Head deformation mechanism for rigid skin of supersonic aircraft

Abstract

The invention discloses a head deformation mechanism for a rigid skin of a supersonic aircraft, and belongs to the technical field of deformation mechanism design of variant aircrafts, an external structure is composed of a forehead cover, a top cover, cheek pieces and a head base body, and multi-degree-of-freedom under-actuated cooperative deformation is achieved through a lead screw linkage module and a rope system linkage module. The lead screw linkage module achieves longitudinal translation and pitching of the forehead cover through a lead screw sliding block, a worm and gear and a gear transmission mechanism, and passively drives the top cover to pitch so as to complete switching of the stretching configuration and the sunken configuration. The rope system linkage module adopts a rope driving wheel, a lifting sliding block, a cylindrical reciprocating mechanism and the like to achieve synchronous lifting of cheek pieces, and a lateral curved surface switching device of a variable triangular structure drives a curved surface shape correction sliding block to pop up or retract so as to compensate the curvature and gaps of the skin. The mechanism can realize reliable deformation and pneumatic continuity maintenance of the head shape in the subsupersonic speed conversion process, and has the advantages of stable structure, controllable boundary gap and high engineering practicability.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of variable aircraft morphing mechanism design, and in particular to a rigid skin splicing supersonic aircraft head aerodynamic shape morphing mechanism. BACKGROUND

[0002] Supersonic aircraft mainly refers to aircraft powered by turbofan, turbojet or scramjet engine, which can fly at a speed exceeding the speed of sound in the atmosphere. Supersonic aircraft adopts the design of waverider fuselage to increase the immersion area of the lower surface air of the aircraft, which is suitable for maintaining high lift coefficient in supersonic flight environment. At present, supersonic aircraft mostly adopts fixed aerodynamic shape, which is a compromise between the flight speed and lift-drag ratio of the aircraft, and it is difficult to adapt to complex and changeable flight environment. At the same time, with the development of science and technology, people's requirements for mechanical efficiency, mechanism reliability, deformation synchronization and space utilization of morphing mechanism are constantly improving. At present, most morphing mechanisms are driven by a single motor and a single mechanism, and the single mechanism is difficult to realize multi-dimensional deformation, resulting in problems such as large space occupation rate of deformation driving mechanism, low reliability of multiple motors, poor deformation synchronization, etc. SUMMARY

[0003] The present application is aimed at the problem that the fixed aerodynamic shape of the existing supersonic aircraft cannot meet the requirements of complex wide-speed flight tasks, and proposes a morphing mechanism that realizes multi-dimensional reciprocating change of the head aerodynamic shape of the supersonic aircraft by the movement of multiple rigid skin splicing combinations, which can meet the requirements of high-precision performance of the aerodynamic shape and improve the heading stability of the aircraft in different speed domains.

[0004] The present application is implemented as follows:

[0005] The head morphing mechanism for supersonic aircraft rigid skin of the present application comprises four external structures of a forehead cover, a top cover, a pair of cheek pieces on both sides and a head base, and two internal mechanisms of a lead screw linkage module and a rope linkage module; the lead screw linkage module is used to realize the coordinated movement of the forehead cover and the top cover, and the rope linkage module is used to realize the lifting of the cheek pieces and the compensation of the head rigid skin curved surface.

[0006] The screw linkage module of the deformation mechanism comprises an axle positioning plate, a guide shaft, a screw nut, a key shaft, a front and rear cover transmission installation bottom plate, a support rod, a support rod base, a worm gear transmission mechanism, a worm positioning clamp, a motor and screw installation plate, a deformation mechanism installation bottom plate, two groups of driving motors, a screw slide block, a front cover clamp, a lateral curved surface switching device, a helical gear transmission mechanism, a gear transmission mechanism, a gear-rack transmission mechanism, a rope mechanism transmission shaft system, and a bottom-mounted motor module. The front and rear cover transmission installation bottom plate is a main body bearing structure, the bottom of which is installed on the deformation mechanism installation bottom plate through four groups of support rods and support rod bases; the front and rear cover transmission installation bottom plate is loaded with an axle positioning plate and a motor and screw installation plate on both sides, and the guide shaft, the key shaft, and the screw are clamped between the axle positioning plate and the motor and screw installation plate; two groups of screw nuts are fixed on both sides of the screw slide block and are threaded on the screw and the guide shaft; the worm positioning clamp clamps the worm gear transmission mechanism and is fixed on one side of the screw slide block, and the worm gear transmission mechanism is threaded on the key shaft; the front cover clamp clamps the front cover and is fixed on the upper end of the screw slide block; the two groups of driving motors are connected with the key shaft and the screw through a shaft coupling; the rack in the gear-rack transmission mechanism is installed at the lower end of the screw slide block, and the gear is installed between the positioning plate and the deformation mechanism installation bottom plate; one side of the gear transmission mechanism is connected in series with the gear in the gear-rack transmission mechanism, and the other side is connected in series with the helical gear transmission mechanism, and the upper end of the helical gear transmission mechanism is connected with the top cover; the two groups of lateral curved surface switching devices are installed on both sides of the screw linkage module and are fixed on the deformation mechanism installation bottom plate, and the two groups of lateral curved surface switching devices are connected through the rope mechanism transmission shaft system; the rope mechanism transmission shaft system is fixed on the deformation mechanism installation bottom plate through the bottom-mounted motor module. The screw slide block and the screw nut are fixedly connected, and under the action of the driving motor driving the screw nut, the screw slide block moves longitudinally along the head of the aircraft to drive the translation of the front cover; similarly, the driving motor drives the worm gear transmission mechanism through the key shaft, thereby making the front cover produce pitching rotation; the rotation shaft of the front cover is fixed on the screw slide block through the front cover clamp, and has rotational freedom relative to the screw slide block.

