Folding empennage of patrol flight unmanned aerial vehicle

Abstract

The invention relates to a folding empennage of a patrol flight unmanned aerial vehicle, and belongs to novel unmanned aerial vehicle structures and mechanisms. The device is composed of a mounting base, a folding and unfolding mechanism, a locking device and an airfoil structure. The mounting seat is arranged on the side surface of the rear part of the unmanned aerial vehicle body and consists of a mounting shaft, a flat spiral spring, a ball bearing, a bearing bush, an end cover, a bottom plate and an empennage nut; the airfoil structure comprises a vertical stabilizer and a rudder; the locking device comprises a locking device 1 and a locking device 2; the locking device 1 comprises a spring clip-clamping block external locking device and a limiting surface limiting-damping device; the locking device 2 comprises a flat spring sliding block-rotating shaft convex angle built-in locking device and a fuselage stop block-vertical fin rear edge limiting-damping device.

Description

Technical Field

[0001] The invention relates to a folding tail of a patrol unmanned aerial vehicle (UAV), belonging to a new type of UAV structure and mechanism. Background Art

[0002] The tail wings of tube-launched patrol drones typically feature a folding design. With the advancement of patrol drone technology and products, manufacturers, research institutions, and individuals have developed numerous folding tail wing design solutions. To address the unique requirements of the patrol drone platform being developed, a folding tail wing design has been developed and patented. Summary of the Invention

[0003] According to one aspect of the present application, there is provided a folding tail for a patrol drone, which comprises a mounting base, a folding and unfolding mechanism, a locking device, and a wing surface structure;

[0004] The patrol drone adopts a single tail design, with the tail arranged on the side of the rear fuselage barrel section, which is an asymmetric layout;

[0005] In the unfolded state, the tail is along the vertical axis of the aircraft; in the folded state, the tail is stored on the side of the rear fuselage barrel section along the longitudinal axis of the aircraft;

[0006] The mounting seat is arranged on the rear side of the cruise drone fuselage and is composed of a mounting shaft, a plane scroll spring, a ball bearing, a bearing bushing, an end cover, a base plate, and a tail wing nut;

[0007] The wing structure includes a vertical stabilizer and a rudder;

[0008] The locking device includes a locking device a and a locking device b;

[0009] The locking device a includes a spring clip-block external locking device and a limit surface limit-damping device;

[0010] The locking device b includes a leaf spring pin lock-mounting shaft cam built-in locking device and a fuselage stopper-tail trailing edge limit-damping device.

[0011] The inner side of the outer end of the mounting seat is provided with a thread, and the end cover is connected to the mounting seat through the thread to close the mounting seat;

[0012] The mounting shaft comprises a fuselage connection end with a circular cross section, a tail mounting end with a square cross section, a circular shaft shoulder in the middle of the mounting shaft, and an outer shaft shoulder located on one side of the tail mounting end close to the circular shaft shoulder;

[0013] The radius of the annular shoulder is greater than the radius of the outer shoulder;

[0014] The center of the bottom plate is provided with a circular hole that matches the size and shape of the fuselage connection end of the mounting shaft;

[0015] The depth of the round hole is 2 to 4 mm;

[0016] A through hole is made in the center of the end cover, and the size and shape of the fin mounting end of the mounting shaft are matched;

[0017] The inner plane of the end cover is in contact with the shoulder of the mounting shaft close to the fin mounting end, realizing the installation and limitation of the mounting shaft, and ensuring the free rotation of the mounting shaft;

[0018] The fin mounting end of the mounting shaft extends out from the through hole in the center of the end cover for mounting the fin;

[0019] A circular ring bushing is provided between the fuselage connection end of the mounting shaft and the bottom plate, and a ball bearing is placed in the circular ring bushing;

[0020] The flat spiral spring is arranged between the circular ring bushing and the bottom plate;

[0021] A notch is made at the symmetric center plane position of the fuselage connection end of the mounting shaft, and the width and height dimensions of the notch are matched with the cross-sectional dimensions of the spring steel strip of the flat spiral spring. The notch is used to mount the 90° inner bent edge at the center of the flat spiral spring, so that the flat spiral spring is connected to the mounting shaft as a whole;

[0022] The mounting seat is also provided with a notch, and the width and height dimensions of the notch are matched with the cross-sectional dimensions of the spring steel strip of the flat spiral spring. The notch is used to mount the 90° outer bent edge at the outer end of the flat spiral spring, so that the flat spiral spring is connected to the mounting seat as a whole;

[0023] The outer end of the mounting shaft is provided with a central threaded hole for mounting a fin nut, and the fin nut connects the fin structure and the mounting shaft into a whole;

[0024] A gasket can be inserted between the notch and the bent edge;

[0025] The outer shoulder is used to limit the lateral position of the fin.

[0026] The folding and unfolding mechanism uses a flat spiral spring as a power source. The flat spiral spring is installed inside the mounting seat and directly connects the mounting seat and the wing surface structure;

[0027] The outer end of the flat spiral spring is fixedly connected to the mounting seat, and the inner end is inserted into the notch in the symmetric center plane of the mounting shaft;

[0028] When in the folded state, the flat spiral spring applies a torque to the wing surface structure. When unfolding, the wing surface structure unfolds under the torque action of the flat spiral spring;

[0029] The flat spiral spring is the power source for the deployment of the tail fin, arranged at the innermost part of the mounting base and sleeved outside the mounting shaft; a notch is made at the symmetrical center plane position of the end section of the mounting shaft, and the width and height dimensions of the notch match the cross-sectional dimensions of the flat spiral spring. The notch is used to install the 90° inner bent edge at the center of the flat spiral spring, so that the flat spiral spring is connected to the mounting shaft as a whole;

[0030] The outer end of the flat spiral spring is connected to the fuselage mounting base; the 90° outer bent edge of the flat spiral spring cooperates with the notch of the fuselage mounting base. In the installed state, the 90° outer bent edge is inserted into the installation notch of the tube body of the fuselage mounting base (in order to ensure the connection effect, a gasket can be inserted between the notch and the bent edge).

[0031] The vertical stabilizer consists of a shell, a root metal joint, a rigid foam core, a servo mounting base, a metal wing tip, and a shroud;

[0032] The shell is made of fiberglass or carbon fiber material;

[0033] The root metal joint has a central hole for connecting to the tail fin mounting end of the mounting shaft;

[0034] The servo mounting base is placed near the root metal joint, and forms an internal space with the two side shells for installing the servo. A pressing block connected by screws is provided at the opening position of the internal space to completely install and fix the servo;

[0035] The metal wing tip is connected to the shell through a connecting block;

[0036] The connecting block and the shell are connected through fasteners;

[0037] The connecting block and the shell are obtained by integral machining;

[0038] The shroud is a detachable component, sleeved outside the lower structure of the vertical stabilizer (below the rudder), and constitutes the aerodynamic outer shape surface of the trailing edge of the stabilizer;

[0039] The inside of the vertical stabilizer is filled with a rigid foam core.

