A deformation mechanism for the front middle section of a supersonic aircraft cabin

Abstract

The present invention discloses a deformation mechanism for the front middle section of a supersonic aircraft cabin. The driving mechanism includes a curved beam, which is the main load-bearing structure of the driving mechanism and is fixed to the front and rear ends of the front middle section of the aircraft cabin; four fan-shaped bottom plates of the same size are equally fixedly connected to the curved beam; a linear guide rail is connected to and fully fits the bottom of the curved beam, and a linear motor group is provided on the linear guide rail, which moves along the linear guide rail; the linear motor group is connected to a slider group through a push rod; a guide rail is provided on the fan-shaped bottom plate for the slider group to move up and down; a synchronous connecting rod passes through the holes on the slider group and the perforated plate to realize the synchronous movement of the slider group; the driving mechanism of the present invention is a synchronous motion device of three groups of slider mechanisms driven by a single motor module, which realizes the problem that the front middle section of a single aircraft cabin has a variable lift-to-drag ratio to meet different flight missions.

Description

Technical Field

[0001] The present invention relates to the technical field of design of deformation mechanisms of variant aircraft, in particular to an aerodynamic shape deformation mechanism of the front section of a supersonic aircraft cabin. Background Art

[0002] Supersonic aircraft mainly refer to aircraft powered by scramjet engines and capable of flying in the atmosphere at speeds exceeding the speed of sound. The waverider cabin mid-front section design adopted by supersonic aircraft can increase the air infiltration area at the bottom of the mid-front section of the cabin, which is suitable for maintaining a high lift coefficient in supersonic flight environments. Currently, most supersonic aircraft adopt a fixed aerodynamic shape, which is a compromise between the flight speed and lift-to-drag ratio of the aircraft by the designer, and it is difficult to adapt to the complex and changing flight environment. At the same time, with the development of science and technology, people's requirements for the mechanical efficiency, mechanism reliability, deformation synchronization, space utilization, etc. of the deformation mechanism are constantly increasing. However, most of the deformation mechanisms currently use a single motor to drive a single mechanism, and a single mechanism is difficult to achieve multi-dimensional deformation, resulting in problems such as large space occupancy of the deformation drive mechanism, low reliability of multiple motors, and poor deformation synchronization. Summary of the Invention

[0003] In response to the limitations of the fixed aerodynamic shape of existing supersonic aircraft, the present invention proposes a deformation mechanism for continuously and reversibly changing the aerodynamic shape of the front section of the supersonic aircraft cabin. This mechanism can meet the requirements of high-precision performance of the aerodynamic shape and broaden the flight speed range of the aircraft.

[0004] The present invention is achieved in that:

[0005] A deformation mechanism for the front middle section of a supersonic aircraft cabin, characterized in that the driving mechanism comprises a bending beam (1), four fan-shaped bottom plates (2) of the same size are equally fixedly connected to the bending beam (1); a linear guide rail (3) is connected to and completely fits the bottom of the bending beam (1), a linear motor group (4) is provided on the linear guide rail (3), and the linear motor group (4) moves along the linear guide rail (3); the linear motor group (4) is connected to a slider group (6) via a push rod (5); the fan-shaped bottom plate (2) is provided with a guide rail, The slider group (6) can be moved up and down; the slider group (6) is fixed to the corresponding perforated plate (9), and the synchronous connecting rod (8) passes through the hole on the perforated plate (9) to achieve the synchronous movement of the slider group (6) and the perforated plate (9); the perforated plate (9) is fixedly connected to the U-shaped push frame (7); the curved beam (1) is used as the main structure to improve the space utilization efficiency, and the fan-shaped bottom plate (2) is installed perpendicular to the central axis of the curved beam (1), which is convenient for installation and improves the bearing capacity of the main structure under high pressure environment. The slider group (6) includes left, right and middle sliders.

