes for evaluating the aircraft, and the continuous improvement of the lift-drag ratio of the aircraft is a continuous pursuit of researchers in the aerospace field. The aerodynamic appearance development of the aircraft successively experiences three main appearances of a revolution body, a lifting body and a waverider, and one of main powers for promoting the development of the aircraft is high lift-drag ratio. Through statistical analysis of various aircraft which are successfully designed at that time, an empirical formula of the maximum lift-drag ratio changing along with the flight Mach number is established in Kuchemann:
analysis of the formula shows that the maximum lift-drag ratio is monotonically decreased with increasing flight Mach number, and when the Mach number is infinite, the maximum lift-drag ratio is only 4, which is the lift-drag ratio barrier of the hypersonic aircraft. The front edge shock wave generated by the conventional hypersonic speed aircraft is disjunctive, and high-pressure airflow on the lower surface leaks from the side edge to the upper surface, so that the pressure difference between the upper surface and the lower surface is reduced, and the lift-drag ratio is reduced. In 1959, professor Nonweile in UK firstly proposes a wave rider concept, aiming at breaking a lift-drag ratio barrier, and the wave rider enables high-pressure airflow not to leak to the upper surface by attaching shock waves, and the maximum lift-drag ratio empirical formula is shown through statistics:
it can be seen that the maximum lift-drag ratio of the waverider at hypersonic speed is improved by about 2 compared with the conventional profile. Through the development of scientists in past generations, the design method of the waverider has been developed to a plurality of methods in the present day in the early stage, and the performance of the method is not limited to the lift-drag ratio.
The wave multiplier has good pneumatic performance at a hypersonic speed, particularly in a design state, but does not have wave multiplication characteristics at a low speed, has a poor lift-drag ratio, and has great difficulty in engineering application when wide-speed-range flight is to be realized from zero-speed starting to hypersonic-speed flight. One effective solution is a double-sweepback design, and CFD verifies that a large lift-drag ratio exists at low speed, so that the method is an effective method for optimizing the pneumatic performance of the waverider at low speed.
Disclosure of Invention
The invention aims to provide a method for designing a double-backswept waverider with a fixed plane shape based on a projection method, which greatly improves the design difficulty and ensures that the appearance of the double-backswept waverider designed by the invention has better aerodynamic characteristics.
The technical scheme adopted by the invention is as follows: a method for designing a double-sweepback waverider with a fixed plane shape based on a projection method comprises the following steps:
step 1: designing wave rider parameters from an origin flow surface, a compression surface and a rear end surface perpendicular to an incoming flow direction;
step 2: the plane shape of a leading edge line of the waverider is designed to be a double-sweepback form, the leading edge line is provided with a first sweepback angle k1 and a second sweepback angle k2, the leading edge line of the first sweepback angle and the leading edge line of the second sweepback angle are connected through an arc for smooth transition, the head is designed to be in a circular arc shape, and when the radius of the arc is 0, the head is a pointed head;
and step 3: and (3) obtaining a zero-attack-angle conical shock wave reference flow field according to the design parameters in the step (1), placing the double-sweepback constant plane-shaped front edge line designed in the step (2) right below the flow field, and obtaining the front edge line with the double-sweepback characteristic on the conical shock wave by adopting an upward orthographic projection method.
And 4, step 4: dispersing the double-sweepback leading edge lines obtained in the step (3) by adopting a cone guided wave body design method to obtain point clouds, forming an upper surface streamline along the direction parallel to the free incoming flow by taking the point clouds as a starting point, wherein the intersection point of the upper surface streamline and a cut-off plane is the point cloud of the upper surface trailing edge line, the upper surface streamline is in smooth connection to form an upper surface with the free incoming flow, and the point cloud of the upper surface trailing edge line is in smooth connection to form an upper surface trailing edge line; and (3) taking the point cloud dispersed from the double-sweepback leading edge line obtained in the step (3) as a starting point, obtaining a lower surface streamline by adopting a streamline tracking method, wherein the intersection point of the lower surface streamline and a cut-off plane is the point cloud of the lower surface trailing edge line, the lower surface streamline is smoothly connected to form a lower surface with a compression surface, and the point cloud of the lower surface trailing edge line is smoothly connected to form the lower surface trailing edge line.