[0040] When installing the data link antenna inside the tail fin, a wave-transparent fiberglass material is used as the shell. If no antenna is installed inside, a carbon fiber shell with better performance can be used.

[0041] The rudder consists of a servo, a shell, and a rigid foam core;

[0042] The shell is made of carbon fiber material;

[0043] The inside of the rudder is filled with a rigid foam core;

[0044] The vertical stabilizer and the rudder are connected by a flexible hinge;

[0045] The servo is installed on the servo mounting base;

[0046] The servo is provided with an output shaft, and the output shaft is coaxial with the flexible hinge;

[0047] The output shaft is connected with a rocker arm, the rocker arm is connected with a jacket, and the jacket is located outside the lower end head of the rudder, so as to realize the driving of the servo on the rudder.

[0048] The flexible hinge is made of Kevlar fiber material with a thickness of 0.2 - 0.3 mm;

[0049] The folding and unfolding stroke of the tail wing is about 90°.

[0050] In the spring clip - block external locking device and the limit surface limit - damping device, the root metal joint is provided with a block extending outside the wing surface structure, and the side of the mounting base is provided with a U - shaped spring clip which can clamp the block to realize the locking, limiting and damping of the wing surface structure;

[0051] The outer end working position of the mounting base has a protruding part with a right - angled groove. One of the right - angled grooves of the protruding part is the mounting surface for installing the U - shaped spring clip, and the other surface is the limit surface for limiting and damping;

[0052] The U - shaped spring clip is a formed part by bending a spring steel plate. The convex - angle structures are formed by the inward bending of the two vertical sides on both sides, and the two convex angles together form a clamping mouth;

[0053] When the wing surface structure rotates from the folded position to the unfolded position, the block rotates around the wing surface structure mounting shaft along with the root metal joint. At the end of the tail wing unfolding stroke, the block head contacts the clamping mouth of the U - shaped spring clip and applies an outward pressure to make the clamping mouth of the U - shaped spring clip deform outward. The block head passes through the clamping mouth, and the clamping mouth of the U - shaped spring clip resets and matches with the block neck to lock the block head in the working position; the block also has the function of a stop block, and the vertical surface at the front end of the block and the limit surface of the right - angled groove of the mounting base cooperate to realize the limit - damping function.

[0054] The circular ring shaft shoulder of the mounting shaft is provided with an acute - angled convex angle which can rotate along with the mounting shaft;

[0055] In the unfolded state of the tail wing, the convex angle is in the vertically downward position. In the folded state of the tail wing, the convex angle rotates 90° clockwise to the horizontal position;

[0056] When the locking device 2 is adopted, the lower part of the mounting base is provided with a boss structure for installing a stud pin lock, a leaf spring and an end cover;

[0057] The upper side and the left side of the mounting base are each provided with a boss structure;

[0058] Threaded holes are provided on all three boss structures. The 3 threaded holes are evenly distributed on a circle centered on the mounting shaft for the connection of the end cover.

[0059] A pin guide groove extending vertically downward is provided on the boss structure at the lower part of the mounting seat. The cross-sectional shape of the pin guide groove matches the cross-sectional shape of the pin latch. The pin guide groove and the end cover jointly restrict the pin latch to slide linearly only along the axis direction of the pin guide groove.

[0060] The front section of the pin latch is a slender column pin with a rectangular cross-section. The front end of the column pin is obliquely cut to form a convex angle. The shape and size of the convex angle at the front end of the column pin match the convex angle of the mounting shaft. The rear section of the pin latch is a short and thick cylindrical base. A notch is provided in the cylindrical base, and a leaf spring is inserted into the notch. The leaf spring applies a pressing force to the pin latch to keep it in the locked position. The leaf spring is installed on the boss structure at the lower part of the mounting seat.

[0061] Three mounting holes are evenly distributed on the end cover and match the 3 threaded holes of the mounting seat. 3 small-diameter bolts / screws are used to connect the end cover to the mounting seat. There is also a limit notch ring structure on the inner side of the end cover. The two cut surfaces of the ring match the two surfaces of the convex angle of the mounting shaft respectively, corresponding to the folded position and the deployed position of the tail fin.

[0062] At the end section of the rotation stroke of the tail fin from the folded position to the deployed position, after the inclined surface of the convex angle of the mounting shaft contacts the inclined surface of the front convex angle of the pin latch, a pressure perpendicular to the inclined surface is applied to it. The component of the pressure in the radial direction (vertical direction) overcomes the pressure of the leaf spring, causing the pin latch to slide linearly outward in the radial direction until the tip of the convex angle of the mounting shaft crosses the tip of the convex angle of the pin, that is, the convex angle of the mounting shaft rotates to the front of the convex angle of the pin, and the rear vertical surface of the convex angle of the mounting shaft is coplanar with the vertical surface of the convex angle of the pin. In this way, the pin latch slides upward along the guide groove under the action of the leaf spring pressure until the tip of the convex angle of the pin abuts against the outer surface of the ring shoulder of the mounting shaft, locking the convex angle of the mounting shaft - the mounting shaft - the tail fin.

[0063] When unlocking, grasp the rear cylindrical base of the pin latch and pull it outwards, so that the front convex angle of the pin latch releases the constraint on the convex angle of the mounting shaft, and thus the mounting shaft - the tail fin can rotate from the deployed position to the folded position.

[0064] A strip-shaped block is arranged on the fuselage structure (machined integrally or mechanically connected). The front end face of the block matches the trailing edge of the tail fin in the deployed state. In this way, when the tail fin rotates to the deployed position, the trailing edge of the tail fin contacts the block, and the block confines the tail fin in the deployed position. The impact energy is absorbed by the block and the tail fin structure, playing a damping role. The trailing edge structure at the root of the tail fin is strengthened to withstand greater loads.

[0065] Optionally, it includes the following structures:

[0066] A folding tail fin for a loitering unmanned aerial vehicle, mainly characterized by adopting a fuselage mounting base - mounting shaft vertical tail mounting structure, a planar spiral spring powered folding and unfolding mechanism, two designs of a spring clip - block external locking device and a leaf spring slider - rotating shaft convex angle internal locking device, a composite material wing surface structure and a flexible hinge.

