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

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

An aircraft folding rudder and its locking and unlocking device

technical field

The invention belongs to the technical field of aircraft structure design, and in particular relates to an aircraft folding rudder and a locking and unlocking device thereof.

Background technique

In order to meet the operational requirements of standoff strikes in modern warfare, the range requirements of flying missiles are constantly increasing. At the same time, the missile is limited by the strict constraints of the space envelope of the carrier aircraft, and requires the missile to reduce its lateral length and adapt to the carrier platform and launching device, which can further increase the carrying capacity of the carrier aircraft to have high-density strike capability. The requirements of long range and small size make more and more combat weapons adopt the layout of folding rudders, and the rudder surface can be quickly unfolded after the missile is launched.

After searching the existing technology, it is found that the Chinese invention patent publication number is CN114199083A, which discloses a missile folding rudder self-locking system, including an inner rudder, an outer rudder, a driving mechanism and a locking mechanism, etc. The inner rudder and the outer rudder are driven by the driving mechanism After being connected and unfolded in place, the end of the locking rod is partially embedded in the locking pin hole of the outer rudder to realize the locking of the folding rudder. However, the above-mentioned technology has the following disadvantages. The inner rudder root of the folding rudder needs enough thickness space to install the lock pin, which will significantly increase the aerodynamic resistance of the rudder surface. The structure is complex, and the lock pin mechanism needs to be additionally provided with a limit mechanism such as a shear screw.

Box-launched missiles are usually constrained by the box wall to fold the rudder, and the folded rudder is deployed under the action of the unfolding mechanism when the missile is out of the box, while the airborne pylon-launched missile also needs to design a special folding rudder locking and unlocking device. According to the prior art search, the Chinese invention patent publication number is CN113624074A, which discloses a missile folding rudder locking and unlocking device, which includes a projectile body, a locking mechanism and a rudder support. The tight mechanism is unlocked. The deflection of the rudder surface will cause the initial disturbance moment of the missile, which will affect the initial flight attitude of the missile. At the same time, the locking mechanism will remain at the tail of the missile body, which will increase the aerodynamic resistance of the missile and affect the flight performance of the missile.

Therefore, it is urgent to develop an aircraft folding rudder and its locking and unlocking device with simpler structure, better aerodynamic performance, and less influence of unlocking and deployment on the flight attitude of the aircraft.

Contents of the invention

Aiming at the above defects or improvement needs of the prior art, the present invention provides an aircraft folding rudder and its locking and unlocking device. The aerodynamic performance of its locking and unlocking device is insufficient, and the unlocking and deployment process greatly interferes with the flight attitude of the aircraft.

To achieve the above object, the technical scheme adopted in the present invention is as follows:

A folding rudder for an aircraft, comprising 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, and the other end is provided with a lock pin hole;

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

After the outer rudder and the inner rudder are assembled, the positioning hole, the shaft hole, the installation hole, and the lock pin hole are arranged in sequence and are located on the same axis of rotation;

The lock pin mechanism is arranged in the lock pin hole and includes a lock pin, a compression spring and a plug, one end of the compression spring abuts against the lock pin, and the other end abuts against the plug;

The drive mechanism includes a quill and a torsion bar. The quill is inserted into the positioning hole, the shaft hole, the installation hole and the lock pin hole. One end of the quill is provided with a first structure and the lock. The second structure provided at one end of the tight pin fits with each other; the torsion bar passes through the sleeve shaft, locking pin, and compression spring in turn, one end is fixed on the positioning hole through the sleeve shaft, and the other end is fixed on the lock pin through a plug on the hole;

The outer rudder can be rotated and folded around the sleeve axis.

Further, the sleeve shaft includes a first cylindrical section, a square positioning section, and a first structure in sequence; the middle part of the positioning hole is square, which cooperates with the square positioning section of the sleeve shaft to play the role of positioning and bearing . The first structure is a protrusion. The quill shaft adopts a multi-purpose structure, on the one hand, it provides rotational support for the inner and outer rudders, and on the other hand, it provides a locking interface for the locking pin.

