CN112340014A - Inner-outer flow decoupling double-waverider high-speed air suction type aircraft and generation method thereof - Google Patents
Inner-outer flow decoupling double-waverider high-speed air suction type aircraft and generation method thereof Download PDFInfo
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Abstract
The invention relates to an internal and external flow decoupling double-waverider high-speed air suction type aircraft, which comprises an aircraft body, wherein the upper surface of the aircraft body is a Bump precursor, the lower surface of the aircraft body is a waverider with a high volume ratio, an air inlet channel, a combustion chamber and a spray pipe are arranged in the aircraft body, and the air inlet channel is an internal waverider with a high external compression ratio. According to the double-waverider high-speed air suction type aircraft with the decoupled internal and external flows, the air inlet channel and the waverider are respectively arranged on the upper side and the lower side of the aircraft body, and the pneumatic decoupling of a waverider flow field and an inlet flow field of the air inlet channel is realized through the decoupling on the geometric layout, so that the problems of low design efficiency and large external resistance of non-design points caused by strong coupling of the internal and external flows are avoided, and the pneumatic design efficiency of the high-speed air suction type aerospace craft is remarkably improved; the problems that the total balance weight/moment balance of the existing internal and external flow coupling aircraft is difficult, the thrust of the aircraft is reduced when the air inlet moves downwards, the flow direction arrangement range of the air inlet is limited, and the total length of the aircraft is limited are effectively solved.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an opposite-side double-waverider high-speed air suction type aircraft with internal and external flow decoupling and a generation method thereof.
Background
In the aspect of designing the aerodynamic profile of hypersonic aerospace power, the traditional aircraft needs to improve the lift characteristic by means of lifting wing load or flying attack angle, and under the conditions of high altitude thin air and large flying dynamic pressure, overlarge external resistance of the aircraft body and overhigh structural strength burden are often caused. The cone guided wave rider concept solves the development dilemma, obtains a wave rider configuration by tracing the streamline of the cone-shaped basic flow field, forms shock waves closely attached to the front edge of the wave rider in flight, and can obtain a high lift-drag ratio in a flat flight state. In the aspect of air inlet system design, the proposal of the kiss-flow theory simplifies the design of a three-dimensional air inlet channel into a series of compression contour designs of two-dimensional kiss-cut surfaces, thereby not only improving the compression efficiency of the air inlet channel, but also realizing the requirement of adapting to the geometric shapes of the inlet and the outlet of the air inlet channel. Meanwhile, the compression surface is generated by the pure pneumatic basic flow field design, so that the pneumatic transition characteristic is achieved, and the flow capture, compression efficiency and internal flow performance of the pneumatic transition REST air inlet channel are superior to those of a geometric transition REST air inlet channel.
In the high-speed flying and launching integrated design, the internal flow and the external flow have stronger coupling effect, new challenges are brought to the pneumatic profile design, and the main problems are that the external shock wave of a machine body and the inlet shock wave of an air inlet channel interfere with each other to cause the shock wave shape distortion, so that the high lift-drag ratio of a wave carrier and the high flow capturing performance of the air inlet channel are suddenly reduced. In order to solve the problem, researchers at home and abroad put forward an internal and external flow coupling design idea, interface parameter exchange is carried out on a compression surface of an aircraft front body and an internal compression surface of an air inlet channel by means of a characteristic line method, a non-uniform inlet designation method and the like, the problem of internal and external flow interference is solved preliminarily, and the pneumatic performance is excellent in each state. However, the concept of coupling the internal and external flows has encountered the following problems in further developing the overall design of the aircraft: 1) the precursor compression surface occupies a large portion of the space of the machine body, so that the volume ratio is reduced, and the weight of the front edge of the machine body is too small, so that the difficulty of the total counterweight/moment balance is caused (the X-43 verification machine adopts a metal tungsten balance counterweight at the front edge); 2) when the position of the air inlet channel moves downstream, the low-energy flow developed by the precursor is thickened to influence the air inlet efficiency, so that the thrust of the aircraft is reduced, the flow direction arrangement range of the air inlet channel is limited, and the overall length of the aircraft is limited finally. The inventor finds that the fundamental reason for the development difficulty is that the internal and external flow coupling design idea has strong dependence on the front profile flow field of the aircraft, so that the flexibility of change between the internal flow field and the external flow field is limited. Therefore, a new technical scheme is designed to comprehensively solve the problems in the prior art.
