CN103010454A - Wave rider aircraft with redundant pneumatic distribution and control method thereof - Google Patents

Abstract

The invention discloses a waverider aircraft with a redundant aerodynamic layout. The waverider aircraft is based on an ideal waverider configuration. Both sides of the tail of the waverider aircraft are provided with rotatable full-motion control rudders. The upper and lower surfaces of the tail of the wave vehicle are provided with rotatable embedded control surfaces, and two sets of obliquely cut nozzles are respectively provided on both sides of the bottom surface of the waverider. The waverider aircraft with redundant aerodynamic layout of the present invention not only has excellent aerodynamic performance, good maneuverability and strong robustness, but also can realize damping adjustment.

Description

Waverider aircraft with redundant aerodynamic layout and control method thereof

technical field

The invention belongs to the technical field of overall structural design of waveriders, in particular to a waverider with redundant aerodynamic layout and a control method thereof.

Background technique

Aerodynamic layout design is the basis of glider aircraft design. Under hypersonic conditions, the waverider configuration has better aerodynamic performance, and has become an effective attempt to break through the "lift-to-drag ratio barrier" faced by hypersonic flight of traditional aircraft. However, the ideal waverider configuration does not have any control mechanism for attitude adjustment. In the process of designing the aerodynamic layout of the gliding aircraft, it is necessary to modify the ideal waverider configuration.

After our analysis, we found that the aerodynamic layout of the existing waverider aircraft is only based on the ideal waverider configuration, and the edges are properly blunted and modified, and the attitude control is performed with a small nozzle on the bottom plane. With such a layout design, although the overall configuration of the waverider aircraft deviates less from the ideal waverider configuration and has better aerodynamic performance, it faces greater challenges in the design of the heat protection system. At the same time, due to the limited means of controlling the attitude of the existing waverider aircraft, the robustness of the control system is poor, and there are defects in the control ability. In addition, due to the small pitch damping of existing waveriders, their pitch channels are prone to instability.

Contents of the invention

The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art, and provide a waverider aircraft with redundant aerodynamic layout that has simple structure, excellent aerodynamic performance, good maneuverability, strong robustness, and can realize damping adjustment. A simple and easy control method of the waverider aircraft is also provided.

In order to solve the above-mentioned technical problems, the technical solution proposed by the present invention is a waverider aircraft with redundant aerodynamic layout. The waverider aircraft is based on the ideal waverider configuration. There are rotatable full-motion control rudders, rotatable embedded control surfaces are provided on the upper and lower surfaces of the tail of the waverider, and two groups of oblique nozzles are respectively provided on both sides of the bottom surface of the waverider.

In the above-mentioned technical solution of the present invention, by applying various control components to the aerodynamic layout based on waveriding configuration design, different control components are combined with each other to form various control means; according to the layout, three channels (including pitch , yaw, roll) At different flight stages (including differences in flight altitude, flight speed, etc.), different combined control methods can be used to achieve the most effective and optimal control of the attitude of the waverider aircraft.

In the above-mentioned waverider aircraft with redundant aerodynamic layout, preferably, the full motion control rudder includes a left full motion rudder and a right full motion rudder, and the left full motion rudder and the right full motion rudder move along the waverider aircraft The middle plane of the waverider is arranged symmetrically; the two sides of the tail of the waverider are provided with two installation planes that are basically parallel to the middle plane (the installation planes are obtained by cutting off the two outermost sides of the rear of the ideal waverider configuration). obtained after a triangular pyramid), the installation shaft of the full-motion control rudder is installed perpendicular to the installation plane. The left full motion rudder and the right full motion rudder can rotate around their respective installation rotating shafts. When the left full motion rudder and the right full motion rudder deflect in the same direction (that is, the left full motion rudder and the right full motion rudder deflect clockwise or counterclockwise around their respective installation axes) at the same angle, the waverider aircraft can be controlled Control of the pitch channel; when the left full-motion rudder and the right full-motion rudder perform differential deflection (that is, the left full-motion rudder and the right full-motion rudder deflect in opposite directions around their respective installation axes at the same time), the roll of the waverider aircraft can be realized. The control of the turning channel; when the deflection angle is different, due to the asymmetrical force, it will have an impact on the pitch, yaw and roll channels, and the roll and yaw control of the waverider aircraft can be realized. The area size, shape and installation position of the control rudder surface of the full-motion control rudder are generally related to the specific shape parameters of the selected waveriding configuration and the required design performance, and those skilled in the art can calculate and determine through the aerodynamic design method .

As a further improvement to the above technical solution, two triangular pyramid-like upper grooves are provided on the middle rear of the upper surface of the waverider (by making the upper surface close to the rear edge and outer side of the ideal waverider configuration) Modified, cut into two symmetrical platforms), the middle and rear of the lower surface of the waverider aircraft are provided with two lower grooves in the shape of triangular pyramids (through the ideal waverider configuration, the lower surface is close to the rear edge and the outer modify the position, cut into two symmetrical platforms), the tails of the upper groove and the lower groove are provided with embedded control surfaces, and the upper grooves, lower grooves and embedded control surfaces are all along the The mid-plane of the waverider is arranged symmetrically. More preferably, the embedded control surface is located on a rotatable triangular prism, and the rotation axis of the triangular prism is arranged in the upper groove and the lower groove along a direction perpendicular to the middle plane. The bottom surface of the triangular prism is preferably parallel to the median plane, and the rotation axis is adjacent to and parallel to a side edge of the triangular prism.

In the preferred technical solution above, the rotation angle of the embedded control surface is constrained by parameters such as the incoming flow state and the angle of the symmetrical platform. When the two embedded control surfaces arranged symmetrically in the upper groove or the two embedded control surfaces arranged symmetrically in the lower groove are deflected at the same angle in the same direction, the control of the pitch channel of the waverider aircraft can be realized; and when the differential deflection , the control of the pitch, yaw, and roll channels of the waverider can be realized; when the embedded control surface in the upper groove deflects upward, and the embedded control surface in the lower groove deflects downward, the multiplier can be increased. The damping of the aerodynamic layout of the wave aircraft improves the defect of small damping in the ideal waverider configuration; when the deflection angle is different, due to the asymmetrical force, it will affect the pitch, yaw and roll channels.

As a further improvement to the above technical solution, in the waverider aircraft, each group of the oblique nozzles is composed of an upper oblique nozzle unit, a middle oblique nozzle unit and a lower oblique nozzle unit. The two groups of oblique nozzles are arranged symmetrically along the mid-plane of the waverider. More preferably, the upper and lower beveled nozzle units are located in the same vertical plane, and are closer to the midplane than the middle beveled nozzle unit; the injection direction of the upper beveled nozzle unit is toward On the top, the jetting direction of the lower chamfered nozzle unit faces downwards, and the jetting direction of the middle chamfered nozzle unit faces outwards. Through our repeated experiments and calculations, the central axis of the upper beveled nozzle unit and the horizontal plane are preferably at an elevation angle of 30° to 60°, and the central axis of the lower beveling nozzle unit and the horizontal plane are preferably at a depression angle of 30° to 60° (Especially preferably the same as the elevation angle of the upper chamfered nozzle unit), the central axis of the middle chamfered nozzle unit preferably forms an included angle of 30° to 60° with the midplane. The two sets of oblique nozzles are mainly used when the atmosphere is relatively thin at the initial stage of re-entry: when the two upper oblique nozzle units or the two lower oblique nozzle units work simultaneously, the control of the pitch channel of the waverider can be realized ; and when the left or right mid-slope nozzle unit works alone, the control of the yaw passage of the waverider aircraft can be realized; when the left upper slope nozzle unit and the right bottom slope nozzle unit Simultaneously working, or when the left lower beveled nozzle unit and the right upper beveled nozzle unit are working simultaneously, the control of the roll channel of the waverider aircraft can be realized.