Further, one end of the locking pin is provided with a second structure, and the other end is provided with a front guide section; the second structure fits with the first structure of the sleeve shaft, and the front guide section extends into the compression spring, The second structure is a card slot; the locking pin is only one set, and it is set as a card slot structure instead of a card convex structure. In a narrow space, the rectangular key is allowed to have a longer size, which can further reduce the locking The guide fit clearance between the pin and the outer rudder improves the bearing capacity between the two.

Preferably, the card protrusion and the card slot adopt a tapered design, and the cooperation of the two has a self-locking function, preventing the locking mechanism from being unlocked under the action of pneumatic force.

Further, two sets of symmetrical rectangular key grooves are arranged in the locking pin hole, two sets of symmetrical rectangular keys are arranged on the locking pin, and the rectangular key grooves and the rectangular keys are installed in cooperation with each other.

Further, a U-shaped groove is provided on the lock pin hole, and when the sleeve shaft is assembled in the lock pin hole, the unlocking hole and the U-shaped groove are aligned.

Further, a limiting plate is provided on the mounting hole.

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

Further, the lock pin hole is provided with a threaded hole, and the plugging and torsion bar are respectively provided with a plugging round hole and a torsion bar round hole. The positions of the threaded hole, the plugging 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 plugging round hole and the torsion bar round hole to fix the locking pin hole, the plugging and the torsion bar simultaneously.

Further, the torsion bar is one or more torsion bars with rectangular section. The rectangular section torsion bar can be used in combination in multiple groups, and has the characteristics of simple structure, high material utilization rate and large driving force. Compared with other elastic elements such as springs and torsion springs, it has the advantages of light weight, simple structure, and large torque. Under the conditions of satisfying the deployment time, the deployment process has little impact on the aircraft itself.

Based on the same technical idea, the present invention also provides a locking and unlocking device for the folding rudder of the above-mentioned aircraft, which includes a grid wing, a limit lever and a separation mechanism;

The aircraft includes a servo cabin housing, the aircraft folding rudder is installed on the peripheral side of the servo cabin housing, the grid wing is installed at the tail of the servo cabin housing through a separation mechanism, and the limit rod is installed on the grille. On the grid wing, the extension of the limit rod constrains the outer rudder in the folded state.

Further, the separation mechanism is an explosive bolt.

Compared with the prior art, the above technical solution conceived by the present invention can achieve the following beneficial effects:

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

2. The position of the folding rudder shaft can be arranged as far as possible at the root of the rudder surface. Under the same envelope size, a larger aerodynamic lift surface is allowed.

3. The compression state of the locking pin is limited by the front end of the sleeve. During the unfolding process of the rudder surface, the compression of the locking pin is gradually released, and no additional mechanisms such as shearing screw and unlocking block are required.

4. All folding rudder surfaces are constrained by the same locking and unlocking device, which reduces the number of locking and unlocking devices and improves the synchronization performance of the rudder wing deployment.

5. The release of the restraint of the folded rudder wing is achieved by separating the locking and unlocking device, without the need to deflect the rudder surface to break away from the locking mechanism, and there is no additional protruding structure after separation. The aerodynamic resistance of the aircraft is reduced, and the process of unlocking and unfolding the folding rudder has little influence on the flight attitude of the aircraft.

6. The structure of the present invention is simple and compact, it is easy to realize the manual or automatic unfolding and locking of the folding rudder, and the installation, commissioning and service processing are convenient, and it is especially suitable for the horizontal folding rudder wings of small and medium-sized aircraft.

