An aircraft folding rudder and its locking and unlocking device

Abstract

The application relates to a folding rudder of an aircraft and a locking and unlocking device thereof, and the folding rudder comprises an outer rudder, an inner rudder, a locking pin mechanism and a driving mechanism; the bottom of the outer rudder is provided with a rotating shaft hole part and a locking pin hole part; the upper part of the inner rudder is provided with a mounting hole part and a positioning hole part; the locking pin mechanism is arranged in the locking pin hole part and comprises a locking pin, a compression spring and a plug; the driving mechanism comprises a sleeve shaft and a torsion bar, the sleeve shaft penetrates through the outer rudder and the inner rudder and connects the two; one end of the torsion bar is fixed on the positioning hole part through the sleeve shaft, and the other end is fixed on the locking pin hole part through the plug; the outer rudder can be folded around the sleeve shaft; the locking and unlocking device comprises a grid wing, a limiting rod and a separation mechanism; the folding rudder is installed on the periphery of a shell of a servo cabin of the aircraft; the limiting rod is installed on the grid wing and is connected with the aircraft through the separation mechanism; and the extending part of the limiting rod restricts the outer rudder in the folded state. Compared with the prior art, the structure of the application is simpler, the aerodynamic performance is better, and the unlocking and unfolding have little influence on the flight attitude of the aircraft.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft structure design, and particularly relates to an aircraft folding rudder and a locking and unlocking device thereof. BACKGROUND

[0002] To meet the combat requirements of modern war outside the defense zone, the range of cruise missiles is required to be continuously improved. At the same time, the missile is limited by the strict constraints of the space envelope of the carrier aircraft, and is required to reduce the transverse length, adapt to the carrier platform and launching device, and further improve the carrying capacity of the carrier aircraft to have high-density strike capability. The requirements of long range and small size make combat weapons more and more adopt the layout mode of folding rudder, and the rudder surface can be rapidly deployed after the missile is launched.

[0003] Through prior art retrieval, it is found that Chinese invention patent publication No. CN114199083A discloses a missile folding rudder self-locking system, which comprises an inner rudder, an outer rudder, a driving mechanism and a locking pin mechanism, etc. The inner rudder and the outer rudder are drivingly connected through the driving mechanism, and after being deployed in place, the end part of the locking rod is embedded into the outer rudder locking pin hole to realize the locking of the folding rudder. However, the above-adopted technology has the following disadvantages. The inner rudder root of the folding rudder needs sufficient thickness space to install the locking pin, which will significantly increase the aerodynamic resistance of the rudder surface. The structure is complex, and the locking pin mechanism needs to be additionally provided with a limiting mechanism such as a shearing screw.

[0004] Box-type launched missiles are usually constrained by box walls to fold the rudder, and the folding rudder is deployed under the action of the deployment mechanism at the moment when the missile is launched out of the box, while the airborne rack-type launched missile also needs to design a special folding rudder locking and unlocking device. Through prior art retrieval, it is found that Chinese invention patent publication No. CN113624074A discloses a missile folding rudder locking and unlocking device, which comprises a missile body, a locking mechanism and a rudder support. After the missile is launched, the rudder surface needs to be unlocked by being deflected to separate from the locking mechanism. The deflection of the rudder surface will cause an initial disturbance torque of the missile, affecting the initial flight attitude of the missile. At the same time, the locking mechanism will remain in the tail of the missile body, increasing the aerodynamic resistance of the missile and affecting the flight performance of the missile.

[0005] Therefore, it is urgent to develop an aircraft folding rudder and a locking and unlocking device thereof, which have a simpler structure, good aerodynamic performance and little influence on the flight attitude of the aircraft during unlocking and deployment. SUMMARY

[0006] In view of the above defects or improvement needs of the prior art, the present application provides an aircraft folding rudder and a locking and unlocking device thereof, which have a simple mechanism composition, reliable function, convenient installation, debugging and service processing, and thus solve the technical problems of insufficient aerodynamic performance of the folding rudder and its locking and unlocking device and large disturbance to the flight attitude of the aircraft during the unlocking and deployment process in the prior art.

