Sweepback wing scaling wing deformation device with variable elongation and deformation method of sweepback wing scaling wing deformation device

Abstract

The invention discloses a variable-elongation sweepback wing scaling wing deformation device and a deformation method thereof, and relates to the technical field of deformation mechanism design of variant aircrafts, the aerodynamic configuration of a variable-elongation sweepback wing scaling wing is composed of a fuselage section, a sweepback fixed section and a telescopic section, the fuselage section is composed of a fuselage shell and an upper hatch cover, and the upper hatch cover is composed of an upper hatch cover and a lower hatch cover. The sweepback fixed section is composed of an upper wing surface shell and a lower wing surface shell, the telescopic section is an independent telescopic wing shell, the fuselage section and the shell of the sweepback wing fixed section are fixed through a sunk screw, and therefore it is guaranteed that the aerodynamic shape meets the aerodynamic design requirement; the linear guide rail is fixedly connected to the lower wing surface shell, and the telescopic wing can move along the linear guide rail; electric push rods are used for driving and are fixed in the fuselage, and inner rods of the electric push rods are connected with the telescopic wings, so that the telescopic wings are controlled to move along the linear guide rails; according to the method, the aerodynamic configuration of the scaled wing is segmented, so that the aerodynamic configuration and internal movement components of the scaled wing are mounted, and the extension length of the wing is changed by driving the telescopic wing to move along the linear guide rail through the electric push rod, so that the lift-drag ratio of the aircraft in the flying process is changed; the method can provide an implementation method for the equivalent scaling experiment of the deformable wing.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of variable aircraft morphing mechanism design, in particular to a variable sweep wing structure and installation method for realizing dynamic adjustment of aerodynamic performance by changing wing span. BACKGROUND

[0002] The geometric parameters of the wings of traditional fixed-wing aircraft are unchangeable, and it is difficult to simultaneously meet the optimal aerodynamic efficiency in different flight stages (such as take-off, cruising, and maneuvering). Variable aircraft emerges as the times require, and the development of variable aircraft is mainly to break through the performance limitations of traditional fixed configuration aircraft, and automatically switch to the optimal aerodynamic configuration in different flight stages (such as take-off, cruising, and high-speed penetration) by changing the shape (such as the shape, area or camber of the wing) and area of the wing in real time, so as to significantly improve the flight efficiency, expand the flight envelope and enhance the task adaptability. Its value lies in improving the overall efficiency, for example, expanding the high-aspect-ratio wing during cruising to reduce fuel consumption, and reducing the resistance by retracting the wing during high-speed flight; balancing the safety of low-speed take-off and high-speed maneuvering, and adapting to complex task scenarios (such as long-time reconnaissance and sudden penetration); and optimizing the adaptability to different altitudes, speeds and weather conditions through active deformation.

[0003] The variable aircraft usually needs to go through subsonic and supersonic stages. In the supersonic wind tunnel experiment, due to the influence of the wind tunnel experiment site, the equal ratio model cannot be directly used, and therefore the actual model needs to be scaled down, and the scaled-down model needs to be subjected to wind tunnel experiment, so as to measure the aerodynamic parameters of the equal ratio model. The present application realizes the installation of the aerodynamic shape and the internal moving components of the scaled-down wing, guarantees the consistency of the aerodynamic shape and the design, changes the span of the wing by driving the extension wing to move along the linear guide rail by the electric push rod, thereby changing the lift-drag ratio of the aircraft during flight, and measuring the deformation performance of the wing. The present application provides an implementation method for the equivalent scaled-down experiment of the deformation wing. SUMMARY

[0004] In view of the limitations of the fixed aerodynamic shape of the existing aircraft, in combination with the size limitation of the supersonic wind tunnel, the present application proposes a variable-span variable sweep wing deformation method of the scaled-down wing, realizes the consistency of the aerodynamic shape of the scaled-down wing and the design, realizes the continuous adjustment of the span of the wing during flight, thereby changing the lift-drag ratio of the aircraft during flight, and provides a method for the scaled-down experiment of the deformation wing.