[0067] The loitering unmanned aerial vehicle adopts a single vertical tail design. The vertical tail includes two parts: a vertical stabilizer and a rudder. The vertical tail is arranged on the side of the rear fuselage barrel section, which is an asymmetric layout. In the deployed state, the vertical tail is along the vertical axis of the aircraft; in the folded state, the vertical tail is stored along the longitudinal axis of the aircraft on the side of the rear fuselage barrel section. The folding and unfolding stroke of the vertical tail is about 90°.

[0068] The vertical tail mainly adopts a composite material structure, including two parts: a vertical stabilizer and a rudder, which are connected by a flexible hinge.

[0069] A vertical tail mounting seat is designed on the side of the rear fuselage barrel section. The mounting structure (mounting shaft) - folding and unfolding mechanism of the vertical tail is arranged in the mounting seat. The vertical tail mounting shaft can rotate around the axis. About half of the length of the mounting shaft is exposed outside the mounting seat for installing and connecting the vertical tail. The mounting shaft bears and transmits the vertical tail load and drives the vertical tail to realize the folding and unfolding movement.

[0070] The planar spiral spring is used as the power source for folding and unfolding. The spring is installed inside the fuselage mounting seat, with the outer end fixedly connected to the mounting seat (tube shaft wall), and the inner end fixedly connected to the mounting shaft. The spring directly connects the vertical tail and the fuselage mounting seat. In the folded state, the spring directly applies torque to the vertical tail. When unfolding, the locking mechanism is unlocked, and the vertical tail unfolds under the action of the spring torque.

[0071] There are two designs for the locking device: a spring clip - block external locking and a leaf spring slider - rotating shaft convex angle internal locking. For the spring clip - block external locking device, the block also cooperates with the fuselage column base to realize the limiting and damping functions. For the leaf spring slider - rotating shaft convex angle internal locking device, the fuselage stop block and the strengthened trailing edge of the vertical tail cooperate to realize the limiting and damping functions.

[0072] Specifically, it includes the following structures:

[0073] Fuselage vertical tail mounting seat

[0074] There is an integral vertical tail cylindrical mounting seat (by integral machining or welding, etc.) on the side of the rear fuselage barrel section. The vertical tail cylindrical mounting seat is composed of a cylinder and a bottom plate. Part of the mounting seat structure is located inside the fuselage barrel section, and part of the structure is outside the fuselage barrel section. The inside of the mounting seat is used to arrange the components and structural parts of the vertical tail folding and unfolding mechanism. The center line of the mounting seat is the rotation axis of the vertical tail.

[0075] Vertical tail structure and rudder actuation system

[0076] The vertical tail includes two parts: a vertical stabilizer and a rudder.

[0077] The vertical stabilizer consists of a shell (glass fiber / carbon fiber panel), a core, a metal wing tip, a lower shroud, etc. When installing a data link antenna inside the vertical stabilizer, a wave-transparent glass fiber panel is used. If no antenna is installed inside, a carbon fiber panel with better performance can be used. The core includes a root metal joint, a servo mount, a rigid foam core, etc. The root metal joint has a central hole for connecting to the installation axis of the vertical stabilizer, and the hole-shaft fit is used to transfer the load of the vertical stabilizer. The servo C-shaped mount is also a metal component. The internal space enclosed by the C-shaped mount and the two side panels is used to install the servo, and a press block connected by screws at the position of the closed space port completely installs and fixes the servo. The vertical stabilizer wing tip is mainly composed of an end plate and a connecting block. The connecting block is sleeved inside the composite stabilizer shell, and the end plate and the connecting block are connected by fasteners (or machined integrally). The lower shroud is a detachable component, sleeved outside the lower structure of the stabilizer (below the rudder), forming the aerodynamic outer contour surface of the stabilizer trailing edge.

[0078] The rudder consists of a shell (carbon fiber panel) and a rigid foam core. A flexible hinge sheet is used between the stabilizer and the rudder. The flexible hinge sheet is a Kevlar fiber cloth with a certain thickness (such as about 0.20mm, 0.30mm, etc.). The front and rear parts of the flexible hinge sheet are respectively connected to the inside of the trailing edge of the stabilizer and the inside of the leading edge of the rudder.

[0079] A small-sized ultra-thin servo is installed inside the C-shaped mount. The output shaft of the servo is coaxial with the rudder hinge. The (variable cross-section) U-shaped clamp on the upper part of the rocker arm is sleeved outside the lower end of the rudder, and the front end of the rocker arm is connected to the output shaft of the servo. In this way, the servo directly drives the rudder to rotate.

[0080] Vertical stabilizer installation structure - folding and unfolding mechanism

[0081] The vertical stabilizer installation structure - folding and unfolding mechanism includes: an installation shaft, a flat spiral spring, a ball bearing, a bearing bushing, an end cover, a vertical stabilizer nut, etc. All parts except the vertical stabilizer nut are installed on the fuselage vertical stabilizer mount, and the end cover encloses / limits other parts inside the mount. A circular hole with a certain depth is made in the center of the bottom plate of the fuselage vertical stabilizer mount, and a through hole is made in the center of the circular end cover. The sizes of the two circular holes match the size of the installation shaft. The inner plane of the circular end cover fits with the front side circular ring surface of the shaft shoulder of the installation shaft, thus realizing the installation and limitation of the installation shaft and ensuring the free rotation of the installation shaft. About half of the installation shaft extends out from the central hole of the end cover for installing the vertical stabilizer. A small-sized ball bearing and a circular ring bushing (rectangular cross-section) assembly are installed between the mount tube body and the installation shaft as the main support of the installation shaft, making the rotational damping moment of the rotating shaft as small as possible.

[0082] The planar scroll spring is the power source for the vertical tail unfolding, arranged at the innermost part of the mounting seat and sleeved outside the mounting shaft. A notch is made at the position of the axisymmetric center plane of the mounting shaft, and the width and height dimensions of the notch match the cross-sectional dimensions of the spring steel strip of the planar scroll spring. The notch is used to install the 90° inner bent edge at the center of the planar scroll spring, so that the spring is connected to the rotating shaft as a whole. The outer end of the planar scroll spring is connected to the fuselage mounting seat. The 90° outer bent edge of the scroll spring cooperates with the notch of the fuselage mounting seat. In the installed state, the 90° outer bent edge is inserted into the mounting notch of the tube body of the fuselage mounting seat (in order to ensure the connection effect, a gasket can be inserted between the notch and the bent edge).

[0083] Internal threads are made on the inner side of the outer end of the tube body of the fuselage mounting seat for connecting the end cover.

[0084] There is an outer shaft shoulder at the position of the exposed part of the mounting shaft close to the mounting seat, which is used to limit the lateral position of the vertical tail. There are two design schemes for the exposed rotating shaft, namely the square cross-section and the circular cross-section. The rotating shaft with a square cross-section cooperates with the square hole at the root of the vertical tail, and the rotating shaft with a circular cross-section needs to be equipped with a keyway and a key pin. Spline connection can also be used, but the processing is relatively complex. The outer end of the rotating shaft is provided with a central threaded hole for installing the vertical tail nut, and the vertical tail nut connects the vertical tail and the rotating shaft into a whole.

[0085] Spring clip - external locking device with a block and block - limiting surface limiting - damping device

[0086] The lower metal joint (load-bearing core) of the vertical tail is provided with a block extending outside the wing surface. The block cooperates with the U-shaped spring clip installed on the fuselage column base (along the transverse axis of the aircraft) to form a spring clip - external locking device with a block. The block also has the function of a stop block, and cooperates with the fuselage column base to realize the limiting and damping functions.

[0087] A right-angle groove is opened at the working position of the outer end of the fuselage column base. One surface (mounting surface) of the right-angle groove is used to install the U-shaped spring clip, and the other surface (limiting surface) is used for limiting and damping. The U-shaped spring clip is a formed part by bending a spring steel plate. The convex angle structures formed by the inward bending of the two side vertical edges together form a clamping mouth. The outer shape and width dimensions of both sides of the front clamping head of the block match the inner shape and width of the U-shaped spring clip, and the outer shape and width of the rear clamping neck match the shape and width dimensions of the clamping mouth part of the U-shaped clip. When the wing surface rotates from the folded position to the unfolded position, the block rotates around the tail wing rotating shaft with the metal joint. At the end of the unfolding stroke of the tail wing, the clamping head contacts the clamping mouth of the U-shaped spring clip and applies an outward pressure to deform the clamping mouth of the U-shaped spring clip outward. The clamping head passes through the clamping mouth, and the clamping mouth of the U-shaped spring clip resets and matches the clamping neck, locking the clamping head in the working position. The block also has the function of a stop block, and the vertical surface at the front end of the block cooperates with the limiting surface of the right-angle groove of the fuselage column base to realize the limiting - damping function.

[0088] Leaf spring slider - internal locking device with a rotating shaft convex angle and fuselage stop block - vertical tail trailing edge limiting - damping device

[0089] A convex angle (acute angle) is constructed on the circular shoulder of the vertical tail mounting shaft. The convex angle can rotate within a certain angular range along with the rotating shaft (corresponding to the folding and unfolding stroke of the wing surface). Sliders are arranged in the vertical direction perpendicular to the vertical tail rotating shaft on the reference plane of the shoulder-convex angle. Specifically, slider guide grooves are machined on the vertical tail mounting seat of the fuselage and related structures. The guide grooves restrict the sliders and enable them to slide linearly. The front end of the slider is a convex angle, and a notch is opened in the middle of the rear section of the slider. A leaf spring is inserted into the notch. The leaf spring is installed on a platform structure outside the vertical tail mounting seat of the fuselage. The leaf spring applies a pressing force to the slider to keep it in a predetermined position (locking position). The shapes and dimensions of the convex angle of the slider and the convex angle of the rotating shaft are designed to match each other.

[0090] At the end of the rotation stroke of the vertical tail from the folded position to the unfolded position, after the inclined plane of the convex angle rotating along with the rotating shaft contacts the inclined plane of the front convex angle of the slider, a pressure perpendicular to the inclined plane is applied to it. The component of the pressure in the radial direction (vertical direction) overcomes the pressure of the leaf spring, causing the slider to slide linearly outward in the radial direction until the tip of the convex angle of the rotating shaft passes over the tip of the convex angle of the slider, that is, the convex angle of the rotating shaft rotates to the front of the convex angle of the slider, and the rear vertical surface of the convex angle of the rotating shaft is coplanar with the vertical surface of the convex angle of the slider. In this way, the slider slides inward along the guide groove under the action of the pressure of the leaf spring until the tip of the convex angle of the slider abuts against the outer surface of the circular shoulder of the rotating shaft, locking the convex angle of the rotating shaft - the rotating shaft - the vertical tail. When unlocking, hold the cylindrical structure at the rear of the slider and pull it outward to release the constraint of the front convex angle of the slider on the convex angle of the rotating shaft. In this way, the rotating shaft - the vertical tail can rotate from the unfolded position to the folded position.

[0091] Bar-shaped blocks are arranged on the fuselage structure (integrally machined or mechanically connected). The front end face of the block matches the trailing edge of the vertical tail in the unfolded state. In this way, when the vertical tail rotates to the unfolded position, the trailing edge of the vertical tail contacts the block, and the block limits the vertical tail in the unfolded position. The impact energy is absorbed by the block and the vertical tail structure, playing a damping role. The trailing edge structure at the root of the vertical tail is strengthened to withstand greater loads.

[0092] Compared with the prior art, the advantages of this application are as follows: A new folding tail wing structure is provided, and a corresponding locking mechanism is designed. Description of the Drawings

[0093] Figure 1 It is the overall layout diagram of the folding tail wing of the cruise unmanned aerial vehicle in Embodiment 1 of this application in the unfolded state. Among them, a is an axonometric view, b is a rear view, and c is an axonometric view from the rear perspective;

[0094] Figure 2 It is the overall schematic diagram of the folding tail wing of the cruise unmanned aerial vehicle in Embodiment 1 of this application;

[0095] Figure 3 It is the schematic diagram of the mounting seat;

[0096] Figure 4 Schematic diagram of the airfoil structure;

[0097] Figure 5 a and b of () are the axonometric views of the mounting shaft structure;

[0098] Figure 6 Schematic diagram of the flat spiral spring;

[0099] Figure 7 Schematic diagram of the mounting shaft;

[0100] Figure 8 Schematic diagram of the end cover;

[0101] Figure 9 Schematic diagram of the root metal joint;

[0102] Figure 10 Schematic diagram of the U-shaped spring clip;

[0103] Figure 11 For Figure 1 Cross-sectional view A-A in a;

[0104] Figure 12 For Figure 1 Cross-sectional view B-B in a;

[0105] Figure 13 For Figure 1 Cross-sectional view C-C in a;

[0106] Figure 14 For Figure 1 Cross-sectional view D-D in a;

[0107] Figure 15 For Figure 1 Cross-sectional view E-E in b;

[0108] Figure 16 Overall layout diagram of the leaf spring pin latch - built-in locking device for the rotating shaft convex corner and the fuselage stop - trailing edge limit - damping device in Embodiment 2, where a is the schematic diagram, b is the partial enlarged view, and c is the schematic diagram of the end cover at 43;

[0109] Figure 17 Schematic diagram of the mounting seat in Embodiment 2;

[0110] Figure 18 Schematic diagram of the locking device in Embodiment 2;

[0111] Figure 19 Overall structural layout diagram at the mounting seat, where the end cover is made transparent;

[0112] Figure 20 For Figure 14 Cross-sectional view F-F in ;

[0113] Figure 21 for Figure 14 Center section view GG.