[0007] To achieve the above object, the technical scheme adopted by the present application is as follows:

[0008] The aircraft folding rudder comprises an outer rudder, an inner rudder, a locking pin mechanism and a driving mechanism.

[0009] One end of the bottom of the outer rudder is provided with a rotating shaft hole part, and the other end is provided with a locking pin hole part.

[0010] One end of the upper part of the inner rudder is provided with a mounting hole part, and the other end is provided with a positioning hole part.

[0011] After the outer rudder and the inner rudder are assembled, the positioning hole part, the rotating shaft hole part, the mounting hole part and the locking pin hole part are arranged in sequence and located on the same rotating shaft line.

[0012] The locking pin mechanism is arranged in the locking pin hole part and comprises a locking pin, a compression spring and a plug. One end of the compression spring abuts against the locking pin, and the other end abuts against the plug.

[0013] The driving mechanism comprises a sleeve shaft and a torsion bar. The sleeve shaft is inserted into the positioning hole part, the rotating shaft hole part, the mounting hole part and the locking pin hole part. One end of the sleeve shaft is provided with a first structure which is matched with a second structure arranged at one end of the locking pin. The torsion bar passes through the sleeve shaft, the locking pin and the compression spring in sequence. One end of the torsion bar is fixed on the positioning hole part through the sleeve shaft, and the other end is fixed on the locking pin hole part through the plug.

[0014] The outer rudder can be folded by rotating around the sleeve shaft.

[0015] Further, the sleeve shaft comprises a first cylindrical segment, a square positioning segment and a first structure in sequence. The middle part of the positioning hole part is square and matched with the square positioning segment of the sleeve shaft to play the role of positioning and bearing. The first structure is a clamping convex. The sleeve shaft adopts a multi-purpose structure form. On the one hand, the sleeve shaft provides rotating support for the inner rudder and the outer rudder. On the other hand, the sleeve shaft provides a locking interface for the locking pin.

[0016] Further, one end of the locking pin is provided with the second structure, and the other end is provided with a front guide segment. The second structure is matched with the first structure of the sleeve shaft, the front guide segment extends into the compression spring, and the second structure is a clamping groove. The locking pin is only one group which is provided with the clamping groove structure instead of the clamping convex structure. In the narrow space, the rectangular key has a longer size, the gap between the locking pin and the outer rudder in the guide cooperation can be further reduced, and the bearing capacity between them can be improved.

[0017] Preferably, the clamping convex and the clamping groove adopt a taper design, the cooperation of the clamping convex and the clamping groove has a self-locking function, and the locking mechanism is prevented from being unlocked under the action of the aerodynamic force.

[0018] Further, the lock pin hole member is provided with two sets of symmetrical rectangular key grooves, and the lock pin is provided with two sets of symmetrical rectangular keys, which are matched and installed.

[0019] Further, the lock pin hole member is provided with two sets of symmetrical rectangular key grooves, and the lock pin is provided with two sets of symmetrical rectangular keys, which are matched and installed.

[0020] Further, the mounting hole member is provided with a limiting plate.

[0021] Further, the plug is provided with a rear guide section at one end and a slot at the other end, and the rear guide section extends into the compression spring.

[0022] Further, the lock pin hole member is provided with a threaded hole, the plug is provided with a plug round hole, and the torsion rod is provided with a torsion rod round hole, the positions of the threaded hole, the plug round hole and the torsion rod round hole correspond to each other, the outer rudder is provided with a tightening screw, and the tightening screw passes through the threaded hole, the plug round hole and the torsion rod round hole to simultaneously fix the lock pin hole member, the plug and the torsion rod.

[0023] Further, the torsion rod is one or more rectangular cross-section torsion rods, which can be used in multiple groups, have the characteristics of simple structure, high material utilization rate and large driving force, and have the advantages of light weight, simple structure and large torque compared with other elastic elements such as springs and torsion springs. Under the condition of meeting the deployment time, the impact on the aircraft itself during the deployment process is small.

[0024] Based on the same technical concept, the application also provides a locking and unlocking device for the aircraft folding rudder, which comprises a grid wing, a limiting rod and a separation mechanism.

[0025] The aircraft comprises a servo cabin shell, the aircraft folding rudder is installed on the side of the servo cabin shell, the grid wing is installed on the tail of the servo cabin shell through the separation mechanism, the limiting rod is installed on the grid wing, and the extending part of the limiting rod restricts the outer rudder in the folded state.

[0026] Further, the separation mechanism is an explosive bolt.

[0027] Compared with the prior art, the above technical solutions based on the technical concept of the application can achieve the following beneficial effects:

[0028] 1. The folding rudder driving mechanism and the locking mechanism are arranged on the same rotation axis, which reduces the protruding structure of the outer surface of the folding rudder or reduces the overall thickness of the rudder surface, and improves the aerodynamic performance of the aircraft.

[0029] 2. The folding rudder rotation shaft position can be arranged at the root of the rudder surface as much as possible, and under the condition of the same envelope size, a larger aerodynamic lift surface is allowed.

[0030] 3. The compression state of the locking pin is limited by the front end face of the sleeve, and during the process of the rudder surface unfolding, the compression of the locking pin is gradually released, and no additional cutting screw, unlocking baffle and other mechanisms are needed.

[0031] 4. All the folded rudder surfaces are constrained by the same locking and unlocking device, the number of locking and unlocking devices is reduced, and the unfolding synchronization performance of the rudder wing is improved.

[0032] 5. The constraint release of the folded rudder wing is achieved by separating the locking and unlocking device, the locking mechanism is not needed to be separated by rudder deflection, and there is no additional protruding structure after separation. The aerodynamic resistance of the aircraft is reduced, and the influence of the folded rudder unlocking and unfolding process on the flight attitude of the aircraft is small.

[0033] 6. The structure of the present application is simple and compact, and the manual or automatic unfolding and locking of the folded rudder is easy to realize, the installation, debugging and service processing are convenient, and it is especially suitable for the transverse folded rudder wing of small and medium-sized aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0034] Figure 1 is the exploded view of the folded rudder in the embodiment of the present application;

[0035] Figure 2 is the partial sectional view of the main view of the folded rudder in the embodiment of the present application;

[0036] Figure 3 is the schematic diagram of the locking state of the driving and locking mechanism of the folded rudder in the embodiment of the present application;

[0037] Figure 4 is the schematic diagram of the unlocking state of the driving and locking mechanism of the folded rudder in the embodiment of the present application;

[0038] Figure 5 is the axonometric view of the folded rudder in the embodiment of the present application;

[0039] Figure 6 is the bottom view of the folded rudder in the embodiment of the present application.

[0040] In all the drawings, the same reference signs are used to represent the same elements or structures, wherein:

[0041] 1. Outer rudder; 1a. Rotary shaft hole (with internal rotating shaft hole 1a1); 1b. Locking pin hole (with internal rotating shaft hole 1b1); 1c. Rectangular keyway; 1d. U-shaped groove; 1e. Threaded hole; 2. Inner rudder; 2a. Mounting hole (with internal mounting hole 2a1); 2b. Positioning hole (with internal positioning hole 2b1); 2c. Limiting plate; 3. Sleeve shaft; 3a. First cylindrical section; 3b. Square positioning structure; 3c. Second cylindrical section; 3d. Locking protrusion; 3e. Positioning surface; 4. Torsion bar; 4a. Torsion bar round hole; 5. Locking pin; 5a. Rectangular key; 5b. Slot; 5c. Unlocking hole; 5d. Front guide section; 6. Compression spring; 7. Plug; 7a. Rear guide section; 7b. Slot; 7c. Plug round hole; 8. Cylindrical pin; 8a. Cylindrical hole; 9. Set screw; 10. Tightening screw; 11. Folding rudder; 12. Grid wing; 13. Limiting rod; 14. Explosion bolt; 15. Servo cabin shell. Detailed Implementation

[0042] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application. Rather, embodiments of the present invention include all variations, modifications, and equivalents falling within the spirit and scope of the appended claims.

