CN116625177A

CN116625177A - Folding rudder of aircraft and locking and unlocking device thereof

Info

Publication number: CN116625177A
Application number: CN202310782399.2A
Authority: CN
Inventors: 王力; 索桂兰; 彭逍; 龚健; 尹凯; 杜爽; 杨涵斐; 张泽; 黄一鸣; 张潇
Original assignee: Hubei Institute Of Aerospacecraft
Current assignee: Hubei Institute Of Aerospacecraft
Priority date: 2023-06-29
Filing date: 2023-06-29
Publication date: 2023-08-22

Abstract

The application relates to a folding rudder of an aircraft and a locking and unlocking device thereof, wherein 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 piece and a locking pin hole piece; the upper part of the inner rudder is provided with a mounting hole piece and a positioning hole piece; the locking pin mechanism is arranged in the locking pin hole piece and comprises a locking pin, a compression spring and a plug; the driving mechanism comprises a sleeve shaft and a torsion bar, and the sleeve shaft penetrates through the outer rudder and the inner rudder to connect the outer rudder and the inner rudder; one end of the torsion bar is fixed on the positioning hole piece through a sleeve shaft, the other end of the torsion bar is fixed on the lock pin hole piece through a plug, and the outer rudder can be folded around the sleeve shaft; the locking and unlocking device comprises grid wings, a limiting rod and a separating mechanism; the folding rudder is arranged on the peripheral side of the servo cabin shell of the aircraft, the limiting rods are arranged on the grid wings and are connected with the aircraft through the separating mechanism, and the extending parts of the limiting rods restrict the outer rudder in a folding state. Compared with the prior art, the application has simpler structure, good aerodynamic performance and small influence on the flight attitude of the aircraft due to unlocking and unfolding.

Description

Folding rudder of aircraft and locking and unlocking device thereof

Technical Field

The application belongs to the technical field of aircraft structural design, and particularly relates to an aircraft folding rudder and a locking and unlocking device thereof.

Background

In order to meet the combat requirements of the external combat of modern war zones, the range requirements of the flying missiles are continuously improved. Meanwhile, the missile is limited by strict constraint of space envelope of the carrier, and the missile is required to reduce transverse length, adapt to a carrier platform and a launching device, and further improve carrying capacity of the carrier so as to have high-density striking capacity. The requirements of long range and small volume make the fight weapon increasingly adopt the layout mode of folding rudder, and the rudder surface can be rapidly unfolded after the missile is put in.

According to the technical search, the Chinese patent publication number is CN114199083A, and a missile folding rudder self-locking system is disclosed, and comprises an inner rudder, an outer rudder, a driving mechanism, a locking pin mechanism and the like, wherein the inner rudder and the outer rudder are in driving connection through the driving mechanism, and after the inner rudder and the outer rudder are unfolded in place, the end part of a locking rod is embedded into a locking pin hole of the outer rudder, so that the folding rudder is locked. However, the adopted technology has the following defects that the root of the rudder in the folding rudder needs enough thickness space to install the lock pin, and the aerodynamic resistance of the control surface can be obviously increased. The structure is complex, and the lock pin mechanism needs to be additionally provided with limiting mechanisms such as a shearing screw rod and the like.

The box-type launched missile is usually restrained by a box wall, the folded rudder is unfolded under the action of an unfolding mechanism when the missile exits from the box, and the airborne pylon type launched missile also needs to design a special folded rudder locking and unlocking device. According to the prior art, the Chinese patent publication number is CN113624074A, which discloses a missile folding rudder locking and unlocking device, comprising a missile body, a locking mechanism and a rudder support, wherein after the missile is launched, the missile needs to be unlocked by deflecting the control surface to be separated from the locking mechanism. The deflection of the control surface can enable the missile to generate initial disturbance moment to influence the initial flight attitude of the missile. Meanwhile, the locking mechanism can be reserved at the tail part of the missile body, so that aerodynamic resistance of the missile is increased, and flying performance of the missile is affected.

Therefore, development of an aircraft folding rudder and a locking and unlocking device thereof, which are simpler in structure, good in aerodynamic performance and small in influence of unlocking and unfolding on the flight attitude of the aircraft, is needed to be developed.