[0114] Among them, 1 fuselage structure, 1-1 mounting seat, 1-2 protruding part with right-angle groove, 1-3 stopper, 2 vertical stabilizer, 21 root metal joint, 22 shell, 23 sleeve, 24 rigid foam core, 3 rudder, 31 outer shell, 32 rigid foam core, 33 flexible hinge, 4 folding mechanism, 41 rotating shaft, 42 flat scroll spring, 43 end cover, 44 ball bearing, 45 bearing bushing, 46 vertical tail nut, 47 U-shaped spring clip, 48 leaf spring and gasket, 51 servo, 52 rocker arm, 53 pressure block. Specific implementation plan

[0115] Example 1

[0116] A folding tail wing for a patrol drone, comprising a mounting base, a folding and unfolding mechanism, a locking device, and a wing surface structure;

[0117] The patrol UAV adopts a single vertical tail design, which is arranged on the side of the rear fuselage barrel section, which is an asymmetric layout;

[0118] In the unfolded state, the tail is along the vertical axis of the aircraft; in the folded state, the tail is stored on the side of the rear fuselage barrel section along the longitudinal axis of the aircraft;

[0119] The mounting seat is arranged on the rear side of the cruise drone fuselage and is composed of a mounting shaft, a plane scroll spring, a ball bearing, a bearing bushing, an end cover, a base plate, and a tail wing nut;

[0120] The wing structure includes a vertical stabilizer and a rudder;

[0121] The locking device includes a spring clip-block external locking device and a limit surface limit-damping device;

[0122] The inner side of the outer end of the mounting seat is provided with a thread, and the end cover is connected to the mounting seat through the thread to close the mounting seat;

[0123] The mounting shaft comprises a fuselage connection end with a circular cross section, a tail mounting end with a square cross section, a circular shaft shoulder in the middle of the mounting shaft, and an outer shaft shoulder located on one side of the tail mounting end close to the circular shaft shoulder;

[0124] The radius of the annular shoulder is greater than the radius of the outer shoulder;

[0125] The center of the bottom plate is provided with a circular hole (depth of 3 mm) that matches the size and shape of the fuselage connection end of the mounting shaft;

[0126] A through hole is formed in the center of the end cover, which is matched with the size and shape of the fin mounting end of the mounting shaft;

[0127] The inner plane of the end cover is in contact with the shoulder of the mounting shaft close to the fin mounting end, realizing the installation and limitation of the mounting shaft, and ensuring the free rotation of the mounting shaft;

[0128] The fin mounting end of the mounting shaft extends out from the through hole in the center of the end cover for mounting fins;

[0129] A circular ring bushing is provided between the fuselage connection end of the mounting shaft and the bottom plate, and a ball bearing is placed in the circular ring bushing;

[0130] The flat spiral spring is arranged between the circular ring bushing and the bottom plate;

[0131] A notch is formed at the symmetric center plane position of the fuselage connection end of the mounting shaft, and the width and height dimensions of the notch are matched with the cross-sectional dimensions of the spring steel strip of the flat spiral spring. The notch is used to install the 90° inner bent edge at the center of the flat spiral spring, so that the flat spiral spring is connected to the mounting shaft as a whole;

[0132] The mounting seat is also provided with a notch, and the width and height dimensions of the notch are matched with the cross-sectional dimensions of the spring steel strip of the flat spiral spring. The notch is used to install the 90° outer bent edge at the outer end of the flat spiral spring, so that the flat spiral spring is connected to the mounting seat as a whole;

[0133] The outer end of the mounting shaft is provided with a central threaded hole for installing a fin nut, and the fin nut connects the fin structure and the mounting shaft into a whole;

[0134] A gasket can be inserted between the notch and the bent edge;

[0135] The outer shoulder is used to limit the lateral position of the fin.

[0136] The vertical stabilizer is composed of a shell, a root metal joint, a rigid foam core, a servo mounting seat, a metal wing tip, and a sheath;

[0137] The shell is made of fiberglass or carbon fiber material;

[0138] The root metal joint is provided with a central hole for connecting with the fin mounting end of the mounting shaft;

[0139] The servo mounting seat is placed near the root metal joint, and forms an internal space with the two side shells for installing a servo. A pressing block connected by screws is provided at the opening position of the internal space to completely install and fix the servo; <�

[0140] The metal wing tip is connected to the shell through a connecting block;

[0141] The connecting block and the shell are connected by fasteners;

[0142] The connecting block and the housing are obtained by integral machining;

[0143] The shroud is a detachable component, sleeved outside the lower structure of the vertical stabilizer (below the rudder), forming the aerodynamic outer surface of the trailing edge of the stabilizer;

[0144] The inside of the vertical stabilizer is filled with a rigid foam core.

[0145] When installing the data link antenna inside the tail, a glass fiber material that transmits waves is used as the housing. If no antenna is installed inside, a carbon fiber housing with better performance can be used.

[0146] The rudder includes a servo, a housing, and a rigid foam core;

[0147] The housing is made of carbon fiber material;

[0148] The inside of the rudder is filled with a rigid foam core;

[0149] The vertical stabilizer and the rudder are connected by a flexible hinge;

[0150] The servo is installed on the servo mounting seat;

[0151] The servo has an output shaft, and the output shaft is coaxial with the flexible hinge;

[0152] The output shaft is connected with a rocker arm, the rocker arm is connected with a clamp sleeve, and the clamp sleeve is located outside the lower end head of the rudder, realizing the drive of the servo to the rudder. [[ID=ID=33]]

[0153] The flexible hinge is made of Kevlar fiber material, with a thickness of 0.2 - 0.3 mm;

[0154] The folding and unfolding stroke of the tail is about 90°.