[0043] like Figures 1-6 As shown, an aircraft folding rudder 11 includes an outer rudder 1, an inner rudder 2, a locking pin mechanism, and a drive mechanism.

[0044] The outer rudder 1 has a pivot hole 1a at one end of its bottom and a locking pin hole 1b at the other end.

[0045] The inner rudder 2 has a mounting hole 2a at one end and a positioning hole 2b at the other end. The positioning hole 2b is open at one end and closed at the other end. The bottom of the inner rudder 2 has a connection interface with the output shaft of the electric servo motor.

[0046] After the outer rudder 1 and the inner rudder 2 are assembled, the positioning hole 2b, the shaft hole 1a, the mounting hole 2a, and the locking pin hole 1b are arranged in sequence and located on the same axis of rotation.

[0047] The locking mechanism is set in the locking pin hole 1b1 in the locking pin hole 1b, and includes a locking pin 5, a compression spring 6 and a plug 7. One end of the compression spring 6 abuts against the locking pin 5 and the other end abuts against the plug 7. The locking pin 5 can move along the rotation axis of the folding rudder 11 under the action of the compression spring 6.

[0048] The driving mechanism comprises a sleeve shaft 3 and a torsion bar 4, the sleeve shaft 3 is inserted into the positioning hole member 2b, the rotating shaft hole member 1a, the mounting hole member 2a and the locking pin hole member 1b, and provides mounting support and a rotating center for the inner rudder 2 and the outer rudder 1. One end of the sleeve shaft 3 is provided with a first structure which is matched with a second structure provided at one end of the locking pin 5; the torsion bar 4 passes through the sleeve shaft 3, the locking pin 5 and the compression spring 6 in sequence, one end of the torsion bar 4 is fixed on the positioning hole member 2b through the sleeve shaft 3, and the other end of the torsion bar 4 is fixed on the locking pin hole member 1b through the plug 7, and the middle part of the torsion bar 4 is a working section.

[0049] The outer rudder 1 can rotate and fold around the sleeve shaft 3, and the folding function of the outer rudder 1 relative to the inner rudder 2 is realized.

[0050] The locking and unlocking device of the folding rudder 11 of the aircraft is arranged at the tail end of the aircraft servo cabin shell 15, and the outer rudder 1 in the folded state is limited by the locking and unlocking device.

[0051] As shown in Figure 1 , in some embodiments, the rotating shaft hole member 1a is provided with a rotating shaft hole 1a1, the locking pin hole member 1b is provided with a locking pin hole 1b1, the diameter of the locking pin hole 1b1 is greater than that of the rotating shaft hole 1a1, the locking pin hole 1b1 is coaxial with the rotating shaft hole 1a1, the inner wall of the locking pin hole 1b1 is provided with two symmetric rectangular key grooves 1c, the locking pin 5 is symmetrically arranged with two groups of rectangular keys 5a, the rectangular keys 5a are matched with the rectangular key grooves 1c for installation, and have the characteristics of high positioning and guiding precision and strong bearing capacity; the locking pin hole member 1b is provided with U-shaped grooves 1d on the left and right sides, and is provided with a threaded hole 1e at the tail, and the threaded hole 1e is used for fixing the plug 7 and the torsion bar 4 by cooperating with the tightening screw 10.