Disclosure of Invention
The invention aims to provide an internal and external flow decoupling double-waverider high-speed air suction type aircraft, which can effectively solve the problems that the existing internal and external flow coupling aircraft is difficult to balance the total weight/moment, the thrust of the aircraft is reduced when an air inlet moves downwards, the flow direction arrangement range of the air inlet is limited, and the total length of the aircraft is limited.
In order to solve the technical problems, the invention adopts the following technical scheme:
the utility model provides a high-speed formula aircraft of breathing in of two ripples of interior external flow decoupling zero, includes the aircraft organism, the upper surface of aircraft organism is the Bump precursor, and the lower surface of aircraft organism is the ripples body of taking advantage of high volume ratio, and inside intake duct, combustion chamber and the spray tube of being equipped with of aircraft organism, the intake duct is the interior ripples intake duct of taking advantage of high external compression ratio.
Furthermore, the waverider is a structure with a convex middle part and two sides rotating to be flat, and the leading edge line of the waverider is the front edge of the aircraft body and is obtained by intercepting the conical basic flow field through a plane or a curved surface.
Furthermore, the air flow before the inlet of the air inlet channel is straight air flow, and the Bump precursor adopts a wing body fusion body of a ridge type pressure distribution Bump surface.
Further, the intake passage compression center includes two arrangements: one of the two modes is a central overflow mode, and an air inlet channel of the central overflow mode is positioned in the central area of a middle section of an aircraft body; the second mode is a two-side overflow mode, and the air inlet channel of the second mode is positioned in the side wall area of the aircraft body.
When the compression center of the air inlet adopts a two-side overflow mode, the position of the compression center of the air inlet comprises forward lip sweepings positioned at two sides of the near Bump precursor, backward lip sweepings positioned at two sides of the far Bump precursor and backward side walls positioned at two sides of the near Bump precursor.
The method for generating the double-waverider high-speed air-breathing aircraft with the inner flow and the outer flow decoupled comprises the following steps:
1) acquiring a leading edge line of a waverider on the lower surface of an aircraft body; selecting a half cone angle theta of a conical basic flow field, wherein the intercepting height of a front edge is HtEquation of section ytF (x), width W is cuttObtaining an intersection line of a conical shock wave surface and a truncated surface according to a conical basic equation, namely a wave multiplier leading edge line;
2) obtaining a wave rider profile; taking each point on the leading edge line of the waverider as a starting point, solving a Taylor Maccoll equation to obtain the arrangement of each point tracking streamline in a three-dimensional space, namely the profile of the waverider;
3) acquiring a pressure-controllable Bump surface of a Bump precursor; determining the flow direction installation position of an air inlet on the upper surface of an aircraft body, obtaining the boundary layer thickness of an air inlet preset position through numerical simulation, designing a corresponding pressure-controllable Bump by taking 70% of the thickness reduction of the boundary layer at the tail end of the Bump as a target, and simultaneously controlling the transverse offset of each streamline of the air inlet preset position to be smaller than 2 degrees, and finally determining the suggested width W of the air inlet preset position;
4) acquiring a high-external compression basic flow field; taking the compression center of the basic flow field as a starting point as a vertical line of a streamline, wherein the intersection point of the vertical line and the wall surface of the basic flow field is a boundary point x of internal and external compression flow, and controlling the external/internal compression ratio of the air inlet passage to be Rπ＝Px 2/(P∞·Pout)>1.8, reaching the standards of high external compression and starting Mach number promotion;
5) acquiring a high external pressure internal waverider air inlet channel; obtaining an incoming flow capture area of an inlet of the air inlet according to the width W determined in the step 3) and the flow demand of the engine, obtaining an air inlet contraction ratio according to the shape size and the Mach number requirement of the inlet of the combustion chamber, determining flow direction projections of the inlet and outlet profiles of the air inlet, and finally obtaining the high external pressure internal waverider air inlet by combining a basic flow field and the inlet and outlet conditions of the air inlet;
6) according to engineering practical experience, the sizes and the shapes of the combustion chamber and the spray pipe are designed, and the inner flow and outer flow decoupling double-waverider high-speed air suction type aircraft is obtained.