[0007] Further, the top cover of the deformation mechanism is driven by the front cover, the top cover is fixedly connected with the helical gear transmission mechanism, there is an axis rotation constraint between the top cover and the head base body, and the initial position of the top cover is limited by a tension spring; when the front cover translates a certain distance towards the head of the principle aircraft with the screw slide block, the gear-rack transmission mechanism will mesh to drive the gear transmission mechanism below the front and rear cover transmission installation bottom plate to rotate, thereby driving the helical gear transmission mechanism and the top cover to perform pitching motion; by adjusting the speed and direction of the driving motor, the pitching of the front cover and the speed of entering the inside of the top cover can be controlled, so that the switching of the head rigid skin of the supersonic aircraft between the stretched state and the contracted state is realized.

[0008] Further, the rope linkage module of the deformation mechanism includes a guide pulley, a lateral mechanism mounting plate, a wire spring, a pulley seat, a pull rod limiting support, a cylindrical reciprocating mechanism, a spring limiting, a push-pull rod limiting, a reciprocating mechanism clamp, a reciprocating mechanism axial stop, a curved guide rail mounting seat, a traction rope, a rope drive wheel, a curved compensation slider, a slider support, a compensation tension spring, a support top rod, a lifting mechanism slider, a linkage mechanism motor, an integral cylindrical guide rail, a cheek piece clamping, a transmission rope, and a limiting cam; the lateral mechanism mounting plate is a main support structure, when the linkage mechanism motor is connected to the bottom through the rope linkage mechanism transmission shaft system and the bottom mounting motor module, drives the rope drive wheel fixed on the rope linkage mechanism transmission shaft system to rotate, further drives the transmission rope wound on the rope drive wheel to rotate in the same direction, through the "8-shaped" winding layout, further drives the two sets of lifting mechanism sliders fixed on the transmission rope to move up and down synchronously along the integral cylindrical guide rail; the integral cylindrical guide rail is installed on the lateral mechanism mounting plate through the curved guide rail mounting seat, the cheek piece clamping clamps the two sets of cheek pieces and is fixed on the lifting mechanism slider, so that the linkage mechanism motor controls the lifting movement of the two sets of cheek pieces.

[0009] Further, when the cheek piece lifts and moves, the linkage mechanism motor drives the traction rope to rotate around the guide pulley and the pulley seat; the traction rope is fixedly connected with a key bar, the key bar is installed in the cylindrical reciprocating mechanism, the key structure of the key bar can slide in the key groove of the cylindrical reciprocating mechanism, and the rotation timing of the cylindrical reciprocating mechanism when the traction rope pulls the key bar can be controlled by drawing different key groove paths; the key bar is constrained to move along the traction rope through the pull rod limiting support; the activity space of the cylindrical reciprocating mechanism is constrained through the reciprocating mechanism clamp and the reciprocating mechanism axial stop.

[0010] Further, the slider support, the compensation tension spring and the support top rod form a stable triangular structure, that is, a lateral curved surface switching device; the lateral curved surface switching device is limited through the spring limiting and the push-pull rod limiting; the linkage mechanism motor drives the traction rope, drives the cylindrical reciprocating mechanism to deflect through the key pull rod, and then drives the compensation tension spring to pass through the triangular singularity position, so that the configuration switching of the lateral curved surface switching device is realized; the position of the support top rod in the push-pull rod limiting is changed through the configuration switching of the lateral curved surface switching device, and then the movement of the slider support is driven; the slider support is fixedly connected with the curved compensation slider and is driven to move in the built-in guide groove of the head base body by the support top rod; the cheek piece can be lowered through the forward rotation of the linkage mechanism motor, and the curved compensation slider can be popped out when the cheek piece is about to be lowered, and the curved compensation slider can be retracted and the cheek piece can be lifted to complete the filling of the gap between the top cover and the top cover.

[0011] The head deformation mechanism for the rigid skin of the supersonic aircraft is characterized in that the driving mechanism mechanism includes two working states, including an extension state and a concave state.

[0012] To let out the movement space of the forehead cover and the top cover, when the aircraft enters the supersonic stage from the subsonic stage, the rope linkage module of the deformation mechanism deforms first; by rotating the linkage mechanism motor, the coaxial rope drive wheel is rotated; the rope drive wheel hoists the transmission rope wound thereon, drives the lifting mechanism slider fixed with the transmission rope to slide downward on the integrated cylindrical guide rail, realizes the descent of the two cheek pieces into the head base, and the cheek pieces are lowered; in the process of the cheek piece descent, the rope drive wheel simultaneously hoists the traction rope and drives the keyed rod; the keyed rod slides in the slot hole on the cylindrical reciprocating mechanism, and the movement freedom of the keyed rod is ensured to be unique through the pull rod limiting support and the reciprocating mechanism clamp; the support top rod and the slider support are connected through the compensation tension spring to form a stable triangular configuration, i.e., the lateral curved surface switching device; the slider support and the curved surface compensation slider are fixedly connected, and the displacement thereof is limited by the push-pull rod limiting and the spring limiting; the keyed rod drives the cylindrical reciprocating mechanism to swing, actuates the support top rod to realize the configuration switching of the lateral curved surface switching device, and then drives the curved surface compensation slider to pop out, so that the curved surface compensation of the head base after the cheek piece retreats into the head base is realized.