[0052] As shown in Figure 1 , Figure 6 , in some embodiments, one end of the inner rudder 2 is provided with a mounting hole member 2a, and the other end is provided with a positioning hole member 2b, the mounting hole member 2a is internally provided with a cylindrical mounting hole 2a1, and the positioning hole member 2b is provided with a positioning hole 2b1, the middle part of the positioning hole 2b1 is in a square structure; the upper end of the positioning hole member 2b is provided with a limiting plate 2c, the limiting plate 2c is an inclined plate, and the outer rudder 1 collides with the limiting plate 2c after being unfolded to position, avoiding the outer rudder 1 from moving forward under the action of inertial force after being unfolded to position, and improving the unfolding precision and unfolding time of the outer rudder 1. In the folded state of the outer rudder 1, the limiting plate 2c and the plane of the outer rudder 1 form an included angle of 135°, as shown in Figure 6 .

[0053] As shown in Figure 1 , Figure 3 , Figure 4As shown, in some embodiments, the drive mechanism includes a sleeve shaft 3 and a torsion bar 4. The sleeve shaft 3 is a concentric cylindrical structure. The front outer end of the sleeve shaft 3 is provided with a first cylindrical section 3a, the middle part is provided with a square positioning structure 3b, which is used to cooperate with the positioning hole 2b1 for installation, the rear end is provided with a second cylindrical section 3c, and the end is provided with a conical locking protrusion 3d (first structure), which can fit with the locking groove 5b (second structure) on the locking pin 5 for locking.

[0054] Preferably, the sleeve shaft 3 and the locking pin 5 are both made of high-strength steel, and they are the main load-bearing components of the folding rudder 11.

[0055] like Figure 1 , Figure 2 As shown, in some embodiments, the sleeve shaft 3 is inserted into the positioning hole 2b, the rotating shaft hole 1a, the mounting hole 2a, and the locking pin hole 1b;

[0056] like Figure 1 , Figure 3 , Figure 4 As shown, in some embodiments, the square structure in the middle of the sleeve shaft 3 is installed in conjunction with the positioning hole 2b1 of the inner rudder 2. On the one hand, this ensures the installation accuracy of the locking protrusion 3d on the sleeve shaft 3 relative to the inner rudder 2. On the other hand, the square structure transmits the aerodynamic load borne by the outer rudder 1 to the inner rudder 2.

[0057] like Figure 1 , Figure 3 , Figure 4 As shown, in some embodiments, the locking pin mechanism is disposed within the locking pin hole 1b, including a locking pin 5, a compression spring 6, and a plug 7. The main body of the locking pin 5 is a concentric cylindrical structure with an unlocking hole 5c. The front end of the locking pin 5 is provided with a groove 5b (second structure), the middle part is provided with an unlocking hole 5c, and the rear end is provided with a front guide section 5d. When the locking pin 5 is assembled within the locking pin hole 1b, the unlocking hole 5c and the U-shaped groove 1d are aligned.

[0058] There is only one set of locking pins 5, which is designed with a slot 5b structure instead of a protrusion 3d structure. In the confined space, this allows the rectangular key 5a to have a longer dimension, which can further reduce the guide clearance between the locking pin 5 and the outer rudder 1 and improve the load-bearing capacity between them. The protrusion 3d and the slot 5b on the sleeve shaft 3 adopt a tapered design, and the two have a self-locking function to prevent the locking mechanism from unlocking under aerodynamic force.

[0059] like Figure 1 , Figure 3 , Figure 4As shown in the drawings, in some embodiments, the card slot 5b and the clamping convex 3d of the sleeve shaft 3 are matched with each other, the front guide section 5d of the locking pin 5 extends into the compression spring 6, the locking pin 5 is matched with the rectangular key groove 1c in the locking pin hole 1b1 of the outer rudder 1 through the rectangular key 5a, the key groove matching surface is long, the matching gap between the outer rudder 1 and the locking pin 5 is reduced, and the rectangular key 5a bears the aerodynamic load of the outer rudder 1, so that the bearing performance is better.

[0060] The locking pin 5 is limited by the rear end surface of the sleeve shaft 3 in the compressed state, and the compression of the locking pin 5 is gradually released during the unfolding process of the outer rudder 1, and no additional shearing pin, unlocking baffle and other mechanisms are needed.