[0006] The deformation mechanism is a synchronous motion device in which three groups of slider mechanisms are driven by a single motor module, that is, the linear motor group (4) drives the slider fixed on the surface to move, and the slider movement drives the push rod (5) to move in the XZ plane. The movement of the push rod (5) drives the slider located in the middle, which is constrained on the guide rail of the fan-shaped bottom plate (2), to move up and down. The slider located in the middle is fixed to the U-shaped push rack (7). At the same time, the U-shaped push rack (7) located in the middle is fixed to the synchronous connecting rod (8). The synchronous connecting rod (8) passes through the perforated plate (9) on the left and right respectively. When the slider located in the middle moves up and down, the synchronous connecting rod (8) pushes the perforated plates (9) on the left and right and the slider fixed thereto to move up and down along the guide rail to achieve synchronous expansion or contraction.

[0007] Furthermore, the driving mechanism further comprises a skin (11), which is a flexible composite material capable of achieving tensile deformation within a certain range; the upper portion of the skin (11) is fitted with the front section of the aircraft cabin and has a fixed shape; the lower portion is fitted with a U-shaped push frame (7) of the deformation driving device to achieve switching of the aerodynamic shape of the front section of the aircraft cabin; the bending beam (1) is the main load-bearing structure of the driving mechanism, and the bending beam (1) is fixed to the front and rear ends of the front section of the aircraft cabin.

[0008] Furthermore, the linear guide rail (3) is connected to the bending beam (1) via a countersunk set screw and is completely fitted thereto, and the motion stroke of the linear motor group (4) on the bending beam (1) is constrained by a limit switch (10) to ensure the motion accuracy and stability of the drive mechanism.

[0009] Furthermore, the linear motor group (4) realizes the synchronous movement of the three sliders through a single motor in the form of a slider-connecting rod mechanism.

[0010] Furthermore, the linear motor group (4) is composed of four motor modules, which can respectively drive the slider-push frame modules on the four sets of fan-shaped base plates (2), thereby achieving high-precision surface control of the aerodynamic shape of the front section of the supersonic aircraft cabin.

[0011] The present invention provides a deformation mechanism for the front middle section of a supersonic aircraft cabin, characterized in that the driving mechanism is divided into three working states, including an initial state, a retracted state, and an extended state;

[0012] When the aircraft is in the take-off to cruising stage, the driving mechanism needs to move the skin (11) of the front section of the aircraft cabin from the initial state to the extended state; the linear motor group (4) moves synchronously along the axial direction of the bending beam (1) to the position of the limit switch (10), and pushes the skin outward to finally reach the extended state;

[0013] When the aircraft moves from cruising to ground diving, the driving mechanism needs to move the front skin (11) of the aircraft cabin from an extended state to a retracted state; the linear motor group (4) moves synchronously along the axial direction of the bending beam (1) to the position of the limit switch (10), loosening the skin and finally returning it to the retracted state.

[0014] The beneficial effects of the present invention are:

[0015] 1. This invention solves the problem of an aircraft's fixed lift-to-drag ratio and low fuel efficiency during high-speed flight missions, achieving a single aircraft cabin with a variable lift-to-drag ratio in the front section to meet different flight missions.

[0016] 2. The present invention discloses a device for synchronously moving three sets of slider mechanisms driven by a single motor module, which can achieve precise control and greatly improve the synchronization and stability of the mechanism's movement;

[0017] 3. The structure and movement process of the present invention are simple and highly universal; multiple sets of U-shaped pushers operate synchronously, and the skin surface accuracy is adjustable, which fully meets the mission requirements of aircraft deformation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is an overall structural diagram of a deformation mechanism for the front middle section of a supersonic aircraft cabin according to the present invention;

[0019] Figure 2 This is a structural diagram of a deformation mechanism with a skin facing the front middle section of a supersonic aircraft cabin according to the present invention;

[0020] Figure 3 It is a side view of the initial state of the driving mechanism of the present invention;

[0021] Figure 4 It is a side view of the driving mechanism of the present invention in an extended state;

[0022] Figure 5 It is a side view of the retracted state of the driving mechanism of the present invention;

[0023] Figure 6 This is a detailed diagram of a single group of mechanisms of the present invention;

[0024] Figure 7 This is the outline of the front section of the aircraft cabin;

[0025] Among them, 1-bending beam, 2-fan-shaped base plate, 3-linear guide rail, 4-linear motor group (including slider), 5-push rod, 6-slider group, 7-U-shaped push rack, 8-synchronous connecting rod, 9-perforated plate, 10-limit switch, 11-skin. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and effect of the present invention clearer and more specific, the following examples are given to further illustrate the present invention in detail. It should be noted that the specific implementation described here is only used to explain the present invention and is not intended to limit the present invention.

[0027] like Figures 1 to 7 As shown, the present invention includes a bending beam 1, a fan-shaped base plate 2, a linear guide rail 3, a linear motor group (including a slider) 4, a push rod 5, a slider group 6, a U-shaped push frame 7, a synchronous connecting rod 8, a perforated plate 9, a limit switch 10, and a skin 11.

[0028] The curved beam 1 is the main load-bearing structure of the driving mechanism. The curved beam 1 is fixed to the front and rear ends of the middle and front sections of the aircraft cabin; four fan-shaped bottom plates 2 of the same size are equally fixedly connected to the curved beam 1; a linear guide 3 is connected to the bottom of the curved beam 1 and fits completely together, and a linear motor group 4 is provided on the linear guide 3, and the linear motor group 4 moves along the linear guide 3; the linear motor group 4 is connected to the slider group 6 through a push rod 5; a guide rail is provided on the fan-shaped bottom plate 2 for the slider group 6 to move up and down; the slider groups 6 are respectively fixed to the corresponding perforated plates 9, and the synchronous connecting rod 8 passes through the holes on the perforated plates 9 to achieve synchronous movement of the slider group 6 and the perforated plates 9; The driving mechanism is a synchronous motion device in which a single motor module drives three groups of slider mechanisms, that is, the movement of the linear motor 4 drives the movement of the slider fixed on the surface, and the movement of the slider drives the push rod 5 to make planar motion in the XZ plane. The movement of the push rod 5 drives the slider 6 located in the middle and constrained on the guide rail of the fan-shaped bottom plate 2 to move up and down. The slider 6 located in the middle is fixed to the U-shaped push rack 7. At the same time, the U-shaped push rack 7 located in the middle is fixed to the synchronous connecting rod 8. The synchronous connecting rod 8 passes through the perforated plate 9 on the left and right respectively. When the slider 6 located in the middle moves up and down, the synchronous connecting rod 8 pushes the left and right perforated plates 9 and the slider 6 fixed thereto to move up and down along the guide rail to achieve synchronous expansion or contraction.

[0029] The skin 11 is a flexible composite material that can achieve tensile deformation within a certain range. The upper half of the skin 11 fits with the front section of the aircraft cabin and has a fixed shape; the lower half fits with the U-shaped push frame 7 of the deformation drive device to achieve the switching of the aerodynamic shape of the front section of the aircraft cabin. The curved beam 1 is the main load-bearing structure of the drive mechanism, which is fixed to the front and rear ends of the front section of the aircraft cabin by bolt connection. Four fan-shaped base plates 2 of the same size are equally fixedly connected to the curved beam 1. The linear guide 3 is connected to the curved beam 1 by countersunk set screws and fits completely. The linear motor 4 moves along the linear guide 3 and is connected to the slider group 6 by the push rod 5. The fan-shaped base plate 2 is provided with a guide rail for the slider group 6 to move up and down. The synchronous connecting rod 8 passes through the holes on the slider group 6 and the perforated plate 9 to achieve synchronous movement of the slider group 6. The perforated plate 9 is fixedly connected to the U-shaped push frame. The motion stroke of the linear motor group 4 on the bending beam 1 is constrained by the limit switch 10 to ensure the motion accuracy and stability of the driving mechanism.

[0030] The driving mechanism is mainly divided into three working states, including an initial state, a retracted state, and an extended state.

[0031] During the aircraft's takeoff to cruise phase, the driving mechanism needs to move the front section of the aircraft cabin's skin 11 from its initial state (e.g. Figure 3 as shown) to the extended position (as shown) Figure 4 The linear motor group 4 is along the axial direction of the bending beam 1 (as shown). Figure 1 The coordinate system shown in the negative x direction) moves synchronously to the position of the limit switch 10, and the skin is pushed outward to the final extended state (as shown in the negative x direction). Figure 4 shown).