As a general technical idea, the present invention also provides a control method for the above-mentioned waverider aircraft, which performs combined control on the waverider aircraft according to the magnitude of the incoming flow pressure of the waverider aircraft during flight, specifically including the following operations:

When the incoming flow pressure is less than a certain value (preferably such as 100 Pa) (corresponding to the initial stage of the re-entry gliding process of the waverider), the flight altitude of the waverider is relatively high, the atmosphere is thin, and the dynamic pressure is low. The control surface (including the full-motion control rudder and the embedded control surface) has a small control force, which cannot provide enough torque to control the attitude of the waverider aircraft, and can hardly play the role of attitude control. At this time, the control of the oblique nozzle plays an important role. Leading role, the two groups of oblique nozzles can be used to effectively control the attitude of the waverider aircraft;

Because the operational efficiency of the oblique nozzle and the aerodynamic control surface in the waverider of the present invention is closely related to the incoming flow pressure, therefore, when the incoming fluid pressure increased, the operational efficiency of the oblique nozzle decreased, and the work efficiency of the aerodynamic control surface Efficiency then increases; when the incoming flow pressure is greater than a certain value (preferably such as 460 Pa) (corresponding to the main stage of the re-entry gliding process), the combined control of the full-motion control rudder and the embedded control surface can be used, Realize effective control of the attitude of the waverider aircraft;

When the incoming flow pressure is between the two cut-off values (for example, between 100 Pa and 460 Pa), through the combined manipulation of the two sets of oblique nozzles, full-motion control rudders and embedded control surfaces, the control of Effective control of waverider attitude.

Since the above-mentioned redundant aerodynamic layout proposed by the present invention does not include the vertical tail, the lateral static stability of the waverider mainly depends on the upside-down design of the full-motion control rudder. When the waverider aircraft skids, the upturned full-motion control rudder will cause differences in the lift force and its distribution on the left and right sides of the waverider aircraft, thereby generating a roll recovery moment.

The above-mentioned redundant aerodynamic layout proposed by the present invention can also generate yaw moment through the embedded control surface working in drag rudder mode. However, in the actual design process, the force and thermal characteristics of the hypersonic gliding waverider vehicle using the waverider configuration as the basic layout are very sensitive to the yaw angle, and its lateral maneuvering is mainly through controlling the roll channel attitude change, Implemented in a roll turn.

Compared with the prior art, the advantage of the present invention is that the redundant aerodynamic layout of the present invention deviates little from the ideal waverider configuration, so it still has its excellent aerodynamic performance under hypersonic conditions; at the same time, the present invention is On the basis of the waveriding configuration, by introducing the combined control method of full-motion control rudder, embedded control surface and inclined nozzle, it not only avoids the severe aerodynamic heating problem faced by the traditional layout under hypersonic conditions. Moreover, the embedded control surface can also be used as an artificial damper to improve the defect of small damping in the ideal waverider configuration. Since the attitude control of the waverider aircraft of the present invention can be realized through multiple combinations of six aerodynamic control surfaces and two groups of oblique nozzles, there is redundancy in the design of the control system, and the control system has strong robustness and is suitable for hypersonic speeds. Effective attitude control of gliding waverider aircraft is of great significance.

Description of drawings

Figure 1 is a schematic structural view (perspective view) of a waverider aircraft with redundant aerodynamic layout in an embodiment of the present invention, and the shadow in the figure indicates the location of the embedded control surface (the same below).

Fig. 2 is a top view of a waverider aircraft with a redundant aerodynamic layout in an embodiment of the present invention.

Fig. 3 is a schematic diagram of the full motion control rudder of the waverider in the embodiment of the present invention when deflecting in the same direction.

Fig. 4 is a schematic diagram of the full motion control rudder of the waverider aircraft in the differential deflection according to the embodiment of the present invention.

Fig. 5 is a front view of a waverider aircraft with a redundant aerodynamic layout in an embodiment of the present invention.

Fig. 6 is a partially enlarged view of the rear part of the waverider in Fig. 5 .

Fig. 7 is a schematic diagram of the embedded control surface of the groove on the waverider in the embodiment of the present invention when it deflects in the same direction.

Fig. 8 is a schematic diagram of the embedded control surface of the groove on the waverider in the embodiment of the present invention during differential deflection.

Fig. 9 is a left side view of the waverider aircraft with redundant aerodynamic layout in the embodiment of the present invention.

Fig. 10 is a schematic diagram of the installation of the right oblique nozzle group in the waverider aircraft in the embodiment of the present invention (stereoscopic perspective after partial enlargement).