[0005] The present application is implemented in the following manner: a variable-span variable sweep wing deformation device, characterized in that the deformation device comprises an aerodynamic shape, a driving mechanism and a deformation mechanism. The aerodynamic shape comprises a fuselage section, a fixed back-swept section and a telescopic section, the cabin is connected with the upper canopy to form the fuselage section, the lower wing surface is connected with the upper wing surface to form the fixed back-swept section, and the telescopic section is a single telescopic wing shell, the fixed back-swept section is fixedly connected with the cabin, and the telescopic wing can move along the internal linear guide rail to realize the expansion state and the contraction state of the wing. The driving mechanism comprises an electric push rod, one end of the electric push rod is fixedly connected with the cabin, the electric push rod passes through the limiting hole formed by the lower wing surface and the upper wing surface, and the electric push rod passes through the reserved hole of the telescopic wing; the inner rod of the electric push rod is connected with the screw rod through threads; the screw rod is connected with the bearing; the bearing is directly attached to the stepped hole in the telescopic wing; the compensating block is connected with the telescopic wing through a countersunk screw; the compensating block is in contact with the bearing; the telescopic wing is connected with the guide rail block through the adapter block; the linear guide rail is fixedly connected on the lower wing surface, and the telescopic wing can slide along the linear guide rail. The transformation mechanism comprises that the inner rod of the electric push rod pushes the screw rod, the screw rod pushes the bearing, the bearing can eliminate the rotary motion generated by the inner rod of the electric push rod, the compensating block presses the bearing, so that the pushing force of the inner rod of the electric push rod is transmitted to the telescopic wing, the telescopic wing is connected with the linear guide rail block through the adapter block, and the telescopic wing slides along the linear guide rail under the action of the pushing force of the inner rod of the electric push rod; the electric push rod is provided with a limiting switch, so that the wing contraction and expansion state is realized.

[0006] Further, the telescopic wing in the aerodynamic shape moves in the cavity of the fixed back-swept section composed of the upper wing surface and the lower wing surface, the movement direction is parallel to the trailing edge line of the fixed back-swept section, the cavity of the fixed back-swept section composed of the upper wing surface and the lower wing surface is slightly larger than the airfoil of the telescopic wing, so as to ensure the integrity of the aerodynamic shape and the movement accuracy of the telescopic wing; the front end and the rear end of the cabin are provided with interfaces, which are connected with the front fuselage and the rear fuselage of the aircraft.

[0007] Further, the upper canopy and the cabin in the aerodynamic shape are connected through a countersunk screw, the upper wing surface and the lower wing surface are connected through a countersunk screw, and the countersunk screw reduces the error of the aerodynamic shape.

[0008] Further, the linear guide rail is connected with the lower wing surface through a screw and is completely attached, and the installation direction of the linear guide rail is parallel to the trailing edge of the fixed back-swept section.

[0009] Further, the electric push rod is provided with a limiting switch, which corresponds to the contraction and expansion state of the wing, in the contraction state, the electric push rod is in the telescopic wing and has no contact with the telescopic wing, the installation direction of the electric push rod is parallel to the installation direction of the linear guide rail, so as to ensure the transmission efficiency and the transmission accuracy.

[0010] In the transformation method of the variable-length back-swept wing contraction ratio wing transformation device, the driving mechanism is divided into two working states, namely the contraction state and the expansion state. In the take-off and dive state of the aircraft, the retractable wing is in the retracted state, that is, the wing tip plane of the retractable wing coincides with the wing tip plane of the fixed rear-swept section composed of the upper and lower wing surfaces; the inner rod of the electric push rod pulls the retractable wing to move along the linear guide rail to the built-in limit switch of the electric push rod, so that the retraction of the retractable wing is realized; In the cruise stage of the aircraft, the retractable wing is in the expanded state, the inner rod of the electric push rod pushes the retractable wing to move along the linear guide rail to the built-in limit switch of the electric push rod, so that the expansion of the retractable wing is realized, the aerodynamic shape of the wing is changed, and the lift-drag ratio of the wing is improved.

[0011] The variable-span rear-swept wing scale model wing deformation method provided by the application has the following advantages: The variable-span rear-swept wing scale model wing deformation method provided by the application has the following advantages:

