A tailless wide-speed-range aircraft based on vortex wave effect and a control method thereof

Abstract

The application provides a tailless wide-speed-range aircraft based on vortex wave effect and a control method thereof. The aircraft comprises a body, the body comprises a fuselage and a wing, the wing and the fuselage form a blended wing body layout, the wing comprises an inner wing and an outer wing, the inner wing is provided with an inboard elevator and an outboard elevator, the outer wing is provided with an aileron, a wing trailing edge resistance rudder and a wing embedded resistance rudder, and the tail of the fuselage is provided with a fuselage lift resistance rudder. The application optimizes the characteristics of the wing windward shock wave and the leeward vortex, realizes wide-speed-range lift generation and wave resistance reduction. The tailless wing layout reduces the radar reflection cross section, and the smooth blended wing body design improves the stealth performance. The multi-surface coordinated control strategy solves the lateral static instability problem of the tailless aircraft, and meets the wide-speed-range control demand. The layout flexibility is improved, the functions of the inner and outer wings and the surfaces are divided, and the aerodynamic control and structural performance of the aircraft are optimized.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a tailless wide-speed-range aircraft based on vortex wave effect and a control method thereof. BACKGROUND

[0002] With the development of aerospace technology, aircraft gradually develops in the direction of high stealth, wide speed range adaptability and multi-task adaptability. However, the performance matching of the traditional aircraft aerodynamic layout between high speed and low speed is difficult to balance, and the optimization of stealth performance and control performance is also bottlenecked due to the tail wing layout. The tailless aircraft is concerned due to its unique aerodynamic layout and stealth performance, but the flight range of the current tailless aircraft is limited to subsonic speed and narrow range flight.

[0003] As an important theory of modern aerodynamics, vortex wave effect can realize significant improvement of aerodynamic performance through coordinated optimization of the shock wave on the windward surface of the wing and the vortex on the leeward surface, which provides a new idea for solving the wide-speed-range adaptability problem of tailless aircraft. SUMMARY

[0004] The purpose of the present application is to provide a tailless wide-speed-range aircraft based on vortex wave effect and a control method thereof, which breaks through the limitation of traditional layout by integrating vortex wave effect aerodynamic design, tailless structure design and multi-rudder surface coordinated control strategy, realizes good wide-speed-range aerodynamic performance and stealth characteristics, and adapts to complex flight conditions from subsonic speed to supersonic speed.

[0005] According to one purpose of the present application, the present application provides a tailless wide-speed-range aircraft based on vortex wave effect, comprising a body, the body comprising a fuselage and a wing, the wing and the fuselage forming a blended wing body layout, the wing comprising an inner wing and an outer wing, the inner wing being provided with an inboard elevator and an outboard elevator, the outer wing being provided with ailerons, a wing trailing edge drag rudder and a wing embedded drag rudder; the tail of the fuselage is provided with a fuselage lift rudder.

[0006] Further, the wing leading edge is designed as a double sweep curve, the inner wing sweep angle is 80°, and the outer wing sweep angle is 45°.

[0007] Further, the rudder shaft of the fuselage lift rudder is at an angle of 30°-60° with the longitudinal symmetry plane of the body.

[0008] Further, the inboard elevator and the outboard elevator realize pitch control by synchronous deflection.

[0009] Further, the ailerons realize roll control by left-right reverse deflection.

[0010] Further, the wing trailing edge drag rudder and the wing embedded drag rudder realize low speed yaw control through synchronous reverse deflection.

[0011] Further, the fuselage lift rudder generates asymmetric lift through deflection to realize high speed yaw control.

[0012] Further, the aircraft adopts a drag control strategy at subsonic speed and a lift control strategy at supersonic speed.

[0013] According to another purpose of the present application, the present application provides a control method of the above-mentioned tailless wide speed range aircraft based on the vortex wave effect, comprising the following steps:

[0014] Pitch control: pitch moment adjustment is realized through synchronous deflection of the inboard elevator and the outboard elevator;

[0015] Roll control: reverse deflection of the aileron provides roll moment, and the aileron is arranged close to the outer wing area, which improves the roll sensitivity;

[0016] Lateral control includes drag control and lift control: wherein,

[0017] Drag control: reverse deflection of the wing trailing edge drag rudder and the wing embedded drag rudder generates yaw moment, which is suitable for low speed control;

[0018] Lift control: asymmetric lift generated by the fuselage lift rudder provides yaw control, which is suitable for high speed state.

[0019] Further, at subsonic speed Ma<1, the drag control is mainly used, and the lift control is used as an auxiliary;

[0020] At supersonic speed Ma≥1, the lift control is mainly used, and the drag control is used as an auxiliary.

[0021] The technical scheme of the present application optimizes the characteristics of the shock wave on the windward surface of the wing and the vortex on the leeward surface based on the vortex wave effect, realizes wide speed range lift generation and wave drag reduction. The tailless wing layout reduces the radar reflection cross section, and the smooth wing-body fusion design improves the stealth performance. The multi-surface collaborative control strategy solves the problem of lateral static instability of the tailless aircraft, while meeting the wide speed range control requirements. The layout flexibility is improved, and through the function partition of the inner and outer wings and the rudder surface, the aerodynamic control and structural performance of the aircraft are optimized. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the specific embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the specific embodiments or prior art description. Obviously, the drawings described below are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0023] Fig. 1 It is a top view structural schematic diagram of the embodiment of the present application.

[0024] Fig. 2 It is a bottom view structural schematic diagram of the embodiment of the present application.

[0025] Fig. 3 It is a rear view structural schematic diagram of the embodiment of the present application.

[0026] In the figure: 1, fuselage; 2, wing; 3, inner wing; 4, outer wing; 5, inboard elevator; 6, outboard elevator; 7, aileron; 8, wing trailing edge drag rudder; 9, wing embedded drag rudder; 10, fuselage lift rudder. DETAILED DESCRIPTION

[0027] The technical solutions of the present application will be described below in conjunction with the embodiments, obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the present application.

[0028] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0029] In addition, the terms "first", "second", "third", etc. are used only for descriptive purposes and do not denote or imply relative importance or a number of indicated technical features. Thus, features defined with "first", "second", "third" can include one or more of the features explicitly or implicitly. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified. In addition, the terms "mounting", "connecting", "connection" should be broadly interpreted, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be direct connection, or indirect connection through intermediate medium, or internal communication of two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0030] Embodiment 1

[0031] As shown in Figs. 1-3

[0032] A tailless wide-speed-range aircraft based on vortex wave effect includes a body, the body including a fuselage 1 and a wing 2, the fuselage 1 and the wing 2 being arranged symmetrically, the wing 2 being arranged on both sides of the fuselage 1 and forming a blended wing body layout through vortex wave effect design. The leading edges of the fuselage 1 and the wing 2 adopt double sweep curve design to reduce wave resistance and improve lift performance.

[0033] In this embodiment, the wing 2 and the fuselage 1 form a smooth transition blended wing body, and the leading edges adopt double sweep curve design (inner wing sweep angle 80°, outer wing sweep angle 45°). The leading edge of the outer wing 2 realizes high-speed airflow diversion through embedded rudder, and the trailing edge enhances the yawing ability through rudder.

[0034] In this embodiment, the body is made of lightweight composite material, and the surface is covered with a wave-absorbing coating to enhance the stealth performance and adapt to high temperature environment.

[0035] The wing 2 includes an inner wing 3 and an outer wing 4, and the inner wing 3 and the outer wing 4 adopt segmented layout. The inner wing 3 is connected to the fuselage, and the inner wing 3 is fixed on both sides of the fuselage, and the inner side elevator 5 and the outer side elevator 6 are arranged to realize main lift generation and pitch control; specifically, the inner side elevator 5 is arranged on one side of the trailing edge of the inner wing 3 close to the fuselage, and the outer side elevator 6 is arranged on the trailing edge of the inner wing 3 and outside the inner side elevator 5.