[0061] As shown in the drawings, Figure 1 , Figure 3 , Figure 4 As shown in the drawings, in some embodiments, one end of the compression spring 6 acts on the front guide section 5d of the locking pin 5, and the other end is fixed and supported at the rear guide section 7a of the plug 7, which is the driving energy source of the locking pin 5, and one side of the plug 7 is provided with a plug round hole 7c.

[0062] As shown in the drawings, Figure 1 , Figure 2 As shown in the drawings, in some embodiments, the outer rudder 1, the inner rudder 2 and the sleeve shaft 3 constitute a rotating pair, and the outer rudder 1 can rotate and fold around the sleeve shaft 3.

[0063] As shown in the drawings, Figure 2 In the embodiments of the present application, the outer rudder 1 and the inner rudder 2 constitute a pneumatic lifting surface, and the locking mechanism and the rotation axis of the outer rudder 1 are arranged on the same axis, so as to reduce the aerodynamic resistance of the rudder surface and improve the aerodynamic performance of the aircraft.

[0064] The torsion bar 4 passes through the sleeve shaft 3, the locking pin 5 and the compression spring 6 in sequence, one end is fixed on the positioning hole piece 2b through the sleeve shaft 3, the other end is fixed on the locking pin hole piece 1b through the plug 7, and the middle part is a working section. The torsion bar 4 adopts a large length-width ratio structure and a rectangular cross section, so that the stress distribution is more uniform and the material utilization rate is higher.

[0065] As shown in the drawings, Figure 1 In some embodiments, one end of the torsion bar 4 is provided with a torsion bar round hole 4a, which corresponds to the position of the threaded hole 1e on the locking pin 5, a screw 10 is screwed through the threaded hole 1e, the plug round hole 7c and the torsion bar round hole 4a to fix the locking pin 5, the plug 7 and the torsion bar 4, at the same time, the other end of the torsion bar 4 is provided with a cylindrical hole 8a, and the sleeve shaft 3 is provided with a corresponding through hole, and the torsion bar 4 and the sleeve shaft 3 are fixed by inserting a cylindrical pin 8.

[0066] Two groups of fastening through holes are respectively arranged on the first cylindrical section 3a and the square positioning structure 3b of the sleeve shaft 3, the mounting hole member 2a and the positioning hole member 2b are provided with corresponding fastening screw holes, the sleeve shaft 3 is fixed with the inner rudder 2 by inserting the fastening screw 9, and the axial displacement of the sleeve shaft 3 is limited.

[0067] As shown in the figure, Figure 1 In some embodiments, the torsion bar 4 is made of NL-2 high-strength steel, and is a power source for unfolding the outer rudder 1. The torsion bar 4 is a large-aspect-ratio rectangular cross-section torsion bar, and high-strength material is selected, so that the tensile strength is as high as 2200Mpa, the cross-sectional size of the torsion bar 4 is reduced, and the mounting structure is more compact. Compared with the circular cross-section and the small-aspect-ratio rectangular cross-section torsion bar, the stress distribution of the large-aspect-ratio rectangular cross-section torsion bar is more uniform, and the material utilization rate is higher. In the embodiment, two groups of rectangular cross-section torsion bars are combined for use. Compared with other elastic elements such as springs and torsion springs, the torsion bar has the advantages of light weight, simple structure and large torque. Under the condition of meeting the unfolding time, the impact on the aircraft itself during the unfolding process is small.

[0068] Based on the same technical concept, the application also provides a locking and unlocking device of the above-mentioned aircraft folding rudder 11, which comprises a grid wing 12, a limiting rod 13 and a separation mechanism.

[0069] As shown in the figure, Figure 5 , Figure 6 In some embodiments, the folding rudder 11 is mounted on the output shaft of the electric rudder on the inside of the aircraft servo cabin shell 15, and four groups of folding rudders 11 are arranged in an X shape. The grid wing 12 is fixed at the end of the servo cabin shell 15 through two explosive bolts 14 (separation mechanism), and plays a role in stabilizing the attitude of the aircraft before the rudder surface is unfolded after the aircraft is launched. The limiting rod 13 is arranged on the grid wing 12, and the outer rudder 1 is limited by the limiting rod 13 in the folded state and cannot be unfolded.

[0070] After receiving the control system unlocking instruction, the explosive bolt 14 works to separate the grid wing 12 and the limiting rod 13 mounted on the grid wing 12, and release the constraint on the outer rudder 1. After the locking and unlocking device is separated, there is no any redundant protrusion on the outer surface of the servo cabin shell 15, and the aircraft has good aerodynamic performance.

[0071] The plurality of outer rudders 1 are constrained by the same locking and unlocking device, the number of the locking and unlocking devices is reduced, and the unfolding synchronization performance of the rudder wing is improved.

[0072] The working principle of the aircraft folding rudder 11 provided by the application is as follows:

[0073] The folding rudder 11 mounting process: the torsion bar 4 is inserted into the inside of the sleeve shaft 3, and is fixed by cooperating with the sleeve shaft 3 through the cylindrical pin 8; the lower part of the outer rudder 1 is mounted with the upper part of the inner rudder 2, and is sequentially butted according to the positioning hole part 2b, the rotating shaft hole part 1a, the mounting hole part 2a and the locking pin hole part 1b, and the axis is aligned, the sleeve shaft 3 assembly with the torsion bar 4 is inserted from the locking pin hole part 1b until the positioning surface 3e of the sleeve shaft 3 contacts the closed end of the positioning hole part 2b, and the four sets of limiting screws 9 are fixed to limit the axial displacement of the sleeve shaft 3; the locking pin 5, the locking spring and the plug 7 are sequentially inserted into the locking pin hole 1b1 of the outer rudder 1 through the torsion bar 4, when the locking pin 5 is assembled in the locking pin hole part 1b, the unlocking hole 5c and the U-shaped groove 1d are aligned, at this time, the clamping groove 5b of the locking pin 5 and the clamping convex 3d of the sleeve shaft 3 are mutually embedded and locked, see Figure 3 ; finally, the plug 7 is rotated by a certain angle through the slot 7b at the rear end of the plug 7, the round hole of the plug 7 and the torsion bar round hole 4a are aligned with the rear end threaded hole 1e of the outer rudder 1, and the screw 10 is tightened to fix the three at the same time, the opening position of the threaded hole 1e on the locking pin hole part 1b in the circumferential direction determines the rotation angle of the torsion bar 4, so that the initial pre-tightening torque of the torsion bar 4 can be controlled.

[0074] The folding rudder 11 unlocking and locking device restraining process: the unlocking hole 5c on the locking pin 5 is pushed by the tool through the U-shaped groove 1d of the outer rudder 1, the locking pin 5 is pushed to the compression spring 6 direction (the compression amount of the compression spring 6 is greater than the length of the clamping groove 5b), the clamping groove 5b of the locking pin 5 is out of the clamping convex 3d on the sleeve shaft 3, and then the outer rudder 1 is manually folded to the locking position. The limiting rod 13 is installed on the corresponding position of the grid wing 12. At this time, the limiting rod 13 restrains the outer rudder 1 in the folded state, the torsion bar 4 is elastically deformed under torsion, the elastic potential energy is stored, the locking pin 5 rotates with the outer rudder 1, and finally is limited by the end surface of the sleeve shaft 3, see Figure 4 .