Fig. 11 is a schematic diagram of the flight trajectory of the waverider aircraft in the embodiment of the present invention.

Fig. 12 is a graph showing the variation of the control torque of the oblique nozzle in the initial stage of the waverider aircraft in the embodiment of the present invention.

Fig. 13 is a change diagram of a rudder deflection angle in the initial stage of the waverider aircraft in the embodiment of the present invention.

illustration:

1. Left full dynamic rudder; 2. Upper left embedded control surface; 3. Upper right embedded control surface; 4. Right full dynamic rudder; 5. Lower right embedded control surface; 6. Lower left embedded control surface; 7. Left 8. Right oblique nozzle group; 81. Upper right oblique nozzle unit; 82. Right middle oblique nozzle unit; 83. Right lower oblique nozzle unit; 9. Triangular prism; 10. Install the rotating shaft; 11. Install the plane; 12. Rotate the shaft.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings and specific preferred embodiments, but the protection scope of the present invention is not limited thereby.

Example:

A waverider aircraft with redundant aerodynamic layout as shown in Figures 1 to 10, the waverider aircraft is based on the ideal waverider configuration, and the two sides of the tail of the waverider aircraft are equipped with rotatable full-motion control rudders A rotatable embedded control surface is provided on the upper and lower surfaces of the tail of the waverider, and two groups of obliquely cut nozzles are respectively provided on both sides of the bottom surface of the waverider.

As shown in Figures 1 to 4, in the above-mentioned waverider aircraft with redundant aerodynamic layout, the full-motion control rudders include left full-motion rudder 1 and right full-motion rudder 4, left full-motion rudder 1 and right full-motion rudder 4 It is arranged symmetrically along the midplane of the waverider; two installation planes 11 that are basically parallel to the midplane are arranged on both sides of the tail of the waverider (the installation planes 11 are formed by cutting off the two outermost rear parts of the ideal waverider configuration). Obtained after the two triangular pyramids on the side), the installation shaft 10 of the full-motion control rudder is installed perpendicular to the installation plane 11. The left full-motion rudder 1 and the right full-motion rudder 4 can rotate around their respective installation rotating shafts 10 .

As shown in Figure 7 and Figure 8, the middle and rear part of the upper surface of the waverider aircraft in this embodiment is provided with two triangular pyramid-shaped upper grooves (through the position of the upper surface near the rear edge and the outer side of the ideal waverider configuration) modified and cut into two symmetrical platforms), the middle and rear of the lower surface of the waverider aircraft are provided with two triangular pyramid-like lower grooves (through the ideal waverider configuration lower surface near the rear edge and outer The position is modified and cut into two symmetrical platforms). Embedded control surfaces are provided at the tails of the upper groove and the lower groove, and the upper groove, the lower groove and the embedded control surface are arranged symmetrically along the mid-plane M of the waverider aircraft. There are four embedded control surfaces in this embodiment, including the upper left embedded control surface 2 and the upper right embedded control surface 3 located in the upper groove, and the lower right embedded control surface 5 located in the lower groove. and the lower left embedded control surface 6; each embedded control surface is located on a rotatable triangular prism 9, and the rotation axis 12 of each triangular prism 9 is installed in the upper groove and the direction perpendicular to the middle plane M in the lower groove. The bottom surface of the triangular prism 9 is parallel to the middle plane M, and the rotation axis 12 is adjacent to and parallel to a side edge of the triangular prism 9 (see FIG. 7 and FIG. 8 ).

As shown in Figures 9 and 10, the two groups of oblique nozzles in the waverider of the present embodiment refer to the left oblique nozzle group 7 and the right oblique nozzle group 8 respectively, each group of oblique nozzles It consists of an upper oblique nozzle unit, a middle oblique nozzle unit and a lower oblique nozzle unit. Cut the nozzle unit 82 and the lower right obliquely cut the nozzle unit 83, and two groups of obliquely cut nozzles are arranged symmetrically along the mid-plane of the waverider aircraft. As shown in Figure 10, the upper right obliquely cut nozzle unit 81 and the right lower obliquely cut nozzle unit 83 are located in the same vertical plane Y, and are closer to the midplane M than the right middle obliquely cut nozzle unit 82; The jetting direction of the nozzle unit 81 is upward, the jetting direction of the lower right oblique nozzle unit 83 is downward, and the jetting direction of the right middle oblique nozzle unit 82 is outward. Through our repeated experiments and calculations, in this embodiment, the central axis of the upper right oblique nozzle unit 81 and the horizontal plane form a 60° elevation angle α, and the central axis of the right lower oblique nozzle unit 83 forms a 60° depression angle β with the horizontal plane. The central axis of the beveled nozzle unit 82 forms an included angle γ of 60° with the central plane M (ie, the vertical plane Y).