Disclosure of Invention

Aiming at the defects or improvement demands of the prior art, the application provides the folding rudder of the aircraft and the locking and unlocking device thereof, which have the advantages of simple mechanism composition, reliable functions and convenient installation, debugging and service processing, and thus, the technical problems of insufficient pneumatic performance of the folding rudder and the locking and unlocking device thereof and large interference of the unlocking and unfolding process on the flight attitude of the aircraft in the prior art are solved.

In order to achieve the above purpose, the technical scheme adopted by the application is as follows:

an aircraft folding rudder comprises an outer rudder, an inner rudder, a locking pin mechanism and a driving mechanism;

one end of the bottom of the outer rudder is provided with a rotating shaft hole piece, and the other end of the bottom of the outer rudder is provided with a locking pin hole piece;

one end of the upper part of the inner rudder is provided with a mounting hole piece, and the other end of the upper part of the inner rudder is provided with a positioning hole piece;

after the outer rudder and the inner rudder are assembled, the positioning hole piece, the rotating shaft hole piece, the mounting hole piece and the locking pin hole piece are sequentially arranged and are positioned on the same rotating shaft line;

the locking pin mechanism is arranged in the locking pin hole piece and comprises a locking pin, a compression spring and a plug, one end of the compression spring is abutted against the locking pin, and the other end of the compression spring is abutted against the plug;

the driving mechanism comprises a sleeve shaft and a torsion bar, the sleeve shaft is inserted into the positioning hole piece, the rotating shaft hole piece, the mounting hole piece and the locking pin hole piece, a first structure is arranged at one end of the sleeve shaft and a second structure is arranged at one end of the locking pin to be mutually matched; the torsion bar sequentially passes through the sleeve shaft, the locking pin and the compression spring, one end of the torsion bar is fixed on the positioning hole piece through the sleeve shaft, and the other end of the torsion bar is fixed on the locking pin hole piece through the plug;

the outer rudder is rotatable about a quill.

Further, the sleeve shaft sequentially comprises a first cylindrical section, a square positioning section and a first structure; the middle part of the positioning hole piece is square and is matched with the square positioning section of the sleeve shaft, so that the positioning and bearing functions are realized. The first structure is a convex clip. The sleeve shaft adopts a multipurpose structural form, so that on one hand, the rotating support is provided for the inner rudder and the outer rudder, and on the other hand, a locking interface is provided for the locking pin.

Further, one end of the locking pin is provided with a second structure, and the other end of the locking pin is provided with a front guide section; the second structure is mutually matched with the first structure of the sleeve shaft, the front guide section extends into the compression spring, and the second structure is a clamping groove; the locking pins are only one group, the locking pins are arranged to be of a clamping groove structure instead of a clamping convex structure, and in a narrow space, rectangular keys are allowed to have longer sizes, so that the guiding fit clearance between the locking pins and an outer rudder can be further reduced, and the bearing capacity between the locking pins and the outer rudder is improved.

Preferably, the clamping protrusion and the clamping groove adopt taper design, and the clamping protrusion and the clamping groove are matched with each other to have a self-locking function, so that the locking mechanism is prevented from unlocking under the action of aerodynamic force.

Furthermore, two groups of symmetrical rectangular key grooves are formed in the lock pin hole piece, two groups of symmetrical rectangular keys are arranged on the lock pin, and the rectangular key grooves and the rectangular keys are mutually matched and installed.

Further, a U-shaped groove is formed in the lock pin hole piece, and when the sleeve shaft is assembled in the lock pin hole piece, the unlocking hole is aligned with the U-shaped groove.

Further, a limiting plate is arranged on the mounting hole piece.

Further, one end of the plug is provided with a rear guide section, and the other end of the plug is provided with a straight slot; the rear guide section extends into the compression spring.

Further, the lock pin hole piece is provided with a threaded hole, the blocking and torsion bar are respectively provided with a blocking round hole and a torsion bar round hole, the positions of the threaded hole, the blocking round hole and the torsion bar round hole are corresponding, the outer rudder is provided with a tightening screw, and the tightening screw passes through the threaded hole, the blocking round hole and the torsion bar round hole to fix the lock pin hole piece, the blocking and the torsion bar at the same time.

Further, the torsion bar is one or more torsion bars with rectangular cross section. The torsion bars with rectangular cross sections can be used in a combined mode, and have the characteristics of simple structure, high material utilization rate and large driving force. Compared with other elastic elements such as springs, torsion springs and the like, the novel spring has the advantages of light weight, simple structure, large torque and the like. Under the condition of meeting the unfolding time, the unfolding process has small impact force on the aircraft.