[0075] When the control system issues an unlocking instruction, the explosive bolt 14 works to separate the grid wing 12 and the limiting rod 13 installed on the grid wing 12, and the four sets of outer rudders 1 are simultaneously unfolded, and the unfolding synchronization is good. During the unfolding process of the outer rudder 1, the locking mechanism is synchronously rotated, and at the same time, the locking pin 5 starts to move along the rotating shaft to the sleeve shaft 3 under the action of the compression spring 6. After the outer rudder 1 is unfolded to the position, the outer rudder 1 is limited by the limiting plate 2c, so that the outer rudder 1 is prevented from moving forward under the action of inertia force after being unfolded to the position, the unfolding precision and the unfolding time of the outer rudder 1 are improved. Under the action of the initial pre-tightening force of the torsion bar 4, the outer rudder 1 is always subjected to the torque in the unfolding direction. After the outer rudder 1 and the inner rudder 2 are unfolded to the position, the clamping groove 5b of the locking pin 5 is embedded on the clamping convex 3d at the rear end of the sleeve shaft 3 under the pushing of the spring, the reliable locking of the inner rudder 2 and the outer rudder 1 is realized, the self-locking function is achieved, and the aerodynamic lift is provided for the aircraft.

[0076] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like refer to the orientation or positional relationship shown in the drawings, and are only intended to facilitate the description of the present application and simplify the description, and are not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0077] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which do not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict, provided that they do not conflict.

Claims

1. An aircraft folding rudder, characterized in that, The outer rudder, the inner rudder, the locking pin mechanism and the driving mechanism are included. The outer rudder is provided with a rotating shaft hole at one end of the bottom and a locking pin hole at the other end. The inner rudder is provided with a mounting hole at one end of the upper part and a positioning hole at the other end. The positioning hole, the rotating shaft hole, the mounting hole and the locking pin hole are arranged in sequence and located on the same rotating shaft line after the outer rudder and the inner rudder are assembled. The locking pin mechanism is arranged in the locking pin hole and includes a locking pin, a compression spring and a plug. The driving mechanism includes a sleeve shaft and a torsion bar. The sleeve shaft is inserted into the positioning hole, the rotating shaft hole, the mounting hole and the locking pin hole. The sleeve shaft is provided with a first structure at one end, which is matched with a second structure arranged at one end of the locking pin. The torsion bar is sequentially inserted into the sleeve shaft, the locking pin and the compression spring. One end of the torsion bar is fixed on the positioning hole through the sleeve shaft, and the other end is fixed on the locking pin hole through the plug. The sleeve shaft sequentially includes a first cylindrical segment, a square positioning segment and the first structure. The middle part of the positioning hole is square, which is matched with the square positioning segment of the sleeve shaft. The first structure is a clamping protrusion. The locking pin is provided with the second structure at one end and a front guide segment at the other end. The second structure is matched with the first structure of the sleeve shaft, and the front guide segment extends into the compression spring. The second structure is a clamping groove. The outer rudder can be rotated and folded around the sleeve shaft.

2. The folding rudder of claim 1, wherein, The locking pin hole is provided with two sets of symmetrical rectangular key grooves, and the locking pin is provided with two sets of symmetrical rectangular keys, which are matched and installed with each other.

3. The folding rudder of claim 1, wherein, An unlocking hole is arranged on the sleeve shaft, and a U-shaped groove is arranged on the locking pin hole. When the sleeve shaft is assembled in the locking pin hole, the unlocking hole and the U-shaped groove are aligned.

4. The folding rudder of claim 1, wherein, A limiting plate is arranged on the mounting hole.

5. The folding rudder of claim 1, wherein, The plug is provided with a rear guide segment at one end and a slot at the other end. The rear guide segment extends into the compression spring.

6. The folding rudder of claim 1, wherein, The torsion bar is one or more rectangular cross-section torsion bars.

7. The locking and unlocking device of the folding rudder of the aircraft according to any one of claims 1-6, including a grid wing, a limiting rod and a separation mechanism. The aircraft includes a servo cabin shell, and the folding rudder of the aircraft is installed on the circumferential side of the servo cabin shell. The grid wing is installed on the tail of the servo cabin shell through the separation mechanism, and the limiting rod is installed on the grid wing. The extending part of the limiting rod restricts the outer rudder in the folded state.

8. The lock release device according to claim 7, wherein The separation mechanism is an explosive bolt.

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