[0036] In this embodiment, the inner side elevator is arranged on the trailing edge of the inner wing close to the fuselage for pitch control, and the outer side elevator is arranged on the outer side of the trailing edge of the inner wing for high-speed pitch adjustment.

[0037] The outer wing 4 is arranged on both sides of the inner wing 3, and includes ailerons 7, wing trailing edge resistance rudders 8 and wing embedded resistance rudders 9 to provide roll and yaw control. ​

[0038] In this embodiment, the aileron is arranged near the wing tip on the trailing edge of the outer wing to realize roll control; the wing trailing edge drag rudder is arranged on the trailing edge of the outer wing, and the wing embedded drag rudder is combined to provide low-speed yawing moment.

[0039] Specifically, the aileron is arranged on the trailing edge of the inner wing near one side of the outer wing, the wing trailing edge drag rudder is arranged on the trailing edge of the outer wing, and the wing embedded drag rudder is arranged on the front part of the upper surface of the outer wing.

[0040] The tail of the fuselage is configured with a fuselage lift rudder 10, which is arranged at the lower side of the tail of the fuselage and is used for lift yaw control at high speed.

[0041] In this embodiment, the angle between the rudder shaft of the fuselage lift rudder and the longitudinal symmetry plane of the machine body is preferably in the range of 30°-60°, and is preferably 45°.

[0042] In this embodiment, the fuselage mainly provides loading space for airborne equipment, payload and power system, and the wing mainly provides flight lift and control force, and the arrangement of elevators, ailerons and rudders on the wing meets the requirements of the aircraft on aerodynamic control and stability performance, so that the aircraft realizes controllable flight in the full speed range.

[0043] The tailless wide-speed-range aircraft based on the vortex wave effect adopts a cooperative control strategy:

[0044] When flying at subsonic speed (Ma<1), resistance control is mainly used, and lift control is auxiliary; through the reverse deflection of the wing trailing edge drag rudder and the wing embedded drag rudder, the yawing moment is generated by the resistance difference to realize lateral control.

[0045] When flying at supersonic speed (Ma≥1), lift control is mainly used, and resistance control is auxiliary; the fuselage lift rudder generates asymmetric lift for yaw control; the inner and outer wing elevators jointly adjust the pitching moment, and the aileron controls the rolling moment.

[0046] Specifically, the aircraft of the present application adopts a dynamic control strategy based on the speed range:

[0047] 3.1 Longitudinal control

[0048] Pitch control:

[0049] The pitching moment is adjusted by the synchronous deflection of the left and right elevators (inner and outer).

[0050] Advantages of double rudder configuration:

[0051] The inner elevators provide most of the control force, and the outer elevators enhance the response speed in high-speed flight.

[0052] 3.2 Lateral control

[0053] Roll control:

[0054] Rolling moment is provided by the counter deflection of the ailerons. The ailerons are arranged close to the outer wing region, which improves roll sensitivity.

[0055] 3.3 Lateral control

[0056] Drag-based control (subsonic):

[0057] Counter deflection of the trailing edge rudders and embedded rudders generates yawing moment, suitable for low speed control.

[0058] Lift-based control (supersonic):

[0059] Asymmetric lift generated by the fuselage lift rudders provides yaw control, suitable for high speed conditions.

[0060] 3.4 Dynamic synergy strategy

[0061] At subsonic speed (Ma < 1), drag-based control is the main, lift-based control is auxiliary;

[0062] At supersonic speed (Ma ≥ 1), lift-based control is the main, drag-based control is auxiliary.

[0063] This strategy enables the aircraft to maintain efficient control performance in different speed domains, while reducing the adverse effects on aerodynamic performance.