Based on the same technical conception, the application also provides a locking and unlocking device of the aircraft folding rudder, which comprises grid wings, a limiting rod and a separating mechanism;

the aircraft comprises a servo cabin shell, the folding rudder of the aircraft is arranged on the peripheral side of the servo cabin shell, the grid wings are arranged at the tail part of the servo cabin shell through a separating mechanism, the limiting rods are arranged on the grid wings, and the extending parts of the limiting rods restrict the outer rudder in a folded state.

Further, the separation mechanism is an explosion bolt.

Compared with the prior art, the following beneficial effects can be achieved through the technical scheme of the application:

1. the folding rudder driving mechanism and the locking mechanism are arranged on the same rotating shaft, so that the protruding structure of the outer surface of the folding rudder is reduced or the overall thickness of the control surface is reduced, and the aerodynamic performance of the aircraft is improved.

2. The position of the folding rudder rotating shaft can be arranged at the root of the control surface as far as possible, and a larger expanding aerodynamic lifting surface is allowed under the condition of the same envelope size.

3. The compression state of the locking pin is limited by the front end surface of the sleeve, and the compression of the locking pin is gradually released in the process of expanding the control surface, so that the mechanisms such as a shearing screw rod, an unlocking baffle plate and the like do not need to be additionally arranged.

4. All the folding control surfaces are restrained by the same locking and unlocking device, so that the number of the locking and unlocking devices is reduced, and the unfolding synchronization performance of the control wings is improved.

5. The constraint release of the folding rudder wings is realized through the separation of the locking and unlocking device, the locking mechanism is not required to be separated through the deflection of the rudder surface, and no additional protruding structure exists after the separation. The aerodynamic resistance of the aircraft is reduced, and the influence of the unlocking and unfolding process of the folding rudder on the flight attitude of the aircraft is small.

6. The application has simple and compact structure, is easy to realize the manual or automatic unfolding and locking of the folding rudder, is convenient to install, debug and service treatment, and is especially suitable for the transverse folding rudder wings of small and medium-sized aircrafts.

Drawings

FIG. 1 is an exploded view of a folding rudder in an embodiment of the application;

FIG. 2 is a partial cross-sectional view of a front view of a folded rudder in an embodiment of the application;

FIG. 3 is a schematic view of a locked state of a folding rudder actuation and locking mechanism in an embodiment of the application;

FIG. 4 is a schematic illustration of an unlocked state of a folding rudder drive and locking mechanism in an embodiment of the application;

fig. 5 is an isometric view of a folded rudder in an embodiment of the application;

fig. 6 is a bottom view of a folded rudder in an embodiment of the application.

The same reference numbers are used throughout the drawings to reference like elements or structures, wherein:

1. an outer rudder; 1a, a rotating shaft hole piece (a rotating shaft hole 1a1 is arranged in the rotating shaft hole piece); 1b, a lock pin hole piece (a rotating shaft hole 1b1 is arranged in the lock pin hole piece); 1c, rectangular key grooves; 1d, U-shaped grooves; 1e, a threaded hole; 2. an inner rudder; 2a, a mounting hole piece (a mounting hole 2a1 is arranged in the mounting hole piece); 2b, positioning hole pieces (positioning holes 2b1 are arranged in the positioning hole pieces); 2c, limiting plates; 3. a quill; 3a, a first cylindrical section; 3b, square positioning structure; 3c, a second cylindrical section; 3d, clamping the convex; 3e, positioning surface; 4. a torsion bar; 4a, torsion bar round holes; 5. a locking pin; 5a, rectangular keys; 5b, a clamping groove; 5c, unlocking the hole; 5d, a front guide section; 6. a compression spring; 7. blocking; 7a, a rear guide section; 7b, a straight slot; 7c, blocking the round hole; 8. a cylindrical pin; 8a, a cylindrical hole; 9. a set screw; 10. tightening the screw; 11. folding a rudder; 12. grid wings; 13. a limit rod; 14. an explosive bolt; 15. a servo cabin housing.

Detailed Description

Embodiments of the present application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the application. On the contrary, the embodiments of the application include all alternatives, modifications and equivalents as may be included within the spirit and scope of the appended claims.