In the control method of the above-mentioned waverider aircraft in this embodiment, the waverider aircraft is controlled in combination by the size of the incoming flow pressure when the waverider aircraft is flying. In this embodiment, 96 Pa and 479 Pa are used as the demarcation point of the incoming flow pressure, that is, The critical point at which the attitude control mode changes, including the following operations:

When the incoming flow pressure is less than 96 Pa (corresponding to the initial stage of the re-entry gliding process of the waverider), the flight altitude of the waverider is relatively high, the atmosphere is thin, and the dynamic pressure is low. rudders and embedded control surfaces) have relatively small control force, cannot provide enough torque to control the attitude of the waverider aircraft, and can hardly play the role of attitude control. At this time, the control of the oblique nozzle plays a leading role, and two groups of The oblique nozzle can effectively control the attitude of the waverider;

Because the operational efficiency of the oblique nozzle and the aerodynamic control surface in the waverider of the present invention is closely related to the incoming flow pressure, therefore, when the incoming fluid pressure increased, the operational efficiency of the oblique nozzle decreased, and the work efficiency of the aerodynamic control surface The efficiency increases; when the incoming flow pressure is greater than 479 Pa (corresponding to the main stage of the re-entry gliding process), the full-motion control rudder and the embedded control surface can be used for combined manipulation to achieve effective control of the attitude of the waverider aircraft;

When the incoming flow pressure is between 96 Pa and 479 Pa, the attitude control of the waverider aircraft can be effectively controlled through the combined control of two sets of oblique nozzles, full-motion control rudders and embedded control surfaces.

The combination mode of the control mechanism in this embodiment is shown in Table 1 below:

Table 1: Judgment on selection of aircraft control mechanism Incoming pressure (Pa) Nozzle full steering Embedded Control Surface Lower Embedded Control Surface 0～96 yes - - - 96～479 yes yes yes yes 479～ - yes yes yes

所需的控制力矩为M^指令，则具体分配如下：Let the flow pressure be

The required control torque is the M ^command , and the specific distribution is as follows:

$\mathrm{<span\; class="notranslate">\; k</span>}<span\; class="notranslate">\; =</span>\frac{\mathrm{<span\; class="notranslate">\; 479</span>}<span\; class="notranslate">\; -</span>\stackrel{<span\; class="notranslate">\; \&OverBar;</span>}{\mathrm{<span\; class="notranslate">\; Q</span>}}}{\mathrm{<span\; class="notranslate">\; 479</span>}<span\; class="notranslate">\; -</span>\mathrm{<span\; class="notranslate">\; 96</span>}}$

M _nozzle = kM ^instruction

M _{aerodynamic surface} = (1-k) M ^command

When adopting oblique nozzles to achieve attitude control, there are a total of 6 oblique nozzle units in the aerodynamic layout designed in this embodiment to control 3 channels. In theory, there are countless distributions of control torques, so as to achieve redundancy control.

When using six aerodynamic control surfaces (including full-motion control rudders and embedded control surfaces) to realize the attitude control of the waverider aircraft, using the six control surfaces to control the three channels can achieve redundant control. There are countless control distribution schemes. The direct distribution method and other methods can be used to distribute the control torque. It is recommended to use the method of the smallest total rudder deflection angle for distribution, that is, the sum of the deflection angles of the six aerodynamic control surfaces is the smallest, so that the full use of each Control capability of the control surface.