According to the internal and external flow decoupling double-waverider high-speed air suction type aircraft and the generation method thereof, the air inlet channel and the waverider are respectively arranged on the upper side and the lower side of the aircraft body, the pneumatic decoupling of the waverider flow field and the air inlet channel inlet flow field is realized through the decoupling on the geometric layout, the problems of low design efficiency and large non-design point external resistance caused by internal and external flow strong coupling are avoided, and the pneumatic design efficiency of the high-speed air suction type aerospace aircraft is remarkably improved.
The invention adopts the high-volume-rate waverider with the middle bulge and the two sides turned to be flat, the middle bulge provides more loading spaces in the aircraft body, the volume rate is improved, and the two sides turned to be flat is beneficial to the profile transition of the upper surface and the lower surface of the aircraft body; the Bump precursor adopts a pressure-controllable Bump surface, the Bump surface adopting ridge-type pressure distribution is used for displacing an incoming flow boundary layer according to different inlet flow direction installation positions, air flow in front of an inlet of the inlet is straightened, and an original expanded flow pipe is adjusted into an even and straight flow pipe so as to meet the requirement of uniformity of inlet air flow of a three-dimensional inner wave-taking inlet.
The compression center of the air inlet comprises two arrangement modes of central overflow and two-side overflow, when the two-side overflow mode is adopted, the compression center of the air inlet comprises three specific arrangement modes, wherein one of the three specific arrangement modes is lip forward, namely the compression center of the air inlet is arranged at two sides of a near Bump precursor, and the flow overflows from two sides of a near wall to ensure the through-flow characteristic of the air inlet; the second mode is that the lip is swept backwards, namely the compression center of the air inlet channel is arranged at two sides of the far Bump precursor, and the flow overflows from the far ends at the two sides to ensure the through-flow characteristic of the air inlet channel; and thirdly, the side wall sweepback, namely the compression center of the air inlet is arranged at the side close to the Bump front body, and the flow overflows from the side wall surface to ensure the through-flow characteristic of the air inlet.
According to the invention, the internal and external flow fields are decoupled, on one hand, the inlet shock wave of the air inlet channel and the external compression shock wave of the waverider are respectively positioned at the upper side and the lower side of the engine body and are not interfered with each other, so that the compression performance of the air inlet channel and the high lift-drag ratio characteristic of the waverider are not influenced by mutual interference of the shock waves; on the other hand, a Bump precursor is arranged between the air inlet channel and the machine body for pneumatic transition; as the thickness of the boundary layer and the unevenness of the flow field of the inlet of the air inlet channel are increased along with the backward movement of the flow direction of the air inlet channel to the installation position, the Bump surfaces with different heights are arranged, the effects of removing the boundary layer with the corresponding thickness and leveling the uniformity of the air flow in front of the inlet of the air inlet channel can be achieved, and the decoupling of the flow direction of the air inlet channel to the installation position is realized. Further, the farther back the inlet preset position is, the wider the width available for arranging the inlet, and the larger the available width of the Bump surface.