[0032] When the aircraft is in the stage of cruising to diving to the ground, the driving mechanism needs to move the front skin 11 of the aircraft cabin from the extended state (such as Figure 4 as shown) to the retracted state (as shown Figure 5 The linear motor group 4 is along the axial direction of the bending beam 1 (as shown). Figure 1 The coordinate system shown in the positive x direction) moves synchronously to the position of the limit switch 10, and the skin is relaxed and finally reaches the retracted state (as shown in the positive x direction). Figure 5 shown).

[0033] The above description is only a preferred specific embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements can be made without departing from the principles of the present invention. These improvements should also be regarded as protection of the present invention.

Claims

1. A deformation mechanism for the front middle section of a supersonic aircraft cabin, characterized in that: The driving mechanism comprises a bending beam (1), four fan-shaped bottom plates (2) of the same size are equally fixedly connected to the bending beam (1); a linear guide rail (3) is connected to the bottom of the bending beam (1) and is completely fitted therewith, a linear motor group (4) is provided on the linear guide rail (3), and the linear motor group (4) moves along the linear guide rail (3); the linear motor group (4) is composed of four motor modules, each of which is connected to a slider group (6) through a push rod (5); a guide rail is provided on the fan-shaped bottom plate (2) for allowing the slider group (6) to move up and down; the slider groups (6) are respectively fixed to corresponding perforated plates (9), and a synchronous connecting rod (8) passes through a hole on the perforated plate (9) to realize synchronous movement of the slider group (6) and the perforated plate (9); the perforated plate (9) is fixedly connected to a U-shaped push frame (7); The deformation mechanism is characterized in that each motor module drives the slider group to move synchronously, and the slider group is composed of three first sliders. The movement of each motor module drives the movement of the second slider fixed on the surface of each motor module, and the movement of the second slider drives the push rod (5) to move in the XZ plane; The movement of the push rod (5) drives the first slider located in the middle, which is constrained on the guide rail of the fan-shaped bottom plate (2), to move up and down. The first slider located in the middle is fixed to the middle perforated plate (9). At the same time, the middle perforated plate (9) is fixed to the synchronous connecting rod (8). The synchronous connecting rod (8) passes through the left and right perforated plates (9) respectively. When the first slider located in the middle moves up and down, the synchronous connecting rod (8) pushes the left and right perforated plates (9) and the first slider fixed thereto to move up and down along the guide rail, thereby realizing synchronous expansion or contraction.

2. The deformation mechanism for the front middle section of a supersonic aircraft cabin according to claim 1, characterized in that: The driving mechanism further comprises a skin (11), which is a flexible composite material capable of achieving tensile deformation within a certain range; the upper portion of the skin (11) is fitted with the front section of the aircraft cabin and has a fixed shape; the lower portion is fitted with a U-shaped push frame (7) of the deformation driving device to achieve switching of the aerodynamic shape of the front section of the aircraft cabin; the bending beam (1) is the main load-bearing structure of the driving mechanism, and the bending beam (1) is fixed to the front and rear ends of the front section of the aircraft cabin.

3. The deformation mechanism for the front middle section of a supersonic aircraft cabin according to claim 1, characterized in that: The linear guide rail (3) is connected to the bending beam (1) via countersunk set screws and is completely fitted thereto. The movement stroke of each motor module on the bending beam (1) is constrained by a limit switch (10), and the limit switch (10) includes a front limit switch and a rear limit switch.

4. The deformation mechanism for the front middle section of a supersonic aircraft cabin according to claim 1, characterized in that: The curved beam (1) serves as the main structure, and the fan-shaped bottom plate (2) is installed perpendicular to the central axis direction of the curved beam (1).

5. The deformation mechanism for the front middle section of a supersonic aircraft cabin according to claim 3, characterized in that: The driving mechanism is divided into three working states, including an initial state, a retracted state, and an extended state; When the aircraft is in the take-off to cruising stage, the driving mechanism needs to move the front skin (11) of the aircraft cabin from the initial state to the extended state; the linear motor group (4) moves synchronously along the axial direction of the bending beam (1) to the position of the rear limit switch, and pushes the skin outward to finally reach the extended state; When the aircraft is in a stage from cruising to diving towards the ground, the driving mechanism needs to move the front skin (11) of the aircraft cabin from an extended state to a retracted state; the linear motor group (4) moves synchronously along the axial direction of the bending beam (1) to the position of the front limit switch, loosening the skin and finally returning it to the retracted state.

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