Description of drawings

Fig. 1 is an exploded schematic diagram of a folding rudder in an embodiment of the present invention;

Fig. 2 is a partial sectional view of the front view of the folding rudder in the embodiment of the present invention;

Fig. 3 is a schematic diagram of the folding rudder driving and locking mechanism locking state in the embodiment of the present invention;

Fig. 4 is a schematic diagram of the folding rudder drive and the unlocking state of the locking mechanism in the embodiment of the present invention;

Fig. 5 is the isometric view of folding rudder in the embodiment of the present invention;

Fig. 6 is a bottom view of the folding rudder in the embodiment of the present invention.

Throughout the drawings, the same reference numerals are used to designate the same elements or structures, wherein:

1. Outer rudder; 1a, shaft hole (with shaft hole 1a1 inside); 1b, lock pin hole (with shaft hole 1b1 inside); 1c, rectangular keyway; 1d, U-shaped slot; 1e, threaded hole; 2. Inner rudder; 2a. Mounting hole (with mounting hole 2a1 inside); 2b. Positioning hole (with positioning hole 2b1 inside); 2c. Limiting plate; 3. Sleeve shaft; 3a. First cylinder 3b, square positioning structure; 3c, second cylindrical section; 3d, card convex; 3e, positioning surface; 4, torsion bar; 4a, torsion bar round hole; 5, locking pin; 5a, rectangular key; 5b, Card slot; 5c, unlocking hole; 5d, front guide section; 6, compression spring; 7, block; 7a, rear guide section; 7b, slot; 7c, block hole; 8, cylindrical pin; 8a, cylindrical hole 9, set screw; 10, tightening screw; 11, folding rudder; 12, grid wing; 13, limit rod; 14, explosion bolt; 15, servo cabin shell.

Detailed ways

Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary, are only for explaining the present application, and should not be construed as limiting the present application. On the contrary, the embodiments of the present invention include all changes, modifications and equivalents falling within the spirit and scope of the appended claims.

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

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

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

After the outer rudder 1 and the inner rudder 2 are assembled, the positioning hole 2b, the shaft hole 1a, the installation hole 2a, and the locking pin hole 1b are arranged in sequence and are located on the same rotation axis;

The lock pin mechanism is arranged in the lock pin hole 1b1 in the lock pin hole part 1b, and includes a lock pin 5, a compression spring 6 and a plug 7. One end of the compression spring 6 abuts against the lock 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 ;

The driving mechanism includes a quill 3 and a torsion bar 4. The quill 3 is inserted into the positioning hole 2b, the rotating shaft hole 1a, the installation hole 2a and the lock pin hole 1b to provide installation for the inner rudder 2 and the outer rudder 1. Support and center of rotation. One end of the sleeve shaft 3 is provided with a first structure and the second structure provided at one end of the locking pin 5 fits each other; the torsion bar 4 passes through the sleeve shaft 3, the locking pin 5, and the compression spring 6 in turn, and one end passes through the sleeve The cylinder shaft 3 is fixed on the positioning hole 2b, and the other end is fixed on the lock pin hole 1b through the plug 7, and the middle part is the working section;

The outer rudder 1 can be rotated and folded around the sleeve shaft 3 to realize the folding function of the outer rudder 1 relative to the inner rudder 2;

The locking and unlocking device of the foldable rudder 11 of the aircraft is arranged at the rear end of the aircraft servo cabin casing 15; the outer rudder 1 is limited by the locking and unlocking device in the folded state.

As shown in Figure 1, in some embodiments, the shaft hole 1a is provided with a shaft hole 1a1, the lock pin hole 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 1a1; the inner wall of the lock pin hole 1b1 is provided with two vertically symmetrical rectangular key grooves 1c, and the locking pin 5 is arranged vertically symmetrically with two groups of rectangular keys 5a. It has the characteristics of high positioning and guiding precision and strong bearing capacity; the left and right sides of the lock pin hole 1b are provided with U-shaped grooves 1d, and the tail is provided with threaded holes 1e. fixed.