Finally, the double-waverider can ensure that the front-edge shock wave of the aircraft body is kept well in the flying state, so that the lift-drag ratio of the whole missile body is ensured, the outer waverider is realized, the inlet shock wave of the air inlet channel is not influenced by the front-edge shock wave, the inner waverider with the shock wave attached to the lip is realized, and the optimal comprehensive flying performance is realized through the double waverider. Meanwhile, a wing body fusion body with low resistance is adopted between the air inlet channel on the upper surface of the engine body and the premise for transition, so that the high-flow capturing characteristic of the air inlet channel facing to non-uniform incoming flow is realized, and the flow direction arrangement range of the air inlet channel is expanded through the efficient Bump low-energy flow displacement capacity.
Drawings
FIG. 1 is a schematic view of an inside-out flow decoupled dual-waverider high-speed air-breathing aircraft according to the present invention;
FIG. 2 is a schematic diagram of acquisition of a leading edge line of a waverider;
FIG. 3 is a pressure-controllable Bump surface for different flow directions at a mounting location;
FIG. 4 is a flow direction projection of an inlet/outlet profile suitable for use with the present patent;
FIG. 5 is a flow chart of a design of a high external pressure three-dimensional internal waverider intake duct;
fig. 6 is a graph showing the results of stability analysis of the total pressure recovery coefficient (left) and the lift-to-drag ratio (right) in each non-design state.
Detailed Description
In order that the objects and advantages of the invention will be more clearly understood, the following description is given in conjunction with the accompanying examples. It is to be understood that the following text is merely illustrative of one or more specific embodiments of the invention and does not strictly limit the scope of the invention as specifically claimed.
Example 1
The technical scheme adopted by the invention is as follows: the utility model provides a high-speed air suction type aircraft of two waverider of interior external flow decoupling zero, includes the aircraft organism, and the upper surface of aircraft organism is the Bump forebody, and according to the intake duct flow direction mounted position of difference, the Bump forebody adopts the wing body fusion body of ridge formula pressure distribution Bump face to carry out the displacement to the incoming flow boundary layer to air current before the intake duct entry is carried out the straightness, adjusts the flow tube of originally expanded type into even, straight flow tube, in order to reach the entry air current homogeneity requirement of three-dimensional interior waverider intake duct.
The lower surface of the aircraft body is a waverider with high volume ratio, the waverider is a structure with a convex middle part and two flat sides, the leading edge line of the waverider is the front edge of the aircraft body, the leading edge line is obtained by intercepting from a conical basic flow field through a plane or a curved surface (refer to figure 2), and then the waverider configuration is obtained by carrying out streamline tracing on each point of the leading edge line; the variable for controlling the shape of the front edge line is the half cone angle theta of the basic flow field (for the super range above Mach 5.0, the theta is recommended to be less than or equal to 5 degrees), and the intercepting height H of the front edgetEquation of section ytF (x), width W is cutt. The important characteristics of the waverider are that the middle is convex and the two sides are flat (refer to the lower surface of fig. 1): the middle bulge provides more loading space for the interior of the aircraft, and the volume ratio is improved; the two sides are rotated flat, so that the molded surface transition of the upper surface and the lower surface of the aircraft is facilitated.