[0013] To improve the heading stability of the aircraft in the supersonic domain, when the aircraft enters the supersonic stage from the subsonic stage, the deformation mechanism needs to move the head rigid skin of the aircraft from the stretched state to the recessed state; after the rope linkage mechanism is actuated, the central drive motor is rotated to rotate the lead screw of the lead screw slider mechanism (18), so that the lead screw slider moves away from the zero position to the inside of the top cover; to avoid the inside of the top cover and the curved surface structure outside the head base, the lateral drive motor is rotated to drive the rotation of the key shaft and the worm gear transmission mechanism, so that the rotation fine adjustment of the forehead cover in the pitch direction is realized, and it is ensured that the forehead cover can enter the inside of the top cover without scratching the external curved surface and reducing the structural gap; when the forehead cover moves to a certain position in the direction of the lead screw to the top cover, the gear-rack transmission mechanism is engaged to drive the gear transmission mechanism installed at the bottom of the deformation mechanism mounting plate to rotate, and then drive the bevel gear transmission mechanism and the top cover pitch movement, and finally the top cover and the head base are spliced to achieve the recessed state of the head of the aircraft.

[0014] To improve the heading stability of the aircraft in the subsonic domain, when the aircraft enters the subsonic phase from the supersonic phase, the deformation mechanism needs to move the head rigid skin from the concave state to the stretched state; the center drive motor reverses, driving the top cover to lift the inner side of the forehead cover under the layer-by-layer transmission of the helical gear transmission mechanism, gear transmission mechanism and gear-rack transmission mechanism; at the same time, the center drive motor reverses the screw block mechanism to pull the forehead cover out from the inner side of the top cover; similarly, the movement of the forehead cover avoids the inner side of the top cover and the external curved surface structure of the head base, which is rotated by the side drive motor, driving the key shaft and worm gear transmission mechanism to rotate, thereby rotating the forehead cover in the pitch direction for fine adjustment, ensuring that the forehead cover can return to zero without scratching the external curved surface and reducing the structural gap.

[0015] To make up for the gap between the forehead cover and the top cover after movement, and to enhance the air tightness of the aircraft head, when the aircraft enters the supersonic phase from the subsonic phase, the rope linkage module of the deformation mechanism begins to deform when the forehead cover and the top cover are about to return to zero; by reversing the linkage mechanism motor, the coaxial rope drive wheel is reversed; the rope drive wheel winches the transmission rope wound thereon, driving the lifting mechanism slider fixed with the transmission rope to slide upward along the integrated cylindrical guide rail, realizing the lifting of the two cheek pieces from the head base; during the lifting of the cheek pieces, the rope drive wheel winches the traction rope and drives the key bar fixed with the traction rope; the key bar reverses in the groove hole on the cylindrical reciprocating mechanism; the support top rod and the slider bracket are connected by a compensation tension spring to form a stable triangular configuration, i.e. the lateral curved surface switching device; the key bar drives the cylindrical reciprocating mechanism to reverse, actuating the support top rod to switch the configuration of the lateral curved surface switching device, and then driving the curved surface compensation slider to retract, thereby realizing the extension of the cheek pieces from the head base and the splicing of the forehead cover, the top cover and the head base to achieve the stretched state of the aircraft head.

[0016] The beneficial effects of the present application are:

[0017] 1. The present application solves the problem of unchangeable lift-drag ratio and adjustable aerodynamic efficiency of the supersonic aircraft in the wide speed domain flight task, and realizes the single aircraft head with variable lift-drag ratio to meet different flight tasks.

[0018] 2. The present application discloses a series of rigid block skin multi-dimensional synchronous motion devices driven by three motors, which can achieve precise control and greatly improve the synchronization and stability of the mechanism motion.

[0019] 3. The present application reduces the long-term dependence of the head deformation mechanism on flexible high-performance skin and complex electrical control systems by combining various motion modes such as gear transmission, screw drive, rope drive, and link-slipper, thereby reducing equipment costs while improving the reliability of the control system. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 Positioning diagram of the deformation mechanism of the present application in an aircraft;

[0021] Figure 2 External structural diagram of the deformation mechanism of the present application;

[0022] Figure 3 Internal structural diagram of the deformation mechanism of the present application;

[0023] Figure 4 Internal structural diagram (top view) of the deformation mechanism of the present application;

[0024] Figure 5 Screw linkage module diagram of the deformation mechanism of the present application;

[0025] Figure 6 Rope linkage module partial diagram of the deformation mechanism of the present application;

[0026] Figure 7 Overall diagram of one side of the rope linkage module of the deformation mechanism of the present application;

[0027] Figure 8 Lifting mechanism structural diagram of the rope linkage module of the deformation mechanism of the present application;

[0028] Figure 9 Spatial position diagram of the rope linkage module of the deformation mechanism of the present application;

[0029] Figure 10 Extended state configuration diagram of the deformation mechanism of the present application;

[0030] Figure 11 Transition state configuration diagram of the deformation mechanism of the present application;

[0031] Figure 12 Recessed state configuration diagram of the deformation mechanism of the present application;

[0032] Wherein, 1 - forehead cover, 2 - top cover, 3 - cheek piece, 4 - head base, 5 - shaft positioning plate, 6 - guide optical axis, 7 - screw nut, 8 - key shaft, 9 - front and rear cover transmission installation bottom plate, 10 - support rod, 11 - support rod base, 12 - rope linkage module, 13 - worm gear transmission mechanism, 14 - worm positioning clamp, 15 - motor and screw installation plate, 16 - deformation mechanism installation bottom plate, 17 - drive motor, 18 - screw block, 19 - forehead cover clamp, 20 - lateral curved surface switching device, 21 - helical gear transmission mechanism, 22 - gear transmission mechanism, 23 - gear and rack transmission mechanism, 24 - rope mechanism transmission shaft system, 25 - bottom installation motor module, 26 - guide pulley, 27 - lateral mechanism installation plate, 28 - iron wire spring, 29 - pulley base, 30 - pull rod limit support, 31 - cylindrical reciprocating mechanism, 32 - spring limit, 33 - push-pull rod limit, 34 - reciprocating mechanism clamp, 35 - reciprocating mechanism axial stop, 36 - curved surface guide rail installation base, 37 - traction rope, 38 - rope drive wheel, 39 - curved surface compensation slider, 40 - slider support, 41 - compensation tension spring, 42 - support top rod, 43 - lifting mechanism slider, 44 - linkage mechanism motor, 45 - integrated cylindrical guide rail, 46 - cheek piece clamping, 47 - transmission rope, 48 - limit cam. DETAILED DESCRIPTION

[0033] To make the purpose, technical scheme and effect of the present application clearer and more explicit, the following examples are used to further describe the present application. It should be noted that the specific implementation described here is only used to explain the present application, and is not used to limit the present application.