[0012] The aerodynamic shape of the variable-span rear-swept wing scale model wing is composed of a fuselage section, a rear-swept fixed section and a retractable section, the fuselage section is composed of a fuselage shell and an upper hatch, the rear-swept fixed section is composed of upper and lower wing surface shells, the retractable section is a separate retractable wing shell, the shells of the fuselage section and the rear-swept wing fixed section are fixed by countersunk screws, so that the aerodynamic shape meets the aerodynamic design requirements; the linear guide rail is fixedly connected to the lower wing surface shell, and the retractable wing can move along the linear guide rail; the drive is provided by the electric push rod, the electric push rod is fixed inside the fuselage, the inner rod of the electric push rod is connected to the retractable wing, so as to control the movement of the retractable wing along the linear guide rail; the method realizes the installation of the aerodynamic shape of the scale model wing and the internal movement components by dividing the aerodynamic shape of the scale model wing, and changes the lift-drag ratio of the aircraft during flight by driving the retractable wing to move along the linear guide rail through the electric push rod, thereby providing an implementation method for equivalent scale experiment of the deformable wing. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 The figure is the overall aerodynamic shape of the initial state of the wing; Figure 2 The figure is a linear guide rail mechanism diagram of the wing; Figure 3 The figure is a structure diagram of the retractable wing connecting part; Figure 4 The figure is a top view of the retracted state of the wing; Figure 5Figure 2 is a plan view of the wing in the deployed state; Wherein, 1 - cabin, 2 - upper hatch, 3 - lower wing surface, 4 - upper wing surface, 5 - telescopic wing, 6 - supplementary block, 7 - linear guide rail, 8 - guide rail slider, 9 - adapter block, 10 - electric push rod, 11 - electric push rod inner rod, 12 - screw, 13 - bearing. DETAILED DESCRIPTION

[0014] In order to make the technical problems, technical solutions and beneficial effects solved by the present application more clear and obvious, the present application will be further described in detail below in combination with the drawings and examples. It should be understood that the specific examples described herein are only used to explain the present application and do not limit the present application.

[0015] As shown in Figures 1-5 the present application includes cabin 1, upper hatch 2, lower wing surface 3, upper wing surface 4, telescopic wing 5, supplementary block 6, linear guide rail 7, guide rail slider 8, adapter block 9, electric push rod 10, electric push rod inner rod 11, screw 12, bearing 13. The cabin 1 is the main force structure, the lower wing surface 3 is fixed to the cabin 1 by screws, the linear guide rail 7 completely matches the installation plane reserved on the lower wing surface 3, and is fixed on the lower wing surface by screw connection, the installation direction is parallel to the trailing edge line of the lower wing surface 3.

[0016] The screw 12 is connected with the electric push rod inner rod 11 through threads, the telescopic wing 5 has a stepped hole reserved inside, the electric push rod 10 is in the hole reserved in the telescopic wing 5 and does not contact the telescopic wing 5, the bearing 13 is connected with the end without threads of the screw from the tail of the telescopic wing, the supplementary block 6 presses the bearing 13, the supplementary block is connected with the telescopic wing 5 through countersunk screws, the lower wing surface 3 has a movement channel slightly larger than the airfoil of the telescopic wing 5, the movement direction of the telescopic wing 5 is parallel to the trailing edge line of the lower wing surface 3, the telescopic wing 5 is connected with the guide rail slider 8 through the adapter block 9, the telescopic wing 5 can move along the linear guide rail 7, the telescopic wing 5 has no jamming in the movement process, the electric push rod 10 is fixed on the cabin 1, the power is turned on, the electric push rod 10 is controlled, the telescopic wing 5 can make telescopic movement along the guide rail 7, the movement process of the telescopic wing 5 is limited by the limit switch built in the electric push rod 10, the upper wing surface 4 is connected with the lower wing surface 3 through countersunk screws to form a complete fixed back-swept section, the upper hatch 2 is connected with the cabin 1 through countersunk screws to form a complete fuselage section, so that the designed aerodynamic shape is obtained.

[0017] The installation direction of the linear guide rail 10 is parallel to the trailing edge line of the lower wing surface 3, the linear guide rail 10 determines the deployment direction of the telescopic wing 5, the telescopic wing 5 can significantly improve the lift-drag ratio of the wing along this direction, so that good aerodynamic characteristics are obtained.

[0018] The driving mechanism mainly has two working states, including the retracted state and the deployed state.

[0019] In the take-off and dive phase of the aircraft, the driving mechanism needs to move the retractable wing 5 from the initial state to the retracted state (as shown in Figure 4 ). The electric push rod 10 drives the retractable wing 5 to move along the linear guide rail 7 to the limit switch built in the electric push rod. At this time, the wing tip plane of the retractable wing 5 coincides with the wing tip plane of the backward swept section, that is, the retracted state of the wing (as shown in Figure 4 ) can be realized.

[0020] In the cruise phase of the aircraft, the driving mechanism needs to move the retractable wing 5 from the retracted state (as shown in Figure 4 ) to the expanded state (as shown in Figure 5 ). The electric push rod 10 drives the retractable wing 5 to move along the linear guide rail 7 to the limit switch built in the electric push rod. At this time, the retractable wing is in the completed expanded state, which improves the lift-drag ratio of the wing, that is, the expanded state of the wing (as shown in Figure 5 ) can be realized.

[0021] The above is only the preferred embodiment of the present application. It should be noted that for those skilled in the art, without departing from the principles of the present application, a number of improvements can be made, and these improvements should also be considered as the protection of the present application.

Claims

1. A variable span, rear swept wing, scaled wing morphing apparatus, characterized by, The morphing device comprises a pneumatic shape, a driving mechanism and a morphing mechanism. The pneumatic shape comprises a fuselage section, a fixed section of a swept wing and a telescopic section, the fuselage section is formed by connecting a cabin (1) and an upper canopy (2), the fixed section of the swept wing is formed by connecting a lower wing surface (3) and an upper wing surface (4), and the telescopic section is a separate telescopic wing (5) shell. The driving mechanism comprises an electric push rod (10), one end of the electric push rod (10) is fixedly connected with the cabin (1), the electric push rod (10) passes through a limiting hole formed by the lower wing surface (3) and the upper wing surface (4), and the electric push rod (10) passes through a reserved hole of the telescopic wing (5). The inner rod (11) of the electric push rod is threadedly connected with a screw rod (12), the screw rod (12) is connected with a bearing (13), the bearing (13) is directly attached to a stepped hole in the telescopic wing (5), a shape-filling block (6) is connected with the telescopic wing (5) through a countersunk screw, the shape-filling block (6) is in contact with the bearing (13), the telescopic wing (5) is connected with a guide rail sliding block (8) through an adapter block (9), and the linear guide rail (7) is fixedly connected with the lower wing surface (3).

2. A variable span rear swept wing scaled wing morphing device according to claim 1, wherein, The telescopic wing (5) is connected with the linear guide rail sliding block (8) through the adapter block (9), and the telescopic wing (5) slides along the linear guide rail (7) under the action of the pushing force of the inner rod (11) of the electric push rod.

3. A variable span rear swept wing scaled wing morphing apparatus according to claim 1, wherein, The telescopic wing (5) in the pneumatic shape moves in the cavity of the fixed section of the swept wing formed by the upper wing surface (4) and the lower wing surface (3), the movement direction is parallel to the trailing edge line of the fixed section of the swept wing, the cavity of the fixed section of the swept wing formed by the upper wing surface (4) and the lower wing surface (3) is slightly larger than the airfoil of the telescopic wing (5), the integrity of the pneumatic shape is ensured, and the movement accuracy of the telescopic wing (5) is ensured.

4. A variable span rear swept wing scaled wing morphing apparatus according to claim 1, wherein, The front end and the rear end of the cabin (1) are provided with interfaces, and the interfaces are connected with the front section of the fuselage and the rear section of the fuselage of the aircraft. The upper canopy (2) and the cabin (1) are connected through countersunk screws, the upper wing surface (4) and the lower wing surface (3) are connected through countersunk screws, and the countersunk screws reduce the error of the pneumatic shape. The linear guide rail (7) is connected with the lower wing surface (3) through a screw and is completely attached, and the installation direction of the linear guide rail (7) is parallel to the trailing edge of the fixed section of the swept wing.

5. A variable span rear swept wing scaled wing morphing apparatus according to claim 1, wherein, The electric push rod (10) is provided with a built-in limit switch, corresponding to the contraction and expansion state of the wing, in the contraction state, the electric push rod (10) is inside the telescopic wing (5) and has no contact with the telescopic wing (5), the installation direction of the electric push rod (10) is parallel to the installation direction of the linear guide rail (7), so as to ensure the transmission efficiency and transmission accuracy.

6. The morphing method of a variable-span, rear-swept wing of a scale model wing morphing apparatus according to any one of claims 1 to 5, characterized in that, The driving mechanism has two working states, which are contraction state and expansion state respectively. In the take-off and diving state of the aircraft, the telescopic wing (5) is in the contraction state, that is, the wing tip plane of the telescopic wing (5) coincides with the wing tip plane of the fixed sweepback section composed of the upper wing surface (4) and the lower wing surface (3); the inner rod (11) of the electric push rod pulls the telescopic wing (5) to move along the linear guide rail (7) to the built-in limit switch of the electric push rod (10), so as to realize the contraction of the telescopic wing (5); In the cruising stage of the aircraft, the telescopic wing (5) is in the expansion state, the inner rod (11) of the electric push rod pushes the telescopic wing (5) to move along the linear guide rail (7) to the built-in limit switch of the electric push rod (10), so as to realize the expansion of the telescopic wing (5), change the aerodynamic shape of the wing, and improve the lift-drag ratio of the wing.

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