[0155] In the spring clip - block external locking device and the limit surface limit - damping device, the root metal joint is provided with a block extending outside the wing surface structure, and the side of the mounting seat is provided with a U - shaped spring clip, which can clamp the block to realize the locking, limiting, and damping of the wing surface structure;

[0156] The outer end working position of the mounting seat has a protruding part with a right - angled groove. One of the right - angled grooves of the protruding part is the mounting surface for installing the U - shaped spring clip, and the other surface is the limit surface for limiting and damping;

[0157] The U - shaped spring clip is a spring steel plate formed by bending. The convex angle structures formed by the inward bending of the two vertical sides on both sides together form the clamping mouth;

[0158] When the wing surface structure rotates from the folded position to the deployed position, the latch rotates with the root metal joint around the wing surface structure rotation axis. At the end of the tail wing deployment stroke, the latch head contacts the mouth of the U-shaped spring clip and applies an outward pressure to deform the mouth of the U-shaped spring clip outward. The latch head passes through the mouth, and the mouth of the U-shaped spring clip resets and matches the latch neck to lock the latch head in the working position; the latch also functions as a stop block, and the vertical surface at the front end of the latch cooperates with the limiting surface of the right-angle groove of the mounting seat to achieve the limiting-damping function.

[0159] Embodiment 2

[0160] A folding tail wing for a cruise unmanned aerial vehicle is composed of a mounting seat, a folding and deploying mechanism, a locking device, and a wing surface structure;

[0161] The cruise unmanned aerial vehicle adopts a single vertical tail design, and the vertical tail is arranged on the side of the rear fuselage barrel section, which is an asymmetric layout;

[0162] In the deployed state, the tail wing is along the vertical axis of the aircraft; in the folded state, the tail wing is stored along the longitudinal axis of the aircraft on the side of the rear fuselage barrel section;

[0163] The mounting seat is arranged on the side of the rear part of the cruise unmanned aerial vehicle fuselage and is composed of a mounting shaft, a flat spiral spring, a ball bearing, a bearing bushing, an end cover, a bottom plate, and a tail wing nut;

[0164] The wing surface structure includes a vertical stabilizer and a rudder;

[0165] The locking device includes a leaf spring slider-rotating shaft convex angle built-in locking device and a fuselage stop-vertical tail trailing edge limiting-damping device.

[0166] The outer end inner side of the mounting seat is provided with threads, and the end cover is threadedly connected to the mounting seat to seal the mounting seat;

[0167] The mounting shaft includes a fuselage connection end with a circular cross-section, a tail wing mounting end with a square cross-section, a circular ring shaft shoulder in the middle position of the mounting shaft, and an outer shaft shoulder on one side of the tail wing mounting end close to the circular ring shaft shoulder;

[0168] The radius of the circular ring shaft shoulder is greater than the radius of the outer shaft shoulder;

[0169] The center of the bottom plate is made with a round hole (depth 3 mm), which matches the size and shape of the fuselage connection end of the mounting shaft;

[0170] The center of the end cover is made with a through hole, which matches the size and shape of the tail wing mounting end of the mounting shaft;

[0171] The inner plane of the end cover fits with the shaft shoulder of the mounting shaft close to the tail wing mounting end to achieve the installation and limitation of the mounting shaft and ensure the free rotation of the mounting shaft;

[0172] The fin mounting end of the mounting shaft extends out from the through hole at the center of the end cap for mounting the fin;

[0173] A circular ring bushing is provided between the fuselage connection end of the mounting shaft and the bottom plate, and the ball bearing is placed in the circular ring bushing;

[0174] The flat spiral spring is arranged between the circular ring bushing and the bottom plate;

[0175] A notch is made at the symmetrical center plane position of the fuselage connection end of the mounting shaft, and the width and height dimensions of the notch match the cross-sectional dimensions of the spring steel strip of the flat spiral spring. The notch is used to install the 90° inner bent edge at the center of the flat spiral spring, so that the flat spiral spring is connected to the mounting shaft as a whole;

[0176] The mounting seat is also provided with a notch, and the width and height dimensions of the notch match the cross-sectional dimensions of the spring steel strip of the flat spiral spring. The notch is used to install the 90° outer bent edge at the outer end of the flat spiral spring, so that the flat spiral spring is connected to the mounting seat as a whole;

[0177] The outer end of the mounting shaft is provided with a central threaded hole for installing the fin nut, and the fin nut connects the fin structure and the mounting shaft into a whole;

[0178] A gasket can be inserted between the notch and the bent edge;

[0179] The outer shaft shoulder is used to limit the lateral position of the fin.

[0180] The vertical stabilizer is composed of a shell, a root metal joint, a rigid foam core, a servo mounting seat, a metal wing tip, and a sheath;

[0181] The shell is made of fiberglass or carbon fiber material;

[0182] The root metal joint is provided with a central hole for connecting with the fin mounting end of the mounting shaft;

[0183] The servo mounting seat is placed near the root metal joint, and forms an internal space with the two side shells for installing the servo. A pressing block connected by screws is provided at the opening position of the internal space to completely install and fix the servo;

[0184] The metal wing tip is connected to the shell through a connecting block;

[0185] The connecting block and the shell are connected by fasteners;

[0186] The connecting block and the shell are obtained by integral machining;

[0187] The sheath is a detachable component, sleeved outside the lower structure of the vertical stabilizer (below the rudder), and constitutes the aerodynamic outer surface of the trailing edge of the stabilizer;

[0188] The interior of the vertical stabilizer is filled with a rigid foam core.

[0189] When installing a data link antenna inside the fin, a wave-transparent fiberglass material is used as the housing. If no antenna is installed inside, a carbon fiber housing with better performance can be used.

[0190] The rudder consists of a servo, a housing, and a rigid foam core;

[0191] The housing is made of carbon fiber material;

[0192] The interior of the rudder is filled with a rigid foam core;

[0193] The vertical stabilizer and the rudder are connected by a flexible hinge;

[0194] The servo is installed on the servo mount;

[0195] The servo has an output shaft, and the output shaft is coaxial with the flexible hinge;

[0196] The output shaft is connected with a rocker arm, the rocker arm is connected with a clamp sleeve, and the clamp sleeve is located outside the lower end head of the rudder, realizing the drive of the servo to the rudder.

[0197] The flexible hinge is made of Kevlar fiber material with a thickness of 0.2 - 0.3 mm;

[0198] The folding and unfolding stroke of the fin is about 90°.