And 5: and (4) combining the leading edge line obtained in the step (3), the free incoming flow upper surface obtained in the step (4), the compressed lower surface, the upper surface trailing edge line and the lower surface trailing edge line to obtain the double-sweepback cone guided-wave body.
The invention also provides a projection method-based double-sweepback waverider with a fixed plane shape, which is obtained by adopting the design method.
It should be noted that the leading edge line of the waverider according to the present invention can be expressed by a plane geometric relationship, the plane geometric shape of the leading edge line is composed of a blunt (or pointed) end, a large back-swept angle (first back-swept angle) straight line segment, a smooth transition circular arc segment of the large back-swept angle straight line segment and the small back-swept angle straight line segment, and a small back-swept angle (second back-swept angle) straight line segment, the two-dimensional constant plane shape leading edge line is placed in a three-dimensional space flow field and projected onto a shock wave surface by a projection method, and the present invention takes a cone guided waverider as an example for explanation. The double-sweepback configuration projected on the conical shock wave surface still exists, the double-sweepback configuration is used as a leading edge line of the wave multiplication design, the upper surface is obtained by adopting free flow surface tracking, and the curved surface with the wave multiplication performance is obtained by adopting streamline tracking and is used as the lower surface.
The blunt area of the two-dimensional fixed plane shape front edge line has an arc angle equal to a large sweepback angle k1, the radius is R1, when R1 is equal to 0, the blunt area is a sharp point, and the starting end point is a wave-rider head cone vertex.
The backswept angle of the large backswept angle straight-line segment of the two-dimensional constant plane shape front edge line is k1 and is tangent with the blunt area circular arc.
The radian of a smooth transition circular arc section of a large sweep angle straight-line section and a small sweep angle straight-line section of the two-dimensional constant plane shape front edge line is equal to the difference k1-k2 between the large sweep angle k1 and the small sweep angle k2, and two ends of the circular arc are respectively tangent to the large sweep angle straight-line section and the small sweep angle straight-line section so as to ensure the smooth transition of the two straight-line sections with double sweep angles.
The sweepback angle of a small sweepback angle straight-line segment of the front edge line of the two-dimensional fixed plane shape is k2, the small sweepback angle straight-line segment is tangent to the smooth transition circular arc segment, and the other end of the small sweepback angle straight-line segment is positioned at the maximum spreading length point of the waverider.
Selecting a flow field incoming flow Mach number, a reference cone and a conical shock wave according to flight requirements of an aircraft, placing a two-dimensional constant plane-shaped double-sweepback leading edge line right below a three-dimensional conical shock wave flow field, and projecting the two-dimensional constant plane-shaped double-sweepback leading edge line to a conical shock wave surface in an upward horizontal mode to obtain a leading edge line obtained by projection on the conical shock wave surface, wherein the leading edge line also has the characteristic of double sweepback.
The invention has the beneficial effects that:
(1) in the existing design method of the double-sweepback waverider with the fixed plane shape, the design parameters such as double-sweepback angles, shock wave angles and the like have complex geometric relations.
In the embodiment of the invention, the planar shape of the leading edge line of the double-sweepback waverider is easy to design, the geometric expression is simple, compared with the traditional double-sweepback waverider design, the design parameters are independent of the half-shock angle and the streamline of the space flow field of the waverider to track the initial line, namely the capture flow pipe and the like, and the design method is more efficient; the design method of the double-sweepback leading edge line with the fixed plane shape is more flexible and efficient, and the generated double-sweepback wave-multiplying body has good pneumatic performance at low speed and high speed.
(2) In the embodiment of the invention, the smooth transition between the blunt area of the leading edge line and the leading edge line with double sweepback angles adopts the arc tangent with the straight line segment with large sweepback angle and the straight line segment with small sweepback angle, and has better smooth transition characteristic compared with the common method.
(3) In the embodiment of the invention, the front edge line of the waverider is obtained by projecting the fixed plane shape of the double-sweepback front edge line onto the conical shock wave surface, the upper surface is obtained by tracking the free flow surface, and the lower surface is a curved surface with waverider characteristics obtained by tracking the streamline. Giving out the geometrical relationship of the plane shape of the double-sweepback leading edge line of the waverider, placing the designed plane shape of the leading edge line right below the conical shock wave surface, projecting the plane shape of the leading edge line along the vertical upward direction, obtaining the leading edge line of the waverider on the conical shock wave surface, then generating the upper surface by adopting a free streamline method, generating the lower surface with the waverider characteristic by adopting streamline tracing, and finally obtaining the waverider with double sweepbacks.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only examples of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic diagram of a wave rider generated by a cone flow field according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a geometric relationship between front edge lines of a double-sweepback waverider for determining a plane shape according to an embodiment of the present invention;
FIG. 3 is a plan view of a dual sweepback waverider according to an embodiment of the present invention;
FIG. 4 is a double sweepback waverider of an embodiment of the present invention;
FIG. 5 is a pressure cloud plot of a double swept-back waverider half-mold of an embodiment of the present invention at an angle of attack of Mach 4 degrees 0.4;
FIG. 6 is a graph showing the variation of lift-drag ratio with angle of attack of a double-sweepback waverider at Mach 0.4 in accordance with the embodiment of the present invention;
FIG. 7 is a bottom pressure cloud of a double swept-back waverider half-mold in a design state at Mach 0 angle of attack of 5 in accordance with an embodiment of the present invention;
FIG. 8 is a variation curve of lift-drag ratio with angle of attack of a double-sweepback waverider at Mach 5 in the embodiment of the present invention;
fig. 9 is a curve of variation of lift coefficient with attack angle under mach 5 of the double-sweepback waverider in the embodiment of the present invention.
Reference numerals: 1-conical shock wave, 2-basic cone, 3-leading edge line, 4-cut-off plane, 5-upper surface trailing edge line, 6-lower surface trailing edge line and 7-shock wave outlet molded line.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, belong to the scope of the present invention.
The embodiment of the invention provides a projection method-based design method of a double-sweepback waverider with a fixed plane shape, which comprises the following steps:
step 1: the design has waverider parameters from the flow surface, the compression surface and the rear end surface perpendicular to the incoming flow direction.
Step 2: the plane shape of the front edge line of the wave multiplier is designed to be a double-sweepback form, the front edge line is provided with a first sweepback angle k1 and a second sweepback angle k2, the front edge line of the first sweepback angle and the front edge line of the second sweepback angle are connected through an arc for smooth transition, the head can be designed to be a circular arc form, and when the radius of the arc is 0, the head is a pointed head.
And step 3: and (3) obtaining a zero-attack-angle conical shock wave reference flow field according to the design parameters in the step (1), placing the double-sweepback constant plane-shaped front edge line designed in the step (2) right below the flow field, and obtaining the front edge line with the double-sweepback characteristic on the conical shock wave by adopting an upward orthographic projection method.
And 4, step 4: dispersing the double-sweepback leading edge lines obtained in the step (3) by adopting a cone guided wave body design method to obtain point clouds, forming an upper surface streamline along the direction parallel to the free incoming flow by taking the point clouds as a starting point, wherein the intersection point of the upper surface streamline and a cut-off plane is the point cloud of the upper surface trailing edge line, the upper surface streamline is in smooth connection to form an upper surface with the free incoming flow, and the point cloud of the upper surface trailing edge line is in smooth connection to form an upper surface trailing edge line; and (3) taking the point cloud dispersed from the double-sweepback leading edge line obtained in the step (3) as a starting point, obtaining a lower surface streamline by adopting a streamline tracking method, wherein the intersection point of the lower surface streamline and a cut-off plane is the point cloud of the lower surface trailing edge line, the lower surface streamline is smoothly connected to form a lower surface with a compression surface, and the point cloud of the lower surface trailing edge line is smoothly connected to form the lower surface trailing edge line.
And 5: and (4) combining the leading edge line obtained in the step (3), the free incoming flow upper surface obtained in the step (4), the compressed lower surface, the upper surface trailing edge line and the lower surface trailing edge line to obtain the double-sweepback cone guided-wave body.
Specific examples are given below
The design principle of the embodiment of the invention is as follows: expressing the shape of the leading edge of the waverider on a two-dimensional plane, wherein the length L and the width of the leading edge line are S, the blunt area is recorded as a first circular arc, and the straight line segment with a large sweepback angle is recorded as a straight line L1Between the straight-line segment with large sweep angle and the straight-line segment with small sweep angleThe smooth transition section is marked as a second arc section, and the straight section with the small sweepback angle is marked as a straight line L2. The distance between the cutoff plane and the starting point of the shock wave flow field is recorded as L0The two-dimensional front edge line plane is geometrically placed right below the shock wave flow field, the two-dimensional fixed plane front edge line symmetry axis and the symmetry flow field central axis are in the same symmetry vertical plane, then the projection method is adopted, the projection position of the front edge line is determined by the design parameter L0Determining that a plane front edge line is projected onto a conical shock wave to obtain a wave-rider front edge line, wherein the upper point of the front edge line is a streamline tracking starting point, the upper surface adopts a free streamline method, namely, a streamline is tracked to a conical section along a free incoming flow direction, and the flow field is a conical flow field and can be solved through a Taylor-Maccll flow control equation, and the control equation of the flow model consists of a gas dynamic equation and a non-rotation condition:
through research of relevant researchers, the wave rider configuration generated by adopting a hypersonic velocity small disturbance theory and a Taylor-Maccoll flow control equation method has no obvious difference. In the embodiment, the lower surface is generated by adopting a hypersonic small perturbation theory.
A blunt tip region. As shown in FIG. 1, the arc with radius R1 is tangent to the line L1, so the corresponding angle of the arc is k1Center of circle O1(0，L-R1) The coordinates on the arc are expressed as:
wherein theta is1Is a radius R1Clockwise rotating to k from the positive direction of the y axis of 0 DEG1Degree, i.e. theta1∈[0,k1]。
(II) obtaining the arc end point A (R) from the formula (1) by using the straight line segment with large sweep angle1sink1,(L-R1)+R1cosk1). Sweep angle k1Slope K of the straight line1＝-tank1Let it have a length of L1And the relation between X and Y coordinates on the straight line is as follows:
Y-(L-R1+R1cosk1)＝-(X-R1sink1)tank1(2)，
wherein X ∈ [ R ]1sink1,R1sink1+L1cosk1]，L1Are unknown parameters.
(III) a large sweep angle straight line segment, wherein the sweep angle is k2Slope K of the straight line2＝-tank2Let it have a length of L2And D (S,0) of the end point of the straight line, the relation between X and Y coordinates on the straight line is as follows:
Y＝-(X-S)tank2(3)，
wherein X is ∈ [ S-L ]2cosk2,S]，L2Are unknown parameters.
And (IV) obtaining B (R) from the formula (2) of a second arc segment, namely a smooth transition segment between the large-sweepback-angle straight-line segment and the small-sweepback-angle straight-line segment1sink1+L1cosk1,L-R1+R1cosk1-L1sink1) From the formula (3), C (S-L) can be obtained2cosk2,L2sink2). Radius CO2And a straight line L2Perpendicular, its slope
From the C point coordinate, radius CO2Slope and length R2Can obtain the center of a circle O2Coordinates are as follows:
XO2＝XC+K3*R2＝S-L2cosk2+R2sink2
YO2＝YC+K3*R2＝L2sink2+R2cosk2
thus, the radius is R2Center O of the arc of2(S-L2cosk2+R2sink2,L2sink2+R2cosk2) The arc angle is k1-k2Radius O2B is the initial direction, rotate k counterclockwise1-k2And when the distance reaches the point C, the coordinates on the arc are as follows:
wherein theta is2∈[270°-k1,270°-k2]。
(V) solving L by the geometric relation of four parts of the whole front edge line1，L2Length of (d). The following equation (4) can be obtained:
from (IV), B (R)1sink1+L1cosk1,L-R1+R1cosk1-L1sink1)，
C(S-L2cosk2,L2sink2)。
Therefore, the following can be obtained:
obtaining L by the resolution of the simultaneous (5) and (6)1、L2Then, the obtained L is separated1、L2The arc R is obtained by substituting in the formulas (1), (2), (3) and (4)1、R2And a straight line L1、L2The geometric relational expression of (1).
The design parameters L of the two-dimensional planar leading edge line are 1, S is 0.65, K1 is 75, K2 is 50, R1 is 0.05, and R2 is 0.1, and the resulting leading edge line is shown in fig. 3. Fig. 1 is a schematic diagram of a cone-guided wave-rider, in this embodiment, a double-sweepback wave-rider is generated by using the cone-guided theory, and the flow field parameters of the cone shock wave are as follows: the incoming flow velocity is Mach 5, referenceThe cone half cone angle is 5.6 degrees, the half shock wave angle is 13 degrees, and the cutoff plane is far away from the parameter L of the cone shock wave flow field head cone 07. Projecting the fixed-plane double-sweepback leading edge line shown in FIG. 3 to a conical shock wave flow field according to the design method of the waverider to obtain a corresponding waverider leading edge line, wherein the upper surface consists of free incoming flow lines passing through the leading edge line, and the lower surface is a curved surface with waverider characteristics obtained by performing streamline tracing by adopting a hypersonic small perturbation theory. The waverider generated by this method is shown in fig. 4.
In a flight environment with the speed of Mach 5 and the high speed of 30 kilometers, the double-sweepback cone guided wave body is subjected to pneumatic calculation by CFD, a graph of variation of lift-drag ratio with an attack angle is given in fig. 8, the maximum lift-drag ratio is 5.53 at an attack angle of 4 degrees, fig. 7 is a pressure cloud diagram of the double-sweepback cone guided wave body viewed from a cut-off plane in a design state at the attack angle of Mach 0 degree of 0.4, the airflow of the upper surface and the lower surface of the guided wave body is blocked by a front edge line, and only a very small amount of high-pressure airflow of the lower surface transversely leaks to the upper surface, so that the aircraft designed by the design method can be proved to have the waveriding characteristic. Fig. 9 shows a curve of the lift coefficient of the double-swept-back cone guided-multiplied wave body at mach 5 along with the change of the attack angle, a blue model curve is an actual curve of the multiplied wave body obtained by CFD calculation, a red linear dotted line is a theoretical linear curve, and the lift is seen to have nonlinear increment, and the increment is as high as 22.41% at an attack angle of 20 °.
Compared with a single-sweepback-angle wavebody, the double-sweepback wavebody has obvious performance advantage at low speed, so that the aerodynamic performance of the double-sweepback-angle wavebody under the state of 0.4 Mach and 0km height is calculated by CFD in the embodiment of the invention, and a curve of variation of lift-drag ratio of the double-sweepback-cone wavebody with the attack angle in the embodiment is shown in FIG. 6, so that the maximum lift-drag ratio of 7.2 at 4-degree attack angle is achieved, and the double-sweepback-angle wavebody has better low-speed performance. Fig. 5 shows a pressure cloud chart of the double-swept-back cone guided wave body of the embodiment at an attack angle of mach 4 ° in the case of 5, it can be seen that the double-swept-back cone guided wave body has an obvious vortex effect on a leading edge line, which is derived from the double-swept-back design, the design is similar to the layout of the strake wing, vortex can be induced by the large-swept-back leading wing in a low-speed state, and the vortex is enhanced by disturbance of the outer wing part, so that good aerodynamic performance at low speed is ensured, which is consistent with the double-swept-back cone guided wave body of the existing design method.
The embodiments of the invention are not described in detail, but are within the common general knowledge of a person skilled in the art.
The foregoing is considered as illustrative of the preferred embodiments of the invention and is not to be construed as limiting the invention in any way. Although the present invention has been described with reference to the preferred embodiments, it is not intended to be limited thereto. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention should fall within the protection scope of the technical scheme of the present invention, unless the technical spirit of the present invention departs from the content of the technical scheme of the present invention.
Claims (3)
1. A method for designing a double-sweepback waverider with a fixed plane shape based on a projection method is characterized by comprising the following steps of:
step 1: designing wave rider parameters from an origin flow surface, a compression surface and a rear end surface perpendicular to an incoming flow direction;
step 2: the plane shape of a leading edge line of the waverider is designed to be a double-sweepback form, the leading edge line is provided with a first sweepback angle k1 and a second sweepback angle k2, the leading edge line of the first sweepback angle and the leading edge line of the second sweepback angle are connected through an arc for smooth transition, the head is designed to be in a circular arc shape, and when the radius of the arc is 0, the head is a pointed head;
and step 3: obtaining a zero-attack-angle conical shock wave reference flow field according to the design parameters in the step 1, placing the double-sweepback constant plane-shaped front edge line designed in the step 2 right below the flow field, and obtaining a front edge line with double-sweepback characteristics on the conical shock wave by adopting an upward orthographic projection method;
and 4, step 4: dispersing the double-sweepback leading edge lines obtained in the step (3) by adopting a cone guided wave body design method to obtain point clouds, forming an upper surface streamline along the direction parallel to the free incoming flow by taking the point clouds as a starting point, wherein the intersection point of the upper surface streamline and a cut-off plane is the point cloud of the upper surface trailing edge line, the upper surface streamline is in smooth connection to form an upper surface with the free incoming flow, and the point cloud of the upper surface trailing edge line is in smooth connection to form an upper surface trailing edge line; taking the point cloud dispersed from the double-sweepback leading edge line obtained in the step 3 as a starting point, obtaining a lower surface streamline by adopting a streamline tracking method, wherein the intersection point of the lower surface streamline and a cut-off plane is the point cloud of a lower surface trailing edge line, the lower surface streamline is smoothly connected to form a lower surface with a compression surface, and the point cloud of the lower surface trailing edge line is smoothly connected to form a lower surface trailing edge line;
and 5: and (4) combining the leading edge line obtained in the step (3), the free incoming flow upper surface obtained in the step (4), the compressed lower surface, the upper surface trailing edge line and the lower surface trailing edge line to obtain the double-sweepback cone guided-multiplied wave body.
2. The method of claim 1, wherein the planar shape of the leading edge line has a combination of a first back sweep angle and a second back sweep angle, as shown in fig. 2 of the drawings.
3. A planform-fixed double-backswept waverider based on projection, characterized in that it is obtained by the design method as claimed in any of claims 1-2.
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| CN111688905A (en) * | 2020-06-10 | 2020-09-22 | 中国空气动力研究与发展中心 | Double-sweepback waverider design method for streamline tracking axial-symmetry curved surface conical flow field |
| CN112389626A (en) * | 2020-10-29 | 2021-02-23 | 中国航天空气动力技术研究院 | High super aerodynamic overall arrangement in integrative fixed wing span of sharp leading edge vortex |
| CN115231005A (en) * | 2022-09-24 | 2022-10-25 | 北京星途探索科技有限公司 | Locking and releasing device for wave-rider aircraft with vortex effect |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111688905A (en) * | 2020-06-10 | 2020-09-22 | 中国空气动力研究与发展中心 | Double-sweepback waverider design method for streamline tracking axial-symmetry curved surface conical flow field |
| CN111688905B (en) * | 2020-06-10 | 2023-03-24 | 中国空气动力研究与发展中心 | Double-sweepback waverider design method for streamline tracking axial-symmetry curved surface conical flow field |
| CN112389626A (en) * | 2020-10-29 | 2021-02-23 | 中国航天空气动力技术研究院 | High super aerodynamic overall arrangement in integrative fixed wing span of sharp leading edge vortex |
| CN115231005A (en) * | 2022-09-24 | 2022-10-25 | 北京星途探索科技有限公司 | Locking and releasing device for wave-rider aircraft with vortex effect |
| CN115231005B (en) * | 2022-09-24 | 2022-12-20 | 北京星途探索科技有限公司 | Locking and releasing device for wave-rider aircraft with vortex wave effect |
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