[0064] The invention is a tailless wide speed range aircraft based on vortex wave effect, which improves aerodynamic performance. The design based on vortex wave effect optimizes the characteristics of the shock wave on the windward surface of the wing and the vortex on the leeward surface, achieving wide speed range lift generation and wave drag reduction. Stealth performance optimization, the use of tailless layout reduces the radar reflection cross section, and the smooth wing-body fusion design improves stealth performance. Enhanced control performance, the multi-surface control strategy solves the problem of lateral static instability of tailless aircraft, while meeting the wide speed range control demand. Layout flexibility is improved, through the functional division of the inner and outer wings and the rudder, the aerodynamic control and structural performance of the aircraft are optimized.

[0065] Vortex wave effect is a modern aerodynamic technology that uses the interaction of vortex and shock wave of high-speed airflow to optimize aerodynamic performance. Its applications include the following key points:

[0066] Vortex-enhanced lift, at low speed, the vortex formed on the leeward surface of the wing increases the local pressure difference, enhancing the lift coefficient. This enables the tailless aircraft to maintain good take-off and landing performance at lower speeds.

[0067] Shock wave control and drag reduction, at high speed, the leading edge of the wing and fuselage will generate shock waves. By optimizing the airfoil design and leading edge curve (such as double back-sweep angle design), the shock wave intensity can be reduced, and the wave drag can be reduced.

[0068] Adapt to wide speed range, vortex wave effect not only applies to subsonic (Ma<1) lift enhancement, but also has significant optimization effect on supersonic (Ma>1) flow stability.

[0069] The theory provides a theoretical basis for the aircraft design of the application, so that the aircraft can maintain the stability of aerodynamic performance and maneuverability in the full speed range.

[0070] The application can further optimize the dynamic control performance of the rudder surface, monitor the aircraft attitude, speed and aerodynamic environment in real time based on multi-sensor fusion technology through an intelligent control system, dynamically adjust the deflection angle of the multi-rudder surface through embedded algorithm, and realize efficient collaborative control. Through adaptive control strategy, the inner and outer wing elevators provide stable pitch moment during take-off and landing stage; during the cruising stage, the embedded rudder cooperates with the lift-type rudder to adjust the yaw, and reduces the control energy consumption.

[0071] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the application, and not to limit them; although the application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the application.

Claims

1. A tailless wide speed range aircraft based on the effect of vortex waves, characterized in that, The aircraft includes a fuselage, the fuselage includes a body and a wing, the wing and the body form a blended wing body layout, the wing includes an inner wing and an outer wing, the inner wing is configured with an inboard elevator and an outboard elevator, the outer wing is configured with ailerons, a wing trailing edge drag rudder and a wing embedded drag rudder; the tail of the body is provided with a body lift rudder; the wing leading edge is designed as a double sweep curve, the inner wing sweep angle is 80°, and the outer wing sweep angle is 45°; the rudder shaft of the body lift rudder is 30°-60° with the longitudinal symmetry plane of the fuselage; the inboard elevator and the outboard elevator realize pitch control through synchronous deflection; the ailerons realize roll control through left-right reverse deflection; the wing trailing edge drag rudder and the wing embedded drag rudder realize low-speed yaw control through synchronous reverse deflection; the body lift rudder realizes high-speed yaw control through deflection to generate asymmetric lift; the aircraft adopts a drag control strategy at subsonic speed and a lift control strategy at supersonic speed.

2. The control method of the vortex-based effect-based tailless wide speed range aircraft according to claim 1, characterized by, The method comprises the following steps: Pitch control: synchronous deflection of the inboard elevator and the outboard elevator realizes pitch moment adjustment; Roll control: reverse deflection of the ailerons provides roll moment, and the ailerons are arranged near the outer wing area, which improves the roll sensitivity; Lateral control includes drag control and lift control: Drag control: reverse deflection of the wing trailing edge drag rudder and the wing embedded drag rudder generates yaw moment, which is suitable for low-speed control; Lift control: asymmetric lift generated by the body lift rudder provides yaw control, which is suitable for high-speed state.

3. The control method of the vortex-based tailless broadband flight vehicle according to claim 2, wherein At subsonic speed Ma < 1, drag control is mainly used, and lift control is auxiliary; at supersonic speed Ma ≥ 1, lift control is mainly used, and drag control is auxiliary.

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