As shown in fig. 1-6, an aircraft folding rudder 11 comprises an outer rudder 1, an inner rudder 2, a locking pin mechanism and a driving mechanism.

One end of the bottom of the outer rudder 1 is provided with a rotating shaft hole piece 1a, and the other end is provided with a locking pin hole piece 1b;

one end of the upper part of the inner rudder 2 is provided with a mounting hole piece 2a, the other end is provided with a positioning hole piece 2b, one end of the positioning hole piece 2b is open, and the other end is closed; the bottom of the inner rudder 2 is provided with an interface connected with an output shaft of the electric steering engine;

after the outer rudder 1 and the inner rudder 2 are assembled, the positioning hole piece 2b, the rotating shaft hole piece 1a, the mounting hole piece 2a and the lock pin hole piece 1b are sequentially arranged and positioned on the same rotating shaft line;

the lock pin mechanism is arranged in a lock pin hole 1b1 in the lock pin hole piece 1b and comprises a lock pin 5, a compression spring 6 and a plug 7, wherein one end of the compression spring 6 is abutted against the lock pin 5, and the other end is abutted 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;

the driving mechanism comprises a sleeve shaft 3 and a torsion bar 4, wherein the sleeve shaft 3 is inserted into the positioning hole piece 2b, the rotating shaft hole piece 1a, the mounting hole piece 2a and the locking pin hole piece 1b to provide mounting support and rotation center for the inner rudder 2 and the outer rudder 1. A first structure is arranged at one end of the sleeve shaft 3 and is mutually matched with a second structure arranged at one end of the locking pin 5; the torsion bar 4 sequentially passes through the sleeve shaft 3, the locking pin 5 and the compression spring 6, one end of the torsion bar is fixed on the positioning hole piece 2b through the sleeve shaft 3, the other end of the torsion bar is fixed on the locking pin hole piece 1b through the plug 7, and the middle part of the torsion bar is a working section;

the outer rudder 1 can rotate around the sleeve shaft 3 to fold, so that the folding function of the outer rudder 1 relative to the inner rudder 2 is realized;

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

As shown in fig. 1, in some embodiments, the shaft hole member 1a is provided with a shaft hole 1a1, the lock pin hole member 1b is provided with a lock pin hole 1b1, the diameter of the lock pin hole 1b1 is larger than the diameter of the shaft hole 1a1, and the lock pin hole 1b1 is coaxial with the shaft hole 1a 1; two rectangular key grooves 1c which are vertically symmetrical are formed in the inner wall of the lock pin hole 1b1, two groups of rectangular keys 5a are vertically symmetrically arranged on the lock pin 5, and the rectangular keys 5a and the rectangular key grooves 1c are mutually matched and installed, so that the lock pin has the characteristics of high positioning and guiding precision and strong bearing capacity; u-shaped grooves 1d are formed in the left side and the right side of the lock pin hole piece 1b, threaded holes 1e are formed in the tail portion of the lock pin hole piece, and the threaded holes 1e are used for fixing the plug 7 and the torsion bar 4 in a matched mode through screw tightening screws 10.

As shown in fig. 1 and 6, in some embodiments, one end of the inner rudder 2 is provided with a mounting hole piece 2a, the other end is provided with a positioning hole piece 2b, a cylindrical mounting hole 2a1 is arranged in the mounting hole piece 2a, the positioning hole piece 2b is provided with a positioning hole 2b1, and the middle part of the positioning hole 2b1 is in a square structure; the locating hole spare 2b upper end is provided with limiting plate 2c, and limiting plate 2c is the hang plate, and outer rudder 1 expands back and takes place the collision spacing with limiting plate 2c in place, avoids outer rudder 1 to expand back in place and continues forward movement under inertial force effect, has improved outer rudder 1's expansion precision and expansion time. In the folded state of the outer rudder 1, the limiting plate 2c forms an included angle of 135 degrees with the plane of the outer rudder 1, see fig. 6.

As shown in fig. 1, 3, 4, in some embodiments, the drive mechanism includes a quill 3 and a torsion bar 4. The sleeve shaft 3 is of a concentric cylinder structure, a first cylinder section 3a is arranged at the outer end of the front part of the sleeve shaft 3, a square positioning structure 3b is arranged in the middle of the sleeve shaft, the square positioning structure 3b is used for being matched with the positioning hole 2b1, a second cylinder section 3c is arranged at the rear end of the sleeve shaft, a conical clamping protrusion 3d (a first structure) is arranged at the tail end of the sleeve shaft, and the conical clamping protrusion 3d can be matched with a clamping groove 5b (a second structure) on the locking pin 5 to lock the sleeve shaft.

Preferably, the sleeve shaft 3 and the locking pin 5 are both made of high-strength steel materials, which are the main bearing components of the rudder 11.

As shown in fig. 1 and 2, in some embodiments, the quill 3 is inserted into the locating hole piece 2b, the rotating shaft hole piece 1a, the mounting hole piece 2a and the lock pin hole piece 1b;

as shown in fig. 1, 3 and 4, in some embodiments, the square structure in the middle of the sleeve shaft 3 is installed in cooperation with the positioning hole 2b1 of the inner rudder 2, so that on one hand, the installation accuracy of the clamping protrusion 3d on the sleeve shaft 3 relative to the inner rudder 2 is ensured, and on the other hand, the pneumatic load borne by the outer rudder 1 is transmitted to the inner rudder 2 through the square structure.

As shown in fig. 1, 3, and 4, in some embodiments, a detent mechanism is provided within the detent bore 1b, including a detent pin 5, a compression spring 6, and a plug 7. The main body of the locking pin 5 is of a concentric cylinder structure, an unlocking hole 5c is formed in the main body, a clamping groove 5b (second structure) is formed in the front end of the locking pin 5, an unlocking hole 5c is formed in the middle of the locking pin, a front guide section 5d is arranged at the rear end of the locking pin, and when the locking pin 5 is assembled in the locking pin hole piece 1b, the unlocking hole 5c is aligned with the U-shaped groove 1 d.

The locking pins 5 are only one group, and are arranged on the locking pins in a clamping groove 5b structure instead of a clamping convex 3d structure, so that in a narrow space, the rectangular key 5a is allowed to have a longer size, the guiding fit clearance between the locking pins 5 and the outer rudder 1 can be further reduced, and the bearing capacity between the locking pins and the outer rudder 1 is improved. The upper clamping convex 3d and the clamping groove 5b of the sleeve shaft 3 adopt taper design, and the two are matched with each other to have a self-locking function, so that the locking mechanism is prevented from unlocking under the aerodynamic force.

As shown in fig. 1, 3 and 4, in some embodiments, the clamping groove 5b is mutually matched with the clamping protrusion 3d of the sleeve shaft 3, the front guiding 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 matching surface of the key groove is long, the matching gap between the outer rudder 1 and the locking pin 5 is reduced, the pneumatic load of the outer rudder 1 is borne through the rectangular key 5a, and the bearing performance is better.

The locking pin 5 is limited by the rear end face of the sleeve shaft 3 in a compressed state, and the compression of the locking pin 5 is gradually released in the process of expanding the outer rudder 1, so that additional mechanisms such as a shear pin, an unlocking baffle and the like are not required.

As shown in fig. 1, 3 and 4, 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 fixedly supported on the rear guide section 7a of the plug 7, and a plug round hole 7c is formed on one side of the plug 7 for driving power of the locking pin 5.

As shown in fig. 1 and 2, in some embodiments, the outer rudder 1, the inner rudder 2 and the quill 3 form a revolute pair, and the outer rudder 1 is rotatable and foldable about the quill 3.

In the embodiment of the application, as shown in fig. 2, the outer rudder 1 and the inner rudder 2 form an aerodynamic lifting surface, and the locking mechanism and the rotation axis of the outer rudder 1 are arranged on the same axis, so that the aerodynamic resistance of the control surface is reduced, and the aerodynamic performance of the aircraft is improved.

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

As shown in fig. 1, in some embodiments, one end of the torsion bar 4 is provided with a torsion bar round hole 4a, corresponding to the position of the threaded hole 1e on the locking pin 5 piece, a tightening screw 10 passes through the threaded hole 1e, the blocking round hole 7c and the torsion bar round hole 4a to fix the locking pin 5 piece, the blocking 7 and the torsion bar 4, meanwhile, the other end of the torsion bar 4 is provided with a cylindrical hole 8a, the sleeve shaft 3 is provided with a corresponding through hole, and the torsion bar 4 and the sleeve shaft 3 are fixed in a matched manner by inserting the cylindrical pin 8.