[0034] As shown in Figure 1 , the deformation mechanism is located at the head bulge position of the supersonic aircraft; as Figures 2-8As shown, the application includes a forehead cover 1, a top cover 2, a cheek piece 3, a head base 4, an axis positioning plate 5, a guide optical axis 6, a lead screw nut 7, a key shaft 8, a front and rear cover transmission installation base plate 9, a support rod 10, a support rod base 11, a rope linkage module 12, a worm gear transmission mechanism 13, a worm positioning clamp 14, a motor and lead screw installation plate 15, a deformation mechanism installation base plate 16, a drive motor 17, a lead screw slider 18, a forehead cover clamp 19, a lateral curved surface switching device 20, a helical gear transmission mechanism 21, a gear transmission mechanism 22, a gear-rack transmission mechanism 23, a rope mechanism transmission shaft system 24, a bottom-mounted motor module 25, a guide pulley 26, a lateral mechanism installation plate 27, a wire spring 28, a pulley base 29, a pull rod limiting support 30, a cylindrical reciprocating mechanism 31, a spring limiting 32, a push-pull rod limiting 33, a reciprocating mechanism clamp 34, a reciprocating mechanism axial stop 35, a curved surface guide rail mounting seat 36, a traction rope 37, a rope drive wheel 38, a curved surface compensation slider 39, a slider bracket 40, a compensation tension spring 41, a support top rod 42, a lifting mechanism slider 43, a linkage mechanism motor 44, an integrated cylindrical guide rail 45, a cheek piece clamping 46, a transmission rope 47, and a limiting cam 48. Figure 9 As shown, the rope linkage module of the deformation mechanism is located on both sides of the deformation mechanism, which is used to drive the movement of the two groups of cheek pieces 3. Figures 10-12 As shown, the deformation mechanism will present three configurations of stretching state, motion transition state and concave state during the deformation process.

[0035] The deformation mechanism includes four external structures of a forehead cover 1, a top cover 2, a pair of cheek pieces 3 on both sides and a head base 4, and two internal mechanisms of a lead screw linkage module ( Figure 5 ) and a rope linkage module 12; the lead screw linkage module ( Figure 5 ) is used to realize the coordinated movement of the forehead cover 1 and the top cover 2, and the rope linkage module 12 is used to realize the lifting of the cheek piece 3 and the curved surface compensation of the head rigid skin.

[0036] The head deformation mechanism for the supersonic aircraft rigid skin is characterized in that the lead screw linkage module ( Figure 5) including shaft positioning plate 5, guide light axis 6, screw nut 7, key shaft 8, front and rear cover transmission installation bottom plate 9, support rod 10, support rod base 11, worm gear transmission mechanism 13, worm positioning clamp 14, motor and screw installation plate 15, deformation mechanism installation bottom plate 16, two groups of driving motor 17, screw block 18, front cover clamp 19, lateral curved surface switching device 20, bevel gear transmission mechanism 21, gear transmission mechanism 22, gear-rack transmission mechanism 23, rope mechanism transmission shaft system 24, bottom-mounted motor module 25. Among them, the screw block 18 is fixedly connected with the screw nut 7, and under the action of the driving motor 17 driving the screw nut 7, it moves along the longitudinal direction of the aircraft head to drive the translation of the front cover 1; similarly, the driving motor 17 drives the worm gear transmission mechanism 13 through the key shaft 8, and then makes the front cover 1 produce pitching rotation; wherein the rotating shaft of the front cover 1 is fixed on the screw block 18 through the front cover clamp 19, and has rotational freedom relative to the screw block 18.

[0037] The head deformation mechanism for the rigid skin of the supersonic aircraft is characterized in that the top cover 2 of the deformation mechanism is driven by the front cover 1, the top cover 2 is fixedly connected with the bevel gear transmission mechanism 21, there is an axis constraint between the top cover 2 and the head base 4, and the initial position of the top cover 2 is limited by the tension spring; when the front cover 1 translates a certain distance along with the screw block 18 towards the direction of the principle aircraft head, the gear-rack transmission mechanism 23 will mesh to drive the gear transmission mechanism 22 below the front and rear cover transmission installation bottom plate 9 to rotate, and then drive the bevel gear transmission mechanism 21 and the top cover 2 to pitch; by adjusting the speed and direction of the driving motor 17, the pitching and entering speed of the front cover 1 into the inside of the top cover 2 can be controlled, so as to realize the switching of the rigid skin of the supersonic aircraft head between the stretched state and the contracted state.