Taking the flight control of the waverider aircraft in this embodiment under specific flight conditions as an example, its designed flight trajectory is shown in Figure 11. In the initial stage of the flight (within the first 300 seconds), due to the high altitude and the thin air, the flow At this time, the attitude control is completed by two groups of oblique nozzles and aerodynamic control surfaces. Figure 12 shows the three-directional control torques and dynamic pressures that need to be provided by the oblique nozzles in the initial stage. Fig. 13 is the change diagram of the deflection angle of one of the aerodynamic control surfaces. It can be seen that when the incoming flow pressure is less than 96 Pa, the control torque is provided by the oblique nozzle, and the incoming flow pressure gradually increases as the flight altitude decreases. Large, the control torque is jointly borne by the beveled nozzle and the aerodynamic control surface. When the incoming flow pressure is greater than 476 Pa, the attitude control is mainly realized by each aerodynamic control surface.

Because the surface aerodynamic heating of the hypersonic gliding waverider is very serious, it is usually not allowed to have a side slip angle or only a small side slip angle is allowed, and its lateral maneuvering will be realized by tilting and turning, that is, through the Posture control implementation for scrolling channels.

Among the above-mentioned control methods, the specific operation method of the full-motion control rudder is as follows: when the left full-motion rudder 1 and the right full-motion rudder 4 deflect in the same direction and at the same angle, the control of the pitch channel of the waverider can be realized; When the dynamic rudder 1 and the right full-motion rudder 4 perform differential deflection at the same angle, the control of the roll channel of the waverider aircraft can be realized; when the deflection angles are different, due to the asymmetrical force, there will be differences in the pitch, yaw, and roll channels. The roll and yaw control of the waverider aircraft can be realized.

In the above control method, the rotation angle of the embedded control surface is constrained by parameters such as the incoming flow state and the angle of the symmetrical platform. The upper left embedded control surface 2 and the upper right embedded control surface 3 symmetrically arranged in the upper groove (or the lower right embedded control surface 5 and the lower left embedded control surface 6 symmetrically arranged in the lower groove) deflect in the same direction and at the same angle , the control of the pitch channel of the waverider can be realized; while the differential deflection can realize the control of the pitch, yaw and roll channels of the waverider; when the upper left embedded control surface 2 and the upper right in the upper groove When the embedded control surface 3 is deflected upward, and when the lower right embedded control surface 5 and the lower left embedded control surface 6 in the lower groove deflect downward, the damping of the aerodynamic layout of the waverider aircraft can be increased, and the ideal waverider configuration can be improved. The defect of small damping; when the deflection angle is different, due to the asymmetrical force, it will affect the pitch, yaw and roll channels.

In the above control method, the two sets of oblique nozzles are mainly used at the initial stage of re-entry: when the two upper oblique nozzle units or the two lower oblique nozzle units work simultaneously, the pitch channel of the waverider can be realized. control; while the left or right mid-slope nozzle unit works alone, the control of the yaw channel of the waverider aircraft can be realized; when the left upper slope nozzle unit and the right bottom slope nozzle The units work at the same time, or when the lower oblique nozzle unit on the left side and the upper oblique nozzle unit on the right work simultaneously, the control of the roll channel of the waverider aircraft can be realized.

Claims (10)