As shown in Figure 1 and Figure 6, in some embodiments, one end of the inner rudder 2 is provided with a mounting hole 2a, and the other end is provided with a positioning hole 2b, and the inside of the mounting hole 2a is provided with a cylindrical mounting hole 2a1, and the positioning hole The part 2b is provided with a positioning hole 2b1, and the middle part of the positioning hole 2b1 is a square structure; the upper end of the positioning hole part 2b is provided with a limit plate 2c, the limit plate 2c is an inclined plate, and the outer rudder 1 collides with the limit plate 2c to limit the position , to prevent the outer rudder 1 from continuing to move forward under the action of inertial force after the outer rudder 1 is deployed in place, and improve the deployment accuracy and deployment time of the outer rudder 1 . In the folded state of the outer rudder 1, the limiting plate 2c forms an included angle of 135° with the plane of the outer rudder 1, see FIG. 6 .

As shown in FIG. 1 , FIG. 3 , and FIG. 4 , in some embodiments, the driving mechanism includes a quill 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, and the middle part is provided with a square positioning structure 3b. The square positioning structure 3b is used to cooperate with the positioning hole 2b1. The two cylindrical sections 3c are provided with a tapered locking protrusion 3d (first structure) at the end, and the tapered locking protrusion 3d can fit with the locking groove 5b (second structure) on the locking pin 5 for locking.

Preferably, both the quill 3 and the locking pin 5 are made of high-strength steel, which are the main load-bearing components of the folding rudder 11 .

As shown in Figures 1 and 2, in some embodiments, the sleeve shaft 3 is inserted into the positioning hole 2b, the shaft hole 1a, the installation hole 2a, and the lock pin hole 1b;

As shown in Figure 1, Figure 3, and Figure 4, in some embodiments, the square structure in the middle of the quill 3 is installed in cooperation with the positioning hole 2b1 of the inner rudder 2. 2, on the other hand, the aerodynamic load borne by the outer rudder 1 is transmitted to the inner rudder 2 through the square structure.

As shown in FIG. 1 , FIG. 3 , and FIG. 4 , in some embodiments, the locking mechanism is disposed in the locking hole 1 b, including a locking pin 5 , a compression spring 6 and a stopper 7 . The main body of the locking pin 5 is a concentric cylindrical structure, and an unlocking hole 5c is provided. The front end of the locking pin 5 is provided with a card slot 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 pin 5 is assembled in the lock pin hole 1b, the unlocking hole 5c is aligned with the U-shaped groove 1d.

The locking pin 5 is only one set, and it is provided with a slot 5b structure instead of a convex 3d structure. In a narrow space, the rectangular key 5a is allowed to have a longer size, which can further reduce the locking pin 5 and the outer rudder. 1 guide fit clearance, improve the carrying capacity between the two. The locking protrusion 3d and the locking groove 5b on the sleeve shaft 3 adopt a tapered design, and the cooperation of the two has a self-locking function to prevent the locking mechanism from being unlocked under the action of pneumatic force.

As shown in Figure 1, Figure 3 and Figure 4, in some embodiments, the locking groove 5b and the locking protrusion 3d of the quill shaft 3 fit each other, and the front guide section 5d of the locking pin 5 extends into the compression spring 6, locking The pin 5 cooperates with the rectangular keyway 1c in the locking pin hole 1b1 of the outer rudder 1 through the rectangular key 5a, the mating surface of the keyway is long, which reduces the matching gap between the outer rudder 1 and the locking pin 5, and bears the aerodynamic force of the outer rudder 1 through the rectangular key 5a. Load, bearing performance is better.

The locking pin 5 is limited by the rear end surface of the sleeve shaft 3 in the compressed state, and the compression on the locking pin 5 is gradually released during the unfolding process of the outer rudder 1, without additional mechanisms such as a shear pin and an unlocking block.

As shown in Figure 1, Figure 3 and Figure 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, for The driving energy of locking pin 5, one side of blocking 7 is provided with blocking circular hole 7c.

As shown in FIG. 1 and FIG. 2 , in some embodiments, the outer rudder 1 , the inner rudder 2 and the sleeve shaft 3 form a rotating pair, and the outer rudder 1 can rotate and fold around the sleeve shaft 3 .

As shown in Figure 2, in the embodiment of the present invention, the outer rudder 1 and the inner rudder 2 constitute an aerodynamic lift surface, and the locking mechanism and the rotation axis of the outer rudder 1 are arranged on the same axis to reduce the aerodynamic resistance of the rudder surface and improve the aircraft aerodynamic performance.

The torsion bar 4 passes through the sleeve shaft 3, the locking pin 5, and the compression spring 6 in turn, and one end is fixed on the positioning hole 2b through the sleeve shaft 3, and the other end is fixed on the lock pin hole 1b through the plug 7, and the middle part For the working section, the torsion bar 4 adopts a structure with a large aspect ratio and a rectangular cross section, so that the force distribution is more uniform and the material utilization rate is higher.

As shown in Figure 1, in some embodiments, one end of the torsion bar 4 is provided with a torsion bar circular hole 4a, which corresponds to the position of the threaded hole 1e on the locking pin 5, and the tightening screw 10 passes through the threaded hole 1e, The plugging round hole 7c and the torsion bar round hole 4a fix the locking pin 5, the plugging 7 and the torsion bar 4. Meanwhile, 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 The through hole of the torsion bar 4 and the sleeve shaft 3 are fixed by inserting the cylindrical pin 8.

The first cylindrical section 3a of the sleeve shaft 3 and the square positioning structure 3b are respectively provided with two sets of fastening through holes, and the mounting hole 2a and the positioning hole 2b are provided with corresponding fastening screw holes. The sleeve shaft 3 is fixed with the inner rudder 2 to limit the axial displacement of the sleeve shaft 3 .

As shown in FIG. 1 , in some embodiments, the torsion bar 4 is made of NL-2 high-strength steel, and is the power source for deploying the outer rudder 1 . The torsion bar 4 is a large aspect ratio rectangular section torsion bar, which is made of high-strength materials, and the tensile strength is as high as 2200Mpa, which reduces the section size of the torsion bar 4 and makes its installation structure more compact. Compared with the torsion bar with circular section and rectangular section with small aspect ratio, the torsion bar with large aspect ratio rectangular section has more uniform stress distribution and higher material utilization rate. In this embodiment, two groups of torsion bars with rectangular cross sections are used in combination. Compared with other elastic elements such as springs and torsion springs, it has the advantages of light weight, simple structure, and large torque. Under the conditions of satisfying the deployment time, the deployment process has little impact on the aircraft itself.

Based on the same technical idea, the present invention also provides a locking and unlocking device for the folding rudder 11 of the above-mentioned aircraft, including a grid wing 12, a limit lever 13 and a separation mechanism;

As shown in Fig. 5 and Fig. 6, in some embodiments, the folding rudder 11 is installed on the output shaft of the electric steering gear inside the aircraft servo cabin housing 15, and four groups of folding rudders 11 are arranged in an X shape; the grid wings 12 pass through Two explosive bolts 14 (separation mechanism) are fixed on the end of the servo cabin housing 15. Before the rudder surface is deployed after the aircraft is launched, the grid wing 12 plays a role in stabilizing the attitude of the aircraft; the limit rod 13 is arranged on the grid wing 12, the outer rudder 1 is limited by the stop rod 13 in the folded state and cannot be launched.

After receiving the control system unlocking command, the explosive bolt 14 works to separate the grid wing 12 and the limit rod 13 installed on the grid wing 12 together, and releases the restraint of the outer rudder 1 . After the locking and unlocking device is separated, there is no redundant protrusion on the outer surface of the servo cabin shell 15, and the aerodynamic performance of the aircraft is good.

A plurality of outer rudders 1 are constrained by the same locking and unlocking device, which reduces the number of locking and unlocking devices and improves the synchronization performance of the rudder wings.

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

The installation process of folding rudder 11: insert the torsion bar 4 into the inside of the sleeve shaft 3, and fix it with the sleeve shaft 3 through the cylindrical pin 8; cooperate and install the lower part of the outer rudder 1 and the upper part of the inner rudder 2, press the positioning hole 2b, Shaft hole 1a, installation hole 2a, lock pin hole 1b are butted in sequence, and the axes are aligned, and the quill 3 assembly equipped with torsion bar 4 is inserted through the lock pin hole 1b until the quill 3 The positioning surface 3e is in contact with the closed end of the positioning hole 2b, and the four set screws 9 are fixed to limit the axial displacement of the sleeve shaft 3; In the locking pin hole 1b1 of the outer rudder 1, when the locking pin 5 is assembled in the locking pin hole 1b, the unlocking hole 5c is aligned with the U-shaped groove 1d, and at this time the locking groove 5b of the locking pin 5 is aligned with the sleeve shaft 3 The card protrusions 3d are fitted and locked with each other, 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, and the round hole of the plug 7 and the round hole 4a of the torsion bar are connected with the threaded hole 1e at the rear end of the outer rudder 1 Align, tighten the screw 10 to fix the three at the same time, the opening position of the threaded hole 1e in the circumferential direction of the lock pin hole 1b determines the rotation angle of the torsion bar 4, so that the initial pre-tightening torque of the torsion bar 4 can be controlled.

Folding rudder 11 unlocking and locking device restraint process: Borrow the tooling and move the unlocking hole 5c on the locking pin 5 through the U-shaped groove 1d of the outer rudder 1, and push the locking pin 5 in the direction of the compression spring 6 (compression spring 6 The amount of compression is greater than the length of the slot 5b), so that the locking pin 5 slot 5b withdraws from the protrusion 3d on the sleeve shaft 3, and then the outer rudder 1 is manually folded to the locked position. Install the limit rod 13 to the corresponding position of the grid wing 12. At this time, the limiting rod 13 constrains the outer rudder 1 in the folded state, the torsion bar 4 undergoes elastic deformation due to torsion, and stores elastic potential energy, and the locking pin 5 rotates together with the outer rudder 1, and is finally limited by the end surface of the sleeve shaft 3 , see Figure 4.

When the control system sends out the unlock command, the explosive bolt 14 works to separate the grid wing 12 and the limit rod 13 installed on the grid wing 12 together, and the four sets of outer rudders 1 start to deploy synchronously, and the deployment synchronization is good. During the unfolding process of the outer rudder 1, it will rotate synchronously with the locking mechanism. At the same time, the locking pin 5 starts to move toward the quill shaft 3 along the rotation axis under the action of the compression spring 6 . After the outer rudder 1 is deployed in place, it will collide with the limit plate 2c and be limited, so as to prevent the outer rudder 1 from continuing to move forward under the action of inertial force after the outer rudder 1 is deployed in place, and improve the deployment accuracy and deployment time of the outer rudder 1 . Under the action of the initial pretightening force of the torsion bar 4, the outer rudder 1 is always subjected to a torque in the deployment direction. After the outer rudder 1 and the inner rudder 2 are deployed in place, the locking pin 5 is pushed by the spring, and its locking groove 5b is embedded in the rear end of the sleeve shaft 3. The locking protrusion 3d realizes the reliable locking of the inner rudder 2 and the outer rudder 1, With self-locking function, it provides aerodynamic lift for the aircraft.

In the description of this application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", The orientation or positional relationship indicated by "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the application and simplifying the description, rather than indicating or implying the referred device Or elements must have a certain orientation, be constructed and operate in a certain orientation, and thus should not be construed as limiting the application.

Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. In the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims (10)

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;

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, 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;

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.

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