The aircraft body is internally provided with an air inlet channel, a combustion chamber and a spray pipe, the air inlet channel is an internal waverider air inlet channel with a high external compression ratio, and the design of the air inlet channel comprises three steps of designing a high external compression basic flow field, arranging a compression center and determining a osculating surface compression profile; the design of the high external compression basic flow field takes the compression center of the basic flow field as a starting point as a vertical line of a streamline, and finally the intersection point of the vertical line and the wall surface of the basic flow field is a boundary point x of internal and external compression flow, so that the external/internal compression ratio of the air inlet channel is Rπ＝Px 2/(P∞·Pout) In this embodiment, the high-to-external compression ratio is Rπ>1.8. It is composed ofThe second is the arrangement of the compression center, as shown in fig. 4, which is a projection view of the inlet and outlet contour lines of the air inlet on yoz, and the compression center of the air inlet has two types of arrangement modes: the first is the central area of the middle section, and adopts a central overflow mode; the second is the side wall area of the air inlet channel, and a two-side overflow scheme is adopted; for the two-side overflow scheme, the two-side overflow scheme comprises three types of forward lip sweepback, backward lip sweepback and backward side wall sweepback; for the forward-swept lip opening, the compression centers are arranged at two sides of a near Bump precursor, and the flow can overflow from two sides of the near wall to ensure the through-flow characteristic of the air inlet channel; for the lip sweepback, the compression centers of the lip sweepback are arranged at two sides of the far Bump precursor, and the flow can overflow from the far ends at the two sides to ensure the through-flow characteristic of the air inlet channel; for side wall sweepback, the compression center is arranged at the side close to the Bump front body, and the flow can overflow from the side wall surface to ensure the through-flow characteristic of the air inlet channel. Here, the compression center may be a point indicated by a red circle in the drawing, or may be an area near the red circle (i.e., an area where the compression center is changed). And finally, determining the kiss-cut surface compression molded line, and selecting and interpolating from a series of basic flow fields through three processes of inlet height conversion, inlet height matching and contraction ratio matching of an air inlet channel according to a specific flow shown in fig. 5 to obtain the kiss-cut surface compression molded line.
The internal and external flow field decoupling adopted by the invention comprises two aspects: on one hand, the inlet shock wave of the air inlet channel and the external compression shock wave of the waverider are respectively positioned at the upper side and the lower side of the engine body and do not interfere with each other, so that the compression performance of the air inlet channel and the high lift-drag ratio characteristic of the waverider are not influenced by the mutual interference of the shock wave and the shock wave; and on the other hand, a Bump profile is arranged between the air inlet channel and the machine body for pneumatic transition. Because the boundary layer thickness and the flow field unevenness of the inlet of the air inlet channel are increased along with the backward movement of the inlet channel towards the installation position, the boundary layer with the corresponding thickness can be removed and the airflow uniformity in front of the inlet of the air inlet channel can be leveled by arranging the Bump surfaces with different heights, and the decoupling of the inlet channel towards the installation position is realized (refer to fig. 3). Further, the farther back the intake duct preset position is, the wider the width available for disposing the intake duct, and therefore the larger the available width of the Bump surface.
In addition, double waverider is realized through the waverider positioned on the lower surface of the aircraft body and the inner waverider air inlet with high external compression ratio, so that the front edge shock wave of the aircraft body is kept good in the flying state of the aircraft body, the lift-drag ratio of the whole missile body is ensured, and 'external waverider' is realized; the inlet shock wave of the air inlet channel is not influenced by the front edge shock wave, so that the 'inner wave' of the shock wave attached to the lip is realized, and the optimal comprehensive flight performance is realized through 'double waves'.
Example 2
A method for generating a double-waverider high-speed air-breathing aircraft with decoupled internal and external flows comprises the following steps:
1) acquiring a leading edge line of a waverider on the lower surface of an aircraft body; selecting a half cone angle theta of a conical basic flow field, wherein the intercepting height of a front edge is HtEquation of section ytF (x), width W is cuttObtaining an intersection line of a conical shock wave surface and a truncated surface according to a conical basic equation, namely a wave multiplier leading edge line;
2) obtaining a wave rider profile; taking each point on the leading edge line of the waverider as a starting point, solving a Taylor Maccoll equation to obtain the arrangement of each point tracking streamline in a three-dimensional space, namely the profile of the waverider;
3) acquiring a pressure-controllable Bump surface of a Bump precursor; determining the flow direction installation position of an air inlet on the upper surface of an aircraft body, obtaining the boundary layer thickness of an air inlet preset position through numerical simulation, designing a corresponding pressure-controllable Bump by taking the thickness reduction of the boundary layer at the tail end of a Bump precursor as a target, and controlling the transverse offset of each streamline of the air inlet preset position to be smaller than 2 degrees at the same time to finally determine the suggested width W of the air inlet preset position;
4) acquiring a high-external compression basic flow field; taking the compression center of the basic flow field as a starting point as a vertical line of a streamline, wherein the intersection point of the vertical line and the wall surface of the basic flow field is a boundary point x of internal and external compression flow, and controlling the external/internal compression ratio of the air inlet passage to be Rπ＝Px 2/(P∞·Pout)>1.8, reaching the standards of high external compression and starting Mach number promotion;
5) acquiring a high external pressure internal waverider air inlet channel; obtaining an incoming flow capture area of an inlet of the air inlet according to the width W determined in the step 3) and the flow demand of the engine, obtaining an air inlet contraction ratio according to the shape size and the Mach number requirement of the inlet of the combustion chamber, determining the flow direction projection of the inlet and outlet profiles of the air inlet, finally obtaining a flow according to a diagram 5, and combining a basic flow field and the inlet and outlet conditions of the air inlet to obtain the high-external-pressure internal-multiplication air inlet;
6) according to engineering practical experience, the size and the shape of a combustion chamber and a spray pipe are designed to obtain the overall aerodynamic configuration of the different-side double-waverider high-speed air-breathing aircraft with internal and external flow decoupling.
The double-waverider high-speed air-breathing aircraft with inner and outer flow decoupling and the generation method are preliminarily verified, and the selected design states are Ma7.0 and 30km, so that the following results are obtained:
based on the concept design of 'double waverider' of the 'external waverider' of the cone-guide waverider and 'internal waverider' of three-dimensional variable cross-section, the air inlet can not only achieve high flow capture (more than 98% of flow coefficient) under non-uniform inflow, but also fully utilize the characteristics of high lift-drag ratio (5 is achieved under the conditions of small attack angle and low airfoil surface) of the cone-guide waverider, such as aerodynamic performance, large volume ratio and the like, and has excellent flight stability under the conditions of variable attack angle, side slip angle and low Mach number (Ma4.5-7.0 starting) (see figure 6).
The present invention is not limited to the above embodiments, and those skilled in the art can make various equivalent changes and substitutions without departing from the principle of the present invention after learning the content of the present invention, and these equivalent changes and substitutions should be considered as belonging to the protection scope of the present invention.
Claims (6)
1. The utility model provides a high-speed air suction type aircraft of two waverider of interior external flow decoupling zero, includes the aircraft organism, its characterized in that: the upper surface of the aircraft body is a Bump precursor, the lower surface of the aircraft body is a waverider with a high volume ratio, an air inlet channel, a combustion chamber and a spray pipe are arranged in the aircraft body, and the air inlet channel is a waverider with a high external compression ratio.
2. The internal and external flow decoupled, dual-waverider high-speed air breathing aircraft of claim 1 wherein: the wave rider is a structure with a convex middle part and two flat sides, and the leading edge line of the wave rider is the front edge of the aircraft body and is obtained by plane or curved surface interception in the conical basic flow field.
3. The internal and external flow decoupled, dual-waverider high-speed air breathing aircraft of claim 1 wherein: the air flow in front of the inlet of the air inlet channel is straight air flow, and the Bump precursor adopts a wing body fusion body of a ridge type pressure distribution Bump surface.
4. The decoupled internal and external flow dual-waverider high-speed air-breathing aircraft of claim 1 wherein the inlet compression center comprises two arrangements: one of the two modes is a central overflow mode, and an air inlet channel of the central overflow mode is positioned in the central area of a middle section of an aircraft body; the second mode is a two-side overflow mode, and the air inlet channel of the second mode is positioned in the side wall area of the aircraft body.
5. The internal and external flow decoupled, dual-waverider high-speed air breathing aircraft of claim 4 wherein: when the compression center of the air inlet adopts a two-side overflow mode, the position of the compression center of the air inlet comprises forward lip sweepings positioned at two sides of the near Bump precursor, backward lip sweepings positioned at two sides of the far Bump precursor and backward side walls positioned at two sides of the near Bump precursor.