1. A waverider with redundant aerodynamic layout, the waverider is based on an ideal waverider configuration, characterized in that: both sides of the tail of the waverider are provided with rotatable full-motion control The rudder, the upper and lower surfaces of the tail of the waverider are provided with rotatable embedded control surfaces, and the two sides of the bottom surface of the waverider are respectively provided with two groups of oblique nozzles. 2. The waverider aircraft with redundant aerodynamic layout according to claim 1, characterized in that: the full-motion control rudder comprises a left full-motion rudder and a right full-motion rudder, and the left full-motion rudder and the right full-motion rudder The rudders are arranged symmetrically along the midplane of the waverider; two installation planes basically parallel to the midplane are provided on both sides of the tail of the waverider, and the installation shaft of the full-motion control rudder is installed perpendicular to the installation plane. set up. 3. The waverider with redundant aerodynamic layout according to claim 1 or 2, characterized in that: the middle and rear part of the upper surface of the waverider is provided with two triangular pyramid-like upper grooves, The middle rear portion of the lower surface of the waverider is provided with two lower grooves in the shape of triangular pyramids, and the tails of the upper groove and the lower groove are provided with embedded control surfaces. The upper groove, Both the lower groove and the embedded control surface are arranged symmetrically along the mid-plane of the waverider. 4. The waverider aircraft with redundant aerodynamic layout according to claim 3, characterized in that: the embedded control surface is located on a rotatable triangular prism, and the rotation axis of the triangular prism is perpendicular to the The direction of the midplane is installed in the upper groove and the lower groove. 5. The waverider aircraft with redundant aerodynamic layout according to claim 4, characterized in that: the bottom surface of the triangular prism is parallel to the mid-plane, and the axis of rotation is in phase with a side edge of the triangular prism adjacent and parallel. 6. The waverider aircraft with redundant aerodynamic layout according to claim 1 or 2, characterized in that: each group of described oblique nozzles is composed of upper oblique nozzle unit, middle oblique nozzle unit and The lower oblique nozzle unit is composed of two groups of oblique nozzles arranged symmetrically along the mid-plane of the waverider aircraft. 7. The waverider aircraft with redundant aerodynamic layout according to claim 6, characterized in that: the upper and lower beveled nozzle units are located in the same vertical plane, and are shorter than the middle beveled nozzle unit. Close to the middle plane; the injection direction of the upper oblique nozzle unit is upward, the injection direction of the lower oblique nozzle unit is downward, and the injection direction of the middle oblique nozzle unit is outward. 8. The waverider aircraft with redundant aerodynamic layout according to claim 7, characterized in that: the central axis of the upper oblique nozzle unit is at an elevation angle of 30° to 60° from the horizontal plane, and the lower oblique nozzle unit The central axis of the pipe unit forms a depression angle of 30°-60° with the horizontal plane, and the central axis of the mid-bevel nozzle unit forms an included angle of 30°-60° with the central plane. 9. A control method for the waverider aircraft according to any one of claims 1 to 8, characterized in that the combined control of the waverider aircraft is carried out according to the size of the incoming flow pressure of the waverider aircraft during flight, specifically comprising the following operate: When the incoming flow pressure is less than 100 Pa, the effective control of the attitude of the waverider aircraft is realized by using the two sets of obliquely cut nozzles; When the incoming flow pressure is greater than 460 Pa, the full-motion control rudder and the embedded control surface are used for combined manipulation, so as to effectively control the attitude of the waverider aircraft; When the incoming flow pressure is between 100 Pa and 460 Pa, the two sets of oblique nozzles, the full-motion control rudder and the embedded control surface are used for joint combined manipulation to realize effective control of the attitude of the waverider aircraft. 10. The control method of the waverider aircraft according to claim 9, characterized in that: The control method of the full-motion control rudder is specifically as follows: by making the full-motion control rudder deflect the same angle in the same direction, the control of the pitch channel of the waverider is realized; by making the full-motion control rudder differentially deflect the same angle, Realize the control of the roll channel of the waverider aircraft; realize the roll and yaw control of the waverider aircraft by deflecting the full-motion control rudder at different angles; The control method of the embedded control surface is specifically: by deflecting the embedded control surface set on the upper surface of the waverider at the same angle in the same direction or making the embedded control surface set on the lower surface in the same direction By deflecting at the same angle, the control of the pitch channel of the waverider is realized; by making the differential deflection of the embedded control surface set on the upper surface of the waverider aircraft or the differential deflection of the embedded control surface set on the lower surface of the waverider aircraft, realizing Controlling the pitch, yaw and roll channels of the waverider aircraft; by deflecting the embedded control plane on the upper surface of the waverider aircraft upwards, and simultaneously deflecting the embedded control plane on the lower surface downwards, to increase The damping of the aerodynamic layout of the Mahayana wave aircraft; The control method of the two groups of obliquely-cut nozzles is specifically: by making the two groups of obliquely-cut nozzles inject air obliquely upward or obliquely downward, the control of the pitch channel of the waverider aircraft is realized; by making the two groups of obliquely-cut nozzles A group of obliquely cut nozzles sprays air outwards to realize the control of the yaw channel of the waverider aircraft; by making one group of obliquely cut nozzles inject air upwards and the other group of obliquely cut nozzles injects air downwards, the control of the roll channel of the waverider aircraft is realized. control.

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