Two groups of fastening through holes are respectively formed in the first cylindrical section 3a and the square positioning structure 3b of the sleeve shaft 3, corresponding fastening screw holes are formed in the mounting hole piece 2a and the positioning hole piece 2b, the sleeve shaft 3 and the inner rudder 2 are fixed through inserting fastening screws 9, and axial displacement of the sleeve shaft 3 is limited.

In some embodiments, the torsion bar 4 is machined from NL-2 high strength steel, as shown in fig. 1, and is the source of power for the deployment of the rudder 1. The torsion bar 4 is a rectangular section torsion bar with a large length-width ratio, and is made of high-strength materials, the tensile strength is up to 2200Mpa, and the section size of the torsion bar 4 is reduced, so that the installation structure is more compact. Compared with torsion bars with round cross sections and small length-width ratio rectangular cross sections, the torsion bar with the large length-width ratio rectangular cross section has more uniform stress distribution and higher material utilization rate. In this embodiment, two sets of torsion bars with rectangular cross sections are used in combination. Compared with other elastic elements such as springs, torsion springs and the like, the novel spring has the advantages of light weight, simple structure, large torque and the like. Under the condition of meeting the unfolding time, the unfolding process has small impact force on the aircraft.

Based on the same technical conception, the application also provides a locking and unlocking device of the aircraft folding rudder 11, which comprises grid wings 12, a limiting rod 13 and a separating mechanism;

as shown in fig. 5 and 6, in some embodiments, the folding rudders 11 are mounted on the electric steering engine output shaft inside the aircraft servo cabin housing 15, and four sets of folding rudders 11 are arranged in an X-shape; the grid wings 12 are fixed at the tail end of the servo cabin shell 15 through two explosion bolts 14 (separating mechanisms), and the grid wings 12 play a role in stabilizing the attitude of the aircraft before the control surface is unfolded after the aircraft is thrown in; the limiting rods 13 are arranged on the grid wings 12, and the outer rudder 1 is limited by the limiting rods 13 in a folded state and cannot be unfolded.

After receiving the control system unlocking instruction, the explosion bolts 14 work to separate the grid wings 12 and the limit rods 13 mounted on the grid wings 12 together, so that the restraint on the outer rudder 1 is released. After the locking and unlocking device is separated, the outer surface of the servo cabin shell 15 does not have any redundant protrusions, and the aerodynamic performance of the aircraft is good.

The outer rudders 1 are restrained by the same locking and unlocking device, so that the number of the locking and unlocking devices is reduced, and the unfolding synchronization performance of the rudder wings is improved.

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

the folding rudder 11 mounting process: the torsion bar 4 penetrates into the sleeve shaft 3 and is matched and fixed with the sleeve shaft 3 through the cylindrical pin 8; the lower part of the outer rudder 1 is matched with the upper part of the inner rudder 2, the positioning hole piece 2b, the rotating shaft hole piece 1a, the mounting hole piece 2a and the lock pin hole piece 1b are sequentially butted, the axes are aligned, a sleeve shaft 3 assembly provided with a torsion bar 4 is penetrated through the lock pin hole piece 1b until a positioning surface 3e of the sleeve shaft 3 is contacted with the closed end of the positioning hole piece 2b, and four set 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 sequentially penetrate through the torsion bar 4 and are installed in the locking pin hole 1b1 of the outer rudder 1, when the locking pin 5 is assembled in the locking pin hole piece 1b, the unlocking hole 5c is aligned with the U-shaped groove 1d, and at the moment, the clamping groove 5b of the locking pin 5 and the clamping convex 3d of the sleeve shaft 3 are mutually embedded and locked, and the locking device is shown in fig. 3; and finally, the plug 7 is rotated by a certain angle through the straight slot 7b at the rear end of the plug 7, the round hole of the plug 7 and the round hole 4a of the torsion bar are aligned with the threaded hole 1e at the rear end of the outer rudder 1, the three are fixed at the same time by screwing the screw 10, and the setting position of the threaded hole 1e in the circumferential direction of the locking pin hole piece 1b determines the rotation angle of the torsion bar 4, so that the initial pretightening moment of the torsion bar 4 can be controlled.

The folding rudder 11 unlocking and locking device restraining process: the tool is used for poking the unlocking hole 5c on the locking pin 5 through the U-shaped groove 1d at the outer rudder 1 to push the locking pin 5 to the direction of the compression spring 6 (the compression amount of the compression spring 6 is larger than the length of the clamping groove 5 b), so that the clamping groove 5b of the locking pin 5 is withdrawn from the clamping protrusion 3d on the sleeve shaft 3, and then the outer rudder 1 is manually folded to the locking position. The limit rods 13 are mounted to the corresponding positions of the grid wings 12. At this time, the outer rudder 1 is restrained in a folded state by the limiting rod 13, the torsion bar 4 is elastically deformed by torsion, elastic potential energy is stored, the locking pin 5 rotates together with the outer rudder 1, and finally, the locking pin is limited by the end face of the sleeve shaft 3, see fig. 4.

After the control system sends an unlocking instruction, the explosion bolts 14 work to separate the grid wings 12 and the limiting rods 13 arranged on the grid wings 12, and the four groups of outer rudders 1 start to be unfolded synchronously, so that the unfolding synchronism is good. During the deployment of the rudder 1, the locking mechanism is brought into synchronous rotation, and at the same time the locking pin 5 starts to move along the axis of rotation in the direction of the quill 3 under the action of the compression spring 6. After the outer rudder 1 is unfolded in place, the outer rudder 1 collides with the limiting plate 2c to be limited, so that the outer rudder 1 is prevented from continuing to move forwards under the action of inertia force after being unfolded in place, and 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 torque in the unfolding direction. After the outer rudder 1 and the inner rudder 2 are unfolded in place, the locking pin 5 is pushed by a spring, the clamping groove 5b of the locking pin is embedded into the clamping protrusion 3d at the rear end of the sleeve shaft 3, reliable locking of the inner rudder 2 and the outer rudder 1 is achieved, and the locking pin has a self-locking function and provides aerodynamic lift for an aircraft.

In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.

The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.

Claims

1. The folding rudder of the aircraft is characterized by comprising an outer rudder, an inner rudder, a locking pin mechanism and a driving mechanism;

the driving mechanism comprises a sleeve shaft and a torsion bar, the sleeve shaft is inserted into the positioning hole piece, the rotating shaft hole piece, the mounting hole piece and the locking pin hole piece, and a first structure is arranged at one end of the sleeve shaft and is mutually matched with a second structure arranged at one end of the locking pin; the torsion bar sequentially passes through the sleeve shaft, the locking pin and the compression spring, one end of the torsion bar is fixed on the positioning hole piece through the sleeve shaft, and the other end of the torsion bar is fixed on the locking pin hole piece through the plug;

the outer rudder is rotatable about a quill.

2. An aircraft rudder according to claim 1 wherein the quill comprises, in order, a first cylindrical section, a square locating section, a first structure; the middle part of the positioning hole piece is square and is matched with the square positioning section of the sleeve shaft, and the first structure is a clamping protrusion.

3. An aircraft rudder according to claim 2, wherein the locking pin has a second structure at one end and a front guide section at the other end; the second structure is mutually engaged with the first structure of the quill, and the front guide section extends into the compression spring; the second structure is a clamping groove.

4. The aircraft folding rudder of claim 1, wherein two sets of symmetrical rectangular key slots are provided in the locking pin hole member, and wherein two sets of symmetrical rectangular keys are provided on the locking pin, and wherein the rectangular key slots and the rectangular keys are cooperatively mounted.

5. An aircraft rudder according to claim 2 wherein the quill is provided with an unlocking hole and the locking pin aperture is provided with a U-shaped slot, the unlocking hole being aligned with the U-shaped slot when the quill is fitted within the locking pin aperture.

6. An aircraft rudder according to claim 1 wherein the mounting hole member is provided with a stop plate.

7. An aircraft folding rudder according to claim 3, wherein one end of the plug is provided with a rear guide section and the other end is provided with a straight slot; the rear guide section extends into the compression spring.

8. An aircraft rudder according to claim 1, wherein the torsion bar is one or more rectangular section torsion bars.

9. The locking and unlocking device of the folding rudder of the aircraft according to any one of claims 1 to 8, comprising a grid wing, a limit lever and a separation mechanism;

10. The lock-unlocking device according to claim 9, wherein the separation mechanism is an explosive bolt.