[0199] The built-in locking device of the leaf spring slider - rotating shaft convex angle and the fuselage stop - vertical tail trailing edge limit - damping device. There is an acute - angled convex angle on the circular shaft shoulder of the mounting shaft, and the convex angle can rotate with the mounting shaft;

[0200] The slider seat is connected to the mounting seat by screws. The slider seat has an inverted T - shaped space inside, and openings are provided on both sides of the bottom and at the top respectively; the longitudinal space of the inverted T - shaped space is the sliding space of the slider; there are through - holes on the mounting seat, which match the synchronous opening size of the slider seat, enabling the slider to slide from the middle of the slider seat to the mounting seat; one end of the leaf spring passes through the slider sleeve through the openings on both sides of the bottom of the slider seat and is screwed to the slider sleeve; the other end of the leaf spring is connected to the leaf spring fixing seat;

[0201] The leaf spring applies a pressing force to the slider to keep it in the locked position;

[0202] The shapes and sizes of the slider convex angle and the mounting shaft convex angle are designed to match;

[0203] At the end of the rotation stroke of the tail fin from the folded position to the deployed position, after the inclined surface of the convex angle rotating with the mounting shaft contacts the inclined surface of the slider convex angle, a pressure perpendicular to the inclined surface is applied to it. The radial component of the pressure overcomes the pressure of the leaf spring, causing the slider to slide linearly outward in the radial direction until the tip of the convex angle of the mounting shaft passes over the tip of the convex angle of the slider, that is, the convex angle of the mounting shaft rotates in front of the convex angle of the slider, and the rear vertical surface of the convex angle of the mounting shaft is coplanar with the vertical surface of the convex angle of the slider. In this way, the slider slides inward along the guide groove under the action of the leaf spring pressure until the tip of the convex angle of the slider abuts against the outer surface of the ring shoulder of the mounting shaft, locking the convex angle of the mounting shaft - the mounting shaft - the tail fin; when unlocking, grasp the cylindrical structure at the rear of the slider and pull it outward, so that the convex angle of the slider releases the constraint on the convex angle of the mounting shaft, and thus the mounting shaft - the tail fin can rotate from the deployed position to the folded position;

[0204] A strip-shaped stop block is provided on the fuselage structure, and the front end surface of the stop block matches the trailing edge of the tail fin in the deployed state; when the tail fin rotates to the deployed position, the trailing edge of the tail fin contacts the stop block, and the stop block confines the tail fin in the deployed position, and the impact energy is absorbed by the stop block and the wing surface structure, playing a damping role;

[0205] The trailing edge structure of the tail fin root is strengthened to withstand greater loads.

Claims

1. A folding tail wing for a loitering unmanned aerial vehicle, characterized in that it consists of a mounting base, a folding and unfolding mechanism, a locking device, and a wing surface structure; The loitering unmanned aerial vehicle adopts a single-tail-wing design, and the tail wing is arranged on the side of the rear fuselage barrel section, which is an asymmetric layout; In the unfolded state, the tail wing is along the vertical axis of the aircraft; In the folded state, the tail wing is stored along the longitudinal axis of the aircraft on the side of the rear fuselage barrel section; The mounting base is arranged on the side of the rear part of the loitering unmanned aerial vehicle fuselage and consists of a mounting shaft, a flat spiral spring, a ball bearing, a bearing bushing, an end cover, a bottom plate, and a tail wing nut; The wing surface structure includes a vertical stabilizer and a rudder; The locking device includes a locking device a and a locking device b; The locking device a includes a spring clip - external locking device for the block and a limiting surface limiting - damping device; The locking device b includes a leaf spring pin latch - internal locking device for the convex angle of the mounting shaft and a fuselage stop - trailing edge limiting - damping device for the tail wing.

2. The folding tail wing for a loitering unmanned aerial vehicle according to claim 1, characterized in that The inner side of the outer end of the mounting base is provided with a thread, and the end cover is connected to the mounting base through the thread for closing the mounting base; The mounting shaft includes a fuselage connection end with a circular cross-section, a tail wing mounting end with a square cross-section, a circular ring shoulder in the middle position of the mounting shaft, and an outer shoulder located on one side of the tail wing mounting end close to the circular ring shoulder; The radius of the circular ring shoulder is greater than the radius of the outer shoulder; A circular hole is made in the center of the bottom plate, which matches the size and shape of the fuselage connection end of the mounting shaft; The depth of the circular hole is 2 - 4 mm; A through hole is made in the center of the end cover, which matches the size and shape of the tail wing mounting end of the mounting shaft; The inner plane of the end cover fits with the shoulder of the mounting shaft close to the tail wing mounting end to achieve the installation and limitation of the mounting shaft and ensure the free rotation of the mounting shaft; The tail wing mounting end of the mounting shaft extends out from the through hole in the center of the end cover for mounting the tail wing; A circular ring bushing is provided between the fuselage connection end of the mounting shaft and the bottom plate, and the ball bearing is placed in the circular ring bushing; The flat spiral spring is arranged between the circular ring bushing and the bottom plate; A notch is made at the symmetric center plane position of the fuselage connection end of the mounting shaft, and the width and height dimensions of the notch match the cross-section dimensions of the spring steel strip of the flat spiral spring. The notch is used to install the 90° inner bent edge in the center of the flat spiral spring, so that the flat spiral spring is connected to the mounting shaft as a whole; A notch is also made on the mounting base, and the width and height dimensions of the notch match the cross-section dimensions of the spring steel strip of the flat spiral spring. The notch is used to install the 90° outer bent edge at the outer end of the flat spiral spring, so that the flat spiral spring is connected to the mounting base as a whole; The outer end of the mounting shaft is provided with a central threaded hole for installing the tail wing nut, and the tail wing nut connects the tail wing structure and the mounting shaft into a whole; A gasket can be inserted between the notch and the bent edge; The outer shoulder is used to limit the lateral position of the tail wing.

3. The folding tail wing for a loitering unmanned aerial vehicle according to claim 1, characterized in that The folding and unfolding mechanism uses a flat spiral spring as the power source. The flat spiral spring is installed inside the mounting base and directly connects the mounting base and the wing surface structure; The outer end of the flat scroll spring is fixedly connected to the mounting seat, and the inner end is inserted into the notch of the axial symmetry center plane of the mounting; When in the folded state, the flat scroll spring applies torque to the wing structure, and when unfolded, the wing structure unfolds under the action of the torque of the flat scroll spring; The flat scroll spring is the power source for the tail wing to unfold, and is arranged at the innermost part of the mounting seat and sleeved outside the mounting shaft; a notch is made at the position of the symmetry center plane at the end section of the mounting shaft, and the width and height dimensions of the notch match the cross-sectional dimensions of the flat scroll spring, and the notch is used to install the 90° inner bent edge at the center of the flat scroll spring, so that the flat scroll spring is connected to the mounting shaft as a whole; The outer end of the flat scroll spring is connected to the fuselage mounting seat; the 90° outer bent edge of the flat scroll spring cooperates with the notch of the fuselage mounting seat, and in the installed state, the 90° outer bent edge is inserted into the mounting notch of the tube body of the fuselage mounting seat.