[0038] The head deformation mechanism for the rigid skin of the supersonic aircraft is characterized in that the rope linkage module 12 of the deformation mechanism comprises a guide pulley 26, a lateral mechanism mounting plate 27, a wire spring 28, a pulley seat 29, a pull rod limiting support 30, a cylindrical reciprocating mechanism 31, a spring limiting 32, a push-pull rod limiting 33, a reciprocating mechanism clamp 34, a reciprocating mechanism axial stop 35, a curved guide rail mounting seat 36, a traction rope 37, a rope drive wheel 38, a curved compensation slider 39, a slider bracket 40, a compensation tension spring 41, a support top rod 42, a lifting mechanism slider 43, a linkage mechanism motor 44, an integral cylindrical guide rail 45, a cheek clamping 46, a transmission rope 47, and a limiting cam 48. The lateral mechanism mounting plate 27 is the main support structure. When the linkage mechanism motor 44 drives the rope drive wheel 38 fixed on the rope linkage transmission shaft 24 through the bottom-mounted motor module 25, the transmission rope 47 wound on the rope drive wheel 38 is further driven to rotate in the same direction, and through the "8-shaped" winding layout, the two sets of lifting mechanism sliders 43 fixed on the transmission rope 47 are further driven to move up and down synchronously along the integral cylindrical guide rail 45. The integral cylindrical guide rail 45 is installed on the lateral mechanism mounting plate 27 through the curved guide rail mounting seat 36, the cheek clamping 46 clamps the two sets of cheeks 3, and is fixed on the lifting mechanism slider 43, so as to realize the control of the linkage mechanism motor 44 on the lifting movement of the two sets of cheeks 3.

[0039] The head deformation mechanism for the rigid skin of the supersonic aircraft is characterized in that when the cheeks 3 move up and down, the linkage mechanism motor 44 drives the traction rope 37 to rotate around the guide pulley 26 and the pulley seat 29. The traction rope 37 is fixedly connected with a key bar, the key bar is installed in the cylindrical reciprocating mechanism 31, the key structure of the key bar can slide in the key groove of the cylindrical reciprocating mechanism 31, and by drawing different key groove paths, the rotation timing of the cylindrical reciprocating mechanism 31 when the traction rope 37 pulls the key bar can be controlled. The key bar is constrained to move along the traction rope 37 through the pull rod limiting support 30. The activity space of the cylindrical reciprocating mechanism 31 is constrained through the reciprocating mechanism clamp 34 and the reciprocating mechanism axial stop 35.

[0040] The head deformation mechanism for the rigid skin of the supersonic aircraft is characterized in that the slider support 40, the compensation tension spring 41 and the support top rod 42 form a stable triangular structure, the lateral curved surface switching device 20 is limited in configuration by the spring limit 32 and the push-pull rod limit 33; the linkage mechanism motor 44 drives the traction rope 37, the cylindrical reciprocating mechanism 31 is deflected by the keyed pull rod, the compensation tension spring 41 is then actuated to pass the triangular singularity position, thereby realizing the switching of the configuration of the lateral curved surface switching device 20; by switching the configuration of the lateral curved surface switching device 20, the position of the support top rod 42 in the push-pull rod limit 33 is changed, thereby driving the movement of the slider support 40; the slider support 40 is fixedly connected with the curved surface compensation slider 39 and is driven by the support top rod 42 to move in the built-in guide groove of the head base body 4; by forward rotation of the linkage mechanism motor 44, the cheek piece 3 can be lowered and the curved surface compensation slider 39 can be ejected when the lowering of the cheek piece 3 is about to be completed, and by reverse rotation, the curved surface compensation slider 39 can be retracted and the cheek piece 3 can be lifted to complete the filling of the gap between the forehead cover 1 and the top cover 2.

[0041] The head deformation mechanism for the cabin fuselage of the supersonic aircraft is characterized in that the driving mechanism is divided into two working states, including an extended state and a recessed state.

[0042] To make room for the movement of the forehead cover 1 and the top cover 2, the rope linkage module 12 of the deformation mechanism is deformed first when the aircraft enters the supersonic stage from the subsonic stage; by rotating the linkage mechanism motor 44, the coaxial rope drive wheel 38 is rotated; the rope drive wheel 38 winds the transmission rope 47 wound thereon, drives the lifting mechanism slider 43 fixed with the transmission rope 47 to slide downward on the integrated cylindrical guide rail 45, and realizes the lowering of the two sets of cheek pieces 3 into the head base body 4; during the lowering of the cheek pieces 3, the rope drive wheel 38 simultaneously winds the traction rope 37 and drives the keyed rod member fixed with the traction rope 37; the keyed rod member slides in the slot hole on the cylindrical reciprocating mechanism 31, and the movement freedom of the keyed rod member is ensured to be unique by the pull rod limit support 30 and the reciprocating mechanism clamp 34; the support top rod 42 and the slider support 40 are connected by the compensation tension spring 41 to form a stable triangular configuration; the slider support 40 and the curved surface compensation slider 39 are fixedly connected, and their displacement is limited by the push-pull rod limit 33 and the spring limit 32; the keyed rod member drives the cylindrical reciprocating mechanism 31 to swing, actuates the support top rod 42 to realize the switching of the triangular configuration, and then drives the curved surface compensation slider 39 to be ejected, thereby realizing the curved surface compensation of the head base body 4 after the cheek pieces 3 are retracted into the head base body 4.

[0043] To improve the heading stability of the aircraft in the supersonic domain, when the aircraft enters the supersonic phase from the subsonic phase, the deformation mechanism needs to move the aircraft head rigid skin from the stretched state to the concave state; after the completion of the rope linkage mechanism 12 actuation, the center drive motor 17 rotates, driving the lead screw slider mechanism (18) to rotate, causing the lead screw slider 18 to move away from the zero position to the inside of the top cover 2; To avoid the inside of the top cover 2 and the external curved surface structure of the head base 5, the side drive motor 17 is rotated, driving the key shaft 8 and the worm gear transmission mechanism 13 to rotate, thereby driving the top cover 1 to rotate in the pitch direction for fine adjustment, ensuring that the top cover 1 can enter the inside of the top cover 2 without scratching the external curved surface and reducing the structural gap; When the top cover 1 moves to a certain position in the direction of the lead screw to the top cover 2, the gear-rack transmission mechanism 23 is engaged, driving the gear transmission mechanism 22 installed at the bottom of the deformation mechanism mounting plate 16 to rotate, and then driving the bevel gear transmission mechanism 21 and the top cover 2 to pitch, finally the top cover 2 and the head base 4 are spliced to achieve the concave state of the aircraft head.

[0044] To improve the heading stability of the aircraft in the subsonic domain, when the aircraft enters the subsonic phase from the supersonic phase, the deformation mechanism needs to move the aircraft head rigid skin from the concave state to the stretched state; the center drive motor 17 is reversed, driving the top cover 2 to lift the inside of the top cover 2 through the bevel gear transmission mechanism 21, the gear transmission mechanism 22 and the gear-rack transmission mechanism 23; At the same time, the center drive motor 17 drives the lead screw slider mechanism 18 in reverse, pulling the top cover 1 out of the inside of the top cover 2; Similarly, the movement of the top cover 1 is to avoid the inside of the top cover 2 and the external curved surface structure of the head base 5, and the side drive motor 17 is rotated, driving the key shaft 8 and the worm gear transmission mechanism 13 to rotate, thereby driving the top cover 1 to rotate in the pitch direction for fine adjustment, ensuring that the top cover 1 can return to the zero position without scratching the external curved surface and reducing the structural gap.

[0045] To make up the gap between the forehead cover 1 and the top cover 2 after the movement, enhance the airtightness of the aircraft head, when the aircraft enters the supersonic stage from the subsonic stage, the rope linkage module 12 of the deformation mechanism begins to deform when the forehead cover 1 and the top cover 2 are about to return to zero; by reversing the linkage mechanism motor 44, the coaxial rope drive wheel 38 is reversed; the rope drive wheel 38 hoists the transmission rope 47 wound thereon, drives the lifting mechanism slider 43 fixed with the transmission rope 47 to slide upward along the integrated cylindrical guide rail 45, and realizes the lifting of the two groups of cheek pieces 3 from the head base 4; in the process of lifting the cheek pieces 3, the rope drive wheel 38 simultaneously hoists the traction rope 37 and drives the keyed rod member fixed with the traction rope 37; the keyed rod member reversely slides in the slot hole on the cylindrical reciprocating mechanism 31; the support top rod 42 and the slider bracket 40 are connected through the compensation tension spring 41 to form a stable triangular configuration, i.e. the lateral curved surface switching device 20; the keyed rod member drives the cylindrical reciprocating mechanism 31 to reverse swing, drives the support top rod 42 to realize the switching of the configuration of the lateral curved surface switching device 20, and then drives the curved surface compensation slider 39 to retract, so as to realize the extension of the cheek pieces 3 from the head base 4 and splice with the forehead cover 1, the top cover 2 and the head base 4 to achieve the extension state of the aircraft head.

[0046] 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 also be made, which should be considered as the protection of the present application.

Claims

1. A head deformation mechanism for a rigid skin of a supersonic aircraft, characterized in that, The aforementioned mechanism includes: an external structure and an internal structure; The external structure includes: a forehead cover (1), a top cover (2), a pair of cheek pieces (3) on both sides, and a head base (4); the internal mechanism includes: a screw linkage module and a rope linkage module (12); the screw linkage module is used to realize the coordinated movement of the forehead cover (1) and the top cover (2), and the rope linkage module (12) is used to realize the lifting and lowering of the cheek pieces (3) and the compensation of the rigid skin surface of the head.

2. The head deformation mechanism for a rigid skin of a supersonic aircraft according to claim 1, characterized in that, The screw linkage module of the deformation mechanism includes a shaft positioning plate (5), a guide shaft (6), a screw nut (7), a key shaft (8), a front and rear cover transmission mounting base plate (9), a support rod (10), a support rod base (11), a worm gear transmission mechanism (13), a worm positioning fixture (14), a motor and screw mounting plate (15), a deformation mechanism mounting base plate (16), two sets of drive motors (17), a screw slider (18), a front cover fixture (19), a lateral curved surface switching device (20), a helical gear transmission mechanism (21), a gear speed change mechanism (22), a gear-rack transmission mechanism (23), a rope mechanism transmission shaft system (24), and a bottom-mounted motor module (25). The front and rear cover transmission mounting base plate (9) is the main load-bearing structure. Its bottom is mounted on the deformation mechanism mounting base plate (16) through four sets of support rods (10) and support rod bases (11). The front and rear cover transmission mounting base plate (9) is loaded with shaft positioning plates (5) and motor and lead screw mounting plates (15) on both sides, and the guide shaft (6), key shaft (8) and lead screw are respectively clamped between the shaft positioning plate (5) and the motor and lead screw mounting plate (15). Two sets of lead screw nuts (7) are fixed on both sides of the lead screw slider (18) and pass through the lead screw and guide shaft (6). The worm gear positioning fixture (14) clamps the worm gear transmission mechanism (13) and fixes it on one side of the lead screw slider (18), and passes the worm gear transmission mechanism (13) through the key shaft (8). The front cover fixture (19) clamps the front cover (1) and fixes it on the upper end of the lead screw slider (18). Two sets of drive The motor (17) is connected to the key shaft (8) and the lead screw through a coupling; the rack in the gear-rack transmission mechanism (23) is installed at the lower end of the lead screw slider (18), and the gear is installed between the positioning plate (5) and the deformation mechanism mounting base plate (16); the gear speed change mechanism (22) is connected in series with the gear in the gear-rack transmission mechanism (23) on one side and in series with the helical gear transmission mechanism (21) on the other side, and the upper end of the helical gear transmission mechanism (21) is connected to the top cover (2); two sets of lateral curved surface switching devices (20) are installed on both sides of the lead screw linkage module and fixed on the deformation mechanism mounting base plate (16), and the two sets of lateral curved surface switching devices (20) are connected through the rope mechanism transmission shaft system (24); the rope mechanism transmission shaft system (24) is fixed on the deformation mechanism mounting base plate (16) through the bottom-mounted motor module (25).

3. The head deformation mechanism for a rigid skin of a supersonic aircraft according to claim 2, characterized in that, The lead screw slider (18) is fixedly connected to the lead screw nut (7). Under the action of the drive motor (17) driving the lead screw nut (7), it moves longitudinally along the head of the aircraft to drive the translation of the front cover (1). Similarly, the drive motor (17) drives the worm gear transmission mechanism (13) through the key shaft (8), thereby causing the front cover (1) to pitch and rotate; wherein the rotating shaft of the front cover (1) is fixed on the lead screw slider (18) through the front cover clamp (19), and has rotational freedom relative to the lead screw slider (18).

4. The head deformation mechanism for a rigid skin of a supersonic aircraft according to claim 1, characterized in that, The top cover (2) of the deformation mechanism is driven by the front cover (1). The top cover (2) is fixedly connected to the helical gear transmission mechanism (21) and there is a fixed axis rotation constraint between it and the head base (4). The initial position of the top cover (2) is limited by the tension spring. When the front cover (1) moves a certain distance towards the head of the prototype aircraft with the lead screw slider (18), the gear-rack transmission mechanism (23) will mesh and drive the gear speed change mechanism (22) under the front and rear cover transmission mounting base plate (9) to rotate, thereby driving the helical gear transmission mechanism (21) and the top cover (2) to perform pitch motion. By adjusting the speed and direction of the drive motor (17), the pitch of the front cover (1) and the speed of entering the inside of the top cover (2) can be controlled, thereby realizing the switching of the rigid skin of the supersonic aircraft head in the extended state and the retracted state.

5. The head deformation mechanism for a rigid skin of a supersonic aircraft according to claim 1, characterized in that, The rope linkage module (12) of the deformation mechanism includes a guide pulley (26), a lateral mechanism mounting plate (27), a wire spring (28), a pulley seat (29), a pull rod limiting support (30), a cylindrical reciprocating mechanism (31), a spring limit (32), a push-pull rod limit (33), a reciprocating mechanism clamp (34), a reciprocating mechanism axial stop (35), a curved guide rail mounting seat (36), a traction rope (37), a rope drive wheel (38), a curved surface shaping slider (39), a slider bracket (40), a compensation tension spring (41), a support top rod (42), a lifting mechanism slider (43), a linkage mechanism motor (44), an integrated cylindrical guide rail (45), a cheek clamp (46), a transmission rope (47), and a limiting cam (48). The side mechanism mounting plate (27) is the main support structure. When the linkage mechanism motor (44) drives the rope drive wheel (38) fixed on the rope drive wheel (24) to rotate through the rope mechanism transmission shaft system (24) and the bottom mounted motor module (25), it further drives the transmission rope (47) wound on the rope drive wheel (38) to rotate in the same direction. Through the figure-eight winding layout, it further drives the two sets of lifting mechanism sliders (43) fixed on the transmission rope (47) to move up and down synchronously along the integrated cylindrical guide rail (45). The integrated cylindrical guide rail (45) is mounted on the side mechanism mounting plate (27) through the curved guide rail mounting seat (36). The cheek clip (46) holds the two sets of cheeks (3) and is fixed on the lifting mechanism slider (43), thereby realizing the control of the linkage mechanism motor (44) on the lifting motion of the two sets of cheeks (3).

6. The head deformation mechanism for a rigid skin of a supersonic aircraft according to claim 5, characterized in that, When the cheek piece (3) moves up and down, the linkage mechanism motor (44) drives the traction rope (37) to rotate around the guide pulley (26) and pulley seat (29); the traction rope (37) is fixedly connected to a keyed rod, which is installed in the cylindrical reciprocating mechanism (31). Its key structure can slide in the keyway of the cylindrical reciprocating mechanism (31). By delineating different keyway paths, the rotation timing of the cylindrical reciprocating mechanism (31) can be controlled when the traction rope (37) pulls the keyed rod; the keyed rod is constrained along the movement range of the traction rope (37) by the pull rod limit support (30); the movement space of the cylindrical reciprocating mechanism (31) is constrained by the reciprocating mechanism clamp (34) and the reciprocating mechanism axial stop (35).

7. A head deformation mechanism for a rigid skin of a supersonic aircraft according to claim 5, characterized in that, The slider bracket (40), the compensating tension spring (41), and the supporting rod (42) form a stable triangular structure. The configuration of the lateral surface switching device (20) is limited by the spring limit (32) and the push-pull rod limit (33). The linkage mechanism motor (44) drives the traction rope (37), which drives the cylindrical reciprocating mechanism (31) to deflect through the keyed pull rod, thereby causing the compensating tension spring (41) to pass the singular point of the triangle, thus realizing the switching of the configuration of the lateral surface switching device (20). By switching the configuration of the lateral surface switching device (20), the supporting rod ( 42) The position of the push-pull rod limit (33) drives the movement of the slider bracket (40); the slider bracket (40) is fixedly connected to the curved surface shaping slider (39) and driven by the support rod (42) to move in the built-in guide groove of the head base (4); the forward rotation of the linkage mechanism motor (44) can drive the cheek piece (3) to descend and pop out the curved surface shaping slider (39) when the cheek piece (3) is about to descend; the reverse rotation can retract the curved surface shaping slider (39) and pull the cheek piece (3) to rise to complete the filling of the gap between the forehead cover (1) and the top cover (2).