6. The method of generating a dual-waverider high-speed air-breathing aircraft with decoupled internal and external flow according to claim 1, comprising the steps of:
1) acquiring a leading edge line of a waverider on the lower surface of an aircraft body; selecting a half cone angle theta of a conical basic flow field, wherein the intercepting height of a front edge is HtEquation of section ytF (x), width W is cuttObtaining an intersection line of a conical shock wave surface and a truncated surface according to a conical basic equation, namely a wave multiplier leading edge line;
2) obtaining a wave rider profile; taking each point on the leading edge line of the waverider as a starting point, solving a Taylor Maccoll equation to obtain the arrangement of each point tracking streamline in a three-dimensional space, namely the profile of the waverider;
3) acquiring a pressure-controllable Bump surface of a Bump precursor; determining the flow direction installation position of an air inlet on the upper surface of an aircraft body, obtaining the boundary layer thickness of an air inlet preset position through numerical simulation, designing a corresponding pressure-controllable Bump surface by taking the thickness reduction of the boundary layer at the tail end of a Bump precursor as a target, and controlling the transverse offset of each streamline of the air inlet preset position to be smaller than 2 degrees at the same time to finally determine the suggested width W of the air inlet preset position;
4) acquiring a high-external compression basic flow field; taking the compression center of the basic flow field as a starting point as a vertical line of a streamline, wherein the intersection point of the vertical line and the wall surface of the basic flow field is a boundary point x of internal and external compression flow, and controlling the external/internal compression ratio of the air inlet passage to be Rπ＝Px 2/(P∞·Pout)>1.8, reaching the standards of high external compression and starting Mach number promotion;
5) acquiring a high external pressure internal waverider air inlet channel; obtaining an incoming flow capture area of an inlet of the air inlet according to the width W determined in the step 3) and the flow demand of the engine, obtaining an air inlet contraction ratio according to the shape size and the Mach number requirement of the inlet of the combustion chamber, determining flow direction projections of the inlet and outlet profiles of the air inlet, and finally obtaining the high external pressure internal waverider air inlet by combining a basic flow field and the inlet and outlet conditions of the air inlet;
6) according to engineering practical experience, the sizes and the shapes of the combustion chamber and the spray pipe are designed, and the inner flow and outer flow decoupling double-waverider high-speed air suction type aircraft is obtained.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011230880.3A CN112340014B (en) | 2020-11-06 | 2020-11-06 | Inner-outer flow decoupling double-waverider high-speed air suction type aircraft and generation method thereof |
| PCT/CN2020/132142 WO2022095163A1 (en) | 2020-11-06 | 2020-11-27 | Internal-external flow decoupled dual-waverider high-speed airbreathing aircraft and generation method therefor |
Applications Claiming Priority (1)
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| CN114313253A (en) * | 2022-03-03 | 2022-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic layout and design method of high lift-drag ratio air-breathing hypersonic aircraft |
| CN115493802A (en) * | 2022-11-18 | 2022-12-20 | 中国空气动力研究与发展中心空天技术研究所 | Internal and external flow aerodynamic decoupling structure of body propulsion integrated model and working installation method |
| CN115871913A (en) * | 2023-02-28 | 2023-03-31 | 中国空气动力研究与发展中心计算空气动力研究所 | Integrated aerodynamic layout of high lift-drag ratio air-breathing aircraft and construction method thereof |
| CN116451343A (en) * | 2023-03-20 | 2023-07-18 | 西北工业大学 | Wing section design method of flying wing layout aircraft considering influence of backpack type air inlet channel |
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| CN115371933B (en) * | 2022-10-24 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Method for testing aerodynamic coupling between air inlet channel and aircraft forebody |
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| CN112340014B (en) | 2022-05-13 |
| WO2022095163A1 (en) | 2022-05-12 |
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