4. The folding tail wing for a cruise unmanned aerial vehicle according to claim 1, wherein The vertical stabilizer is composed of a shell, a root metal joint, a rigid foam core, a servo mounting seat, a metal wing tip, and a cover; The shell is made of fiberglass or carbon fiber material; The root metal joint is provided with a central hole for connecting with the tail wing mounting end of the mounting shaft; The servo mounting seat is placed near the root metal joint, and forms an internal space with the two side shells for installing the servo, and a pressing block connected by screws is provided at the opening position of the internal space to completely install and fix the servo; The metal wing tip is connected to the shell through a connecting block; The connecting block and the shell are connected by fasteners; The connecting block and the shell are obtained by integral machining; The cover is a detachable component, sleeved outside the lower structure of the vertical stabilizer, and constitutes the aerodynamic outer surface of the trailing edge of the stabilizer; The inside of the vertical stabilizer is filled with a rigid foam core.

5. The folding tail wing for a cruise unmanned aerial vehicle according to claim 1, wherein When installing the data link antenna inside the tail wing, a shell made of wave-transparent fiberglass material is used. If no antenna is installed inside, a carbon fiber shell with better performance can be used.

6. The folding tail wing for a cruise unmanned aerial vehicle according to claim 1, wherein The rudder is composed of a servo, a housing, and a rigid foam core; The housing is made of carbon fiber material; The inside of the rudder is filled with a rigid foam core; The vertical stabilizer and the rudder are connected by a flexible hinge; The servo is installed on the servo mounting seat; The servo is provided with an output shaft, and the output shaft is coaxial with the flexible hinge; The output shaft is connected with a rocker arm, the rocker arm is connected with a clamp, and the clamp is located outside the lower end head of the rudder to realize the driving of the servo to the rudder; The flexible hinge is made of Kevlar fiber material, and the thickness is 0.2 - 0.3 mm.

7. The folding tail wing for the loitering unmanned aerial vehicle according to claim 1, wherein The folding and unfolding stroke of the tail wing is about 90°.

8. The folding tail wing for a cruise unmanned aerial vehicle according to claim 1, wherein In the spring clip - block external locking device and the limit surface limit - damping device, the root metal joint is provided with a block extending outside the wing structure, and a U-shaped spring clip is provided on the side of the mounting seat, and the U-shaped spring clip can clamp the block to realize the locking, limiting and damping of the wing structure; The outer end working position of the mounting seat has a protruding part with a right-angle groove. One of the right-angle grooves of the protruding part is the mounting surface for mounting the U-shaped spring clip, and the other surface is the limiting surface for limiting and damping. The U-shaped spring clip is a formed part by bending a spring steel plate. The convex angle structures are formed by bending the two vertical sides inward, and the two convex angles together form the clamping mouth. When the wing surface structure rotates from the folded position to the unfolded position, the locking block rotates with the root metal joint around the mounting axis of the wing surface structure. At the end of the tail wing unfolding stroke, the locking head contacts the clamping mouth of the U-shaped spring clip and applies an outward pressure to deform the clamping mouth of the U-shaped spring clip outward. The locking head passes through the clamping mouth, and the clamping mouth of the U-shaped spring clip resets and matches with the locking neck to lock the locking head in the working position. The locking block also has the function of a stop block. The vertical front surface of the locking block and the limiting surface of the right-angle groove of the mounting seat cooperate to achieve the limiting-damping function.

9. The folding tail wing for a cruise unmanned aerial vehicle according to claim 1, wherein The circular ring shoulder of the mounting axis is provided with a convex angle with an acute angle, and the convex angle can rotate with the mounting axis. In the unfolded state of the tail wing, the convex angle is in the vertically downward position. In the folded state of the tail wing, the convex angle rotates 90° clockwise to the horizontal position. When the locking device 2 is adopted, the lower part of the mounting seat is provided with a convex platform structure for mounting the pin latch, the leaf spring, and the end cap. The upper side and the left side of the mounting seat are each provided with a convex platform structure. Threaded holes are made on the three convex platform structures, and the 3 threaded holes are evenly distributed on a circle with the mounting axis as the center for connecting the end cap. The convex platform structure at the lower part of the mounting seat is provided with a vertically downward pin guide groove, and the cross-sectional shape of the pin guide groove matches the cross-sectional shape of the pin latch. The pin guide groove and the end cap jointly restrict the pin latch to slide linearly only along the axis direction of the pin guide groove. The front section of the pin latch is a slender rectangular cross-section pin, and the front end of the pin is obliquely cut to form a convex angle. The shape and size of the convex angle at the front end of the pin match the convex angle of the mounting axis. The rear section of the pin latch is a short and thick cylindrical base, and a notch is opened in the cylindrical base, and the leaf spring is inserted into the notch. The leaf spring applies a pressing force to the pin latch to keep it in the locked position. The leaf spring is installed on the convex platform structure at the lower part of the mounting seat. Three mounting holes are evenly distributed on the end cap and match the 3 threaded holes of the mounting seat. Three small-diameter bolts / screws are used to connect the end cap to the mounting seat. There is also a limiting notch ring structure on the inner side of the end cap. The two cut surfaces of the ring match the two surfaces of the convex angle of the mounting axis, corresponding to the folded position and the unfolded position of the tail wing respectively. At the end of the rotation stroke of the tail wing from the folded position to the unfolded position, after the inclined surface of the convex angle of the mounting axis contacts the inclined surface of the front convex angle of the pin latch, a pressure perpendicular to the inclined surface is applied to it, and the radial component of the pressure overcomes the pressure of the leaf spring to make the pin latch slide linearly outward in the radial direction until the tip of the convex angle of the mounting axis passes over the tip of the convex angle of the pin, that is, the convex angle of the mounting axis rotates to the front of the convex angle of the pin, and the rear vertical surface of the convex angle of the mounting axis is coplanar with the vertical surface of the convex angle of the pin. In this way, the pin latch slides upward along the guide groove under the action of the leaf spring pressure until the tip of the convex angle of the pin abuts against the outer surface of the circular ring shoulder of the mounting axis to lock the convex angle of the mounting axis - the mounting axis - the tail wing. When unlocking, grasp the cylindrical base at the rear of the pin latch and pull it outwards, so that the convex corner at the front of the pin latch releases the constraint on the convex corner of the mounting shaft. In this way, the mounting shaft - fin can rotate from the deployed position to the folded position; Arrange strip - shaped stoppers on the fuselage structure, and the front end face of the stopper matches the trailing edge of the fin in the deployed state. When the fin rotates to the deployed position, the trailing edge of the fin contacts the stopper, and the stopper confines the fin in the deployed position. The impact energy is absorbed by the stopper and the fin structure, playing a damping role; Reinforce the design of the trailing edge structure at the root of the fin to withstand greater loads.

Images