8. A deformation mechanism for the nose section of a supersonic vehicle cabin according to any one of claims 1 to 7, characterized in that, The drive mechanism has two working states: an extended state and a recessed state. To allow space for movement between the forehead cover (1) and the top cover (2), when the aircraft transitions from the subsonic to the supersonic phase, the rope linkage module (12) of the deformation mechanism deforms first; by rotating the linkage mechanism motor (44), the coaxial rope drive wheel (38) is driven to rotate; the rope drive wheel (38) winds up the transmission rope (47) wrapped around it, causing the lifting mechanism slider (43) fixed to the transmission rope (47) to slide downward on the integrated cylindrical guide rail (45), so that the two cheek pieces (3) descend into the head base (4); during the descent of the cheek pieces (3), the rope drive wheel (38) simultaneously winds up the traction rope (37) and drives the keyed rod fixed to the traction rope (37); the keyed rod The component slides through the slot in the cylindrical reciprocating mechanism (31), and the keyed rod is ensured to have a unique degree of freedom of movement by means of the pull rod limiting support (30) and the reciprocating mechanism clamp (34); the support rod (42) and the slider bracket (40) are connected by the compensating tension spring (41) to form a stable triangular configuration; the slider bracket (40) is fixedly connected to the curved surface compensation slider (39), and its displacement is limited by the push-pull rod limiting (33) and the spring limiting (32); the keyed rod drives the cylindrical reciprocating mechanism (31) to swing, and moves the support rod (42) to realize the triangular configuration switching, thereby driving the curved surface compensation slider (39) to pop out, so as to realize the curved surface compensation of the head base (4) after the cheek piece (3) retracts into the head base (4).

9. A deformable mechanism for the nose section of a supersonic vehicle cabin according to claim 8, characterized in that, To improve the directional stability of the aircraft in the supersonic range, when the aircraft enters the supersonic range from the subsonic stage, the deformation mechanism needs to move the rigid skin of the aircraft's head from an extended state to a concave state. After the rope linkage mechanism (12) is activated, the central drive motor (17) rotates, driving the lead screw of the lead screw slider mechanism (18) to rotate, causing the lead screw slider (18) to move away from the zero position and towards the inside of the top cover (2). To avoid the inner side of the top cover (2) from the outer curved surface structure of the head base (5), the side drive motor (17) rotates, driving the key shaft (8) and the worm gear transmission. The rotation of mechanism (13) causes the front cover (1) to rotate and fine-tune in the pitch direction, ensuring that the front cover (1) can enter the inside of the top cover (2) without scraping the external curved surface and reducing the structural gap; when the front cover (1) moves to a certain position along the screw towards the top cover (2), the gear-rack transmission mechanism (23) meshes, causing the gear transmission mechanism (22) installed at the bottom of the deformation mechanism mounting base plate (16) to rotate, thereby causing the helical gear transmission mechanism (21) and the top cover (2) to pitch, and finally the top cover (2) and the head base (4) are spliced ​​together to achieve the concave state of the aircraft head; To improve the directional stability of the aircraft in the subsonic range, when the aircraft enters the subsonic range from the supersonic stage, the deformation mechanism needs to move the rigid skin of the aircraft head from a concave state to an extended state; the central drive motor (17) reverses and drives the top cover (2) to lift up the front cover (1) exposed by the layer transmission of the helical gear transmission mechanism (21), the gear speed change mechanism (22) and the gear-rack transmission mechanism (23); at the same time, the central drive motor (17) drives the lead screw slider mechanism (18) in the opposite direction to pull the front cover (1) out from the inside of the top cover (2); similarly, the movement of the front cover (1) avoids the inner side of the top cover (2) and the outer curved surface structure of the head base (5). Through the rotation of the side drive motor (17), the key shaft (8) and the worm gear transmission mechanism (13) are driven to rotate, thereby driving the front cover (1) to rotate and fine adjust in the pitch direction, so as to ensure that the front cover (1) can return to the zero position without scraping the outer curved surface and reducing the structural gap.

10. A deformable mechanism for the nose section of a supersonic vehicle cabin according to claim 8, characterized in that, To compensate for the gap between the forehead cover (1) and the top cover (2) after movement and enhance the airtightness of the aircraft head, when the aircraft enters the supersonic stage from the subsonic stage, just as the forehead cover (1) and the top cover (2) are about to return to the zero position, the rope linkage module (12) of the deformation mechanism begins to deform; through the reverse linkage mechanism motor (44), the coaxial rope drive wheel (38) is driven to reverse; the rope drive wheel (38) winds up the transmission rope (47) wrapped around it, and drives the lifting mechanism slider (43) fixed to the transmission rope (47) to slide upward along the integrated cylindrical guide rail (45), so that the two cheek pieces (3) rise from the head base (4); during the process of the cheek pieces (3) rising, the rope drive wheel (38) simultaneously winds up the traction rope (37) and drives the keyed rod fixed to the traction rope (37); the keyed rod slides in the opposite direction in the slot on the cylindrical reciprocating mechanism (31); The support rod (42) and the slider bracket (40) are connected by a compensating tension spring (41) to form a stable triangular configuration, namely the lateral curved surface switching device (20). The keyed rod drives the cylindrical reciprocating mechanism (31) to swing back, and the support rod (42) is moved to realize the switching of the configuration of the lateral curved surface switching device (20), thereby driving the curved surface supplementing slider (39) to retract, so that the cheek piece (3) extends out of the head base (4) and is spliced ​​with the forehead cover (1), the top cover (2) and the head base (4) to achieve the extended state of the aircraft head.

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