Folding control surface combined movement mechanism

Abstract

The invention relates to the technical field of aircraft flight control equipment, and provides a folding control surface combined movement mechanism which comprises a mounting support, a driving mechanism, a bevel gear mechanism, a locking device and a control surface mechanism, the driving mechanism and the bevel gear mechanism are both arranged on the mounting support, the bevel gear mechanism is connected with the control surface mechanism, and the locking device is connected with the bevel gear mechanism. The driving mechanism is configured to drive the bevel gear mechanism to drive the control surface mechanism to synchronously rotate to the driving mechanism and then drive the control surface mechanism to rotate around the center line of the control surface mechanism; the locking device is configured to lock the control surface mechanism to limit rotation of the control surface mechanism when the control surface mechanism does not rotate around the center line of the control surface mechanism. A special control surface unfolding mechanism is not needed, the structure is simple and compact, position locking is reliable, and the motion is stable in the control surface unfolding process.

Description

Technical Field

[0001] This invention relates to the technical field of aircraft flight control equipment, and in particular to a folding control surface combined motion mechanism. Background Technology

[0002] Control surfaces are components of a missile's flight control system, typically mounted at the tail of the missile. They utilize the aerodynamic drag generated by their deflection to maneuver the missile, and are also known as control surfaces. Foldable control surfaces are a common structure for missile control surfaces, primarily used in missiles requiring canister-mounted, tube-mounted, or internal weapons bays. This reduces their overall size, facilitates storage and transportation, saves installation space, and increases missile capacity. When the missile is in storage or transport, the foldable control surfaces can be folded to reduce its volume. When the missile needs to operate during flight, the folding mechanism unfolds the control surfaces, restoring them to their normal operating state.

[0003] Existing folding control surfaces require a separate folding and unfolding mechanism. Once the missile control surfaces are unfolded, a separate servo drive system activates. This system typically consists of a motor, transmission, and control system, driving the control surfaces to deflect around their axis. By adjusting the control surface position, the aerodynamic direction is changed, achieving missile flight attitude control. The folding and unfolding mechanism for folding control surfaces usually consists of connecting rods, hinges, locking devices, and drive components. The driving power is generally derived from springs or compressed air, and the control surface position is typically locked using a locking pin. For example, the longitudinal folding mechanism of the control surface disclosed in Chinese patent CN106225604B uses a spiral spring as the driving unit for the unfolding of the control surface. The pull pin and the positioning lock lock the two positions of the control surface respectively. The structure is complex and the reliability is poor. The control surface fixing and unfolding mechanism disclosed in Chinese patent CN113375511B has a groove on the side of the control surface. The folding position is fixed by the boss on the motor mounting plate. The locking is released by the deflection of the control surface. After the spring push head pushes open the control surface, it directly enters the locking hole to lock the control surface. Its disadvantage is that the deflection of the control surface during the unlocking process will affect the stability of the missile flight. At the same time, the mechanical structure is complex, and it is difficult for the control surface positioning device to enter the locking hole to lock. The reliability of operation is poor.

[0004] Therefore, there is an urgent need for those skilled in the art to design a foldable control surface combined motion mechanism that is simple in structure and can achieve both control surface deployment and control surface position during flight through a set of motion mechanisms. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention provides a foldable control surface combined motion mechanism, comprising a mounting bracket, a drive mechanism, a bevel gear mechanism, a locking device, and a control surface mechanism. The drive mechanism and the bevel gear mechanism are both mounted on the mounting bracket. The bevel gear mechanism is connected to the control surface mechanism. The drive mechanism is configured to drive the bevel gear mechanism to synchronously rotate the control surface mechanism to the drive mechanism, and then drive the control surface mechanism to rotate around its own centerline. The locking device is configured to lock the control surface mechanism and restrict its rotation when the control surface mechanism is not rotating around its own centerline.

[0006] Furthermore, the drive mechanism includes a motor bracket, a motor, a reducer, a drive shaft, and a first bevel gear. The reducer is fixed on the motor bracket, the motor is fixed at the rear end of the reducer, and the drive shaft is fixed on the output component of the reducer. The motor bracket is provided with a first through hole, and the drive shaft passes through the first through hole to connect with the first bevel gear.

[0007] Furthermore, the bevel gear mechanism includes a gear base, a rotary shaft, a rotary bearing, and a second bevel gear. The gear base is fixed on a mounting bracket, and the rotary shaft and rotary bearing are disposed inside the gear base. The rotary shaft and the inner ring of the rotary bearing are in transition fit. The rotary shaft is also connected to the second bevel gear, and the second bevel gear is provided with a first pull ring.

[0008] Furthermore, a circular boss is provided on the outer circular surface of the gear base. The circular boss has a first circular hole and a second circular hole inside. The first circular hole and the second circular hole are connected, and the first circular hole is located above the second circular hole. The diameter of the first circular hole is smaller than the diameter of the second circular hole, and the bottom of the inner ring of the second circular hole is provided with an internal thread.

[0009] Furthermore, the second bevel gear is an incomplete bevel gear, and the number of teeth of the incomplete bevel gear is an integer and satisfies:

[0010]

[0011] In the formula, Z0 is the number of teeth of the original complete bevel gear; Z is the number of teeth of the incomplete bevel gear.

[0012] Furthermore, the rudder mechanism includes a slewing bracket, which includes a connecting part and a supporting part. The connecting part is a cylindrical sleeve and is sleeved on the slewing shaft. The supporting part includes a rectangular platform and a fan-shaped platform that is transitionally connected to the rectangular platform. The rectangular platform is provided with a stop pin hole, a perforated protruding lug, a first positioning hole, and a bolt hole.

[0013] Furthermore, the support portion is located at the corresponding position where there are no teeth in the second bevel gear.

[0014] Furthermore, the rudder mechanism also includes a rudder bearing housing, a rudder bearing, a rudder shaft, a third bevel gear, a rudder panel, and a rudder panel support. The rudder bearing housing is fixed on the support, the rudder bearing is placed inside the rudder bearing housing, and the rudder shaft is transition-fitted with the inner ring of the rudder bearing. One end of the rudder shaft is connected to the third bevel gear, and the other end is connected to the rudder panel support. The rudder panel support is fixedly connected to the rudder panel.

[0015] Furthermore, the third bevel gear is provided with two protrusions, and a braking groove is formed between the protrusions.

[0016] Furthermore, the locking device includes a brake block, a stop pin, a stop pin spring, and a tension spring with hooks at both ends. The brake block is connected to a perforated lug via a rotating pin. The brake block has a second pull ring, and a tension spring is provided between the second pull ring and the first pull ring. The stop pin is connected to the stop pin spring. The stop pin is sequentially placed in the second circular hole, the first circular hole, and the stop pin hole. The stop pin spring is placed in the second circular hole, and one end of the stop pin spring is screwed into the internal thread of the second circular hole. The brake block is positioned directly above the stop pin hole, and the brake block is configured to be lifted away from the brake groove by the stop pin passing through the stop pin hole under the action of the tension spring.

[0017] The present invention has the following beneficial effects:

[0018] (1) The present invention drives the bevel gear mechanism to drive the rudder surface mechanism to rotate synchronously to the drive mechanism, and then drives the rudder surface mechanism to rotate around its own center line. With the help of the locking device, the two movements of rudder surface deployment and rudder surface deflection are realized. No special rudder surface deployment mechanism is required. The structure is simple and compact, the position locking is reliable, and the movement is smooth during the rudder surface deployment process.

[0019] (2) The present invention uses bevel gears for transmission. Bevel gear transmission has the advantages of stable transmission ratio, high torque transmission efficiency and small backlash. It can accurately convert the rotational motion of the motor into the deflection angle of the control panel, ensuring the accuracy of attitude adjustment during missile flight and avoiding the expansion of attitude deviation due to transmission error.

[0020] (3) In this invention, when the missile is inside the launch tube, the stop pin in the locking mechanism is pressed by the fan-shaped platform on the rotating bracket and is located in the stop pin hole, which does not restrict the rotation of the rotating bracket. The rotating bracket is fixed by the motor and the reducer. At this time, the brake block rotates counterclockwise under the tension of the tension spring and enters the brake groove on the third bevel gear, so that the rudder panel is locked and cannot rotate relative to the rudder bearing seat. When the missile is launched out of the launch tube, the first bevel gear is driven to rotate by the reducer and the drive shaft. Since the second bevel gear is engaged with the first bevel gear at this position, the second bevel gear is driven by the first bevel gear to drive the rotating bracket to rotate. The rudder panel installed on the rotating bracket begins to unfold. When the rudder panel rotates to the fully unfolded position on the side of the motor, the second bevel gear disengages from the first bevel gear, and the third bevel gear engages with the first bevel gear. The engagement occurs when the stop pin moves upward under the force of the stop pin spring, entering the stop pin hole on the slewing bracket and restricting the rotation of the slewing bracket relative to the gear base. The stop pin continues to move upward under the force of the stop pin spring, overcoming the tension of the tension spring and lifting the brake block, causing the brake block to rotate clockwise. The brake block leaves the brake groove on the third bevel gear, releasing the lock of the control panel. The motor rotates according to the missile flight control command, driving the control panel shaft and the control panel to deflect through the first bevel gear, thus controlling the missile's flight attitude. The unlocking process relies entirely on the spring force and the force transmission of the mechanical structure, which can effectively resist the harsh environment such as electromagnetic interference and high temperature vibration that the missile may encounter during flight. Compared with the electronic unlocking mechanism, the mechanical linkage unlocking has higher reliability, ensuring that the missile can still be unlocked stably in complex battlefield environments and ensuring the activation of the attitude control function.

[0021] (4) In this invention, the stop pin first releases the stop of the rotating bracket (enters the stop pin hole → restriction is released) by the elastic force of the stop pin spring, and then overcomes the tension of the tension spring to lift the brake block, so that it is disengaged from the brake groove of the third bevel gear. No additional drive components (such as a separate unlocking motor or electromagnet) are required, reducing the number of power sources, and the action is smooth and without delay. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of the rudder panel in the deployed state of the present invention.

[0023] Figure 2 This is a schematic diagram of the drive mechanism in this invention.

[0024] Figure 3 This is a schematic diagram of the bevel gear mechanism in this invention.

[0025] Figure 4 This is a cross-sectional view of the circular boss of the gear base in this invention.

[0026] Figure 5This is a schematic diagram of the rotating support structure in this invention.

[0027] Figure 6 This is a schematic diagram of the rudder surface mechanism in this invention.

[0028] Figure 7 This is a schematic diagram of the structure of the third bevel gear in this invention.

[0029] Figure 8 This is a partial schematic diagram of the location of the locking device in this invention.

[0030] Figure 9 This is a top view of the folded position of the rudder panel in this invention.

[0031] Figure 10 This is a structural diagram of the deflection motion part of the rudder panel in this invention. Detailed Implementation

[0032] The technical solution of the present invention will be further described in detail below with reference to specific embodiments. However, these embodiments are not intended to limit the present invention. Any similar structures and similar variations of the present invention should be included in the protection scope of the present invention. The commas in the present invention all indicate the relationship between and. The English letters in the present invention are case-sensitive.

[0033] like Figure 1 As shown, this invention provides a folding control surface combined motion mechanism, including a mounting bracket 1, a drive mechanism 2, a bevel gear mechanism 3, a locking device 4, and a control surface mechanism 5. The drive mechanism 2 and the bevel gear mechanism 3 are both mounted on the mounting bracket 1. The bevel gear mechanism 3 is connected to the control surface mechanism 5. The drive mechanism 2 is configured to drive the bevel gear mechanism 3 to synchronously rotate the control surface mechanism 5 to the drive mechanism 2 position, and then drive the control surface mechanism 5 to rotate around its own centerline. The locking device 4 is configured to lock the control surface mechanism 5 and restrict its rotation when it is not rotating around its own centerline. The mounting bracket 1 is fixed to the missile body.

[0034] like Figure 2 As shown, the drive mechanism 2 includes a motor bracket 21, a motor 22, a reducer 25, a drive shaft 23, and a first bevel gear 24. The reducer is fixed on the motor bracket 21, and the motor 22 is fixed at the rear end of the reducer. The reducer is driven to move by the motor shaft of the motor 22. The drive shaft 23 is fixed on the output component of the reducer. The motor bracket 21 is provided with a first through hole, and the drive shaft 23 passes through the first through hole and connects to the first bevel gear 24.

[0035] Preferably, the motor bracket 21 is L-shaped, with the short side of the L-shape fixed to the mounting bracket 1 by bolts; the first through hole is located on the long side of the L-shape of the motor bracket 21. The motor bracket 21 is provided with triangular stiffeners 211 to enhance its stability.

[0036] The first bevel gear 24 is a complete bevel gear. The first bevel gear 24 has a first central hole and a first radial hole in the middle. The axis of the first radial hole intersects perpendicularly with the axis of the first central hole of the first bevel gear. The drive shaft has a second radial hole in the middle and a second central hole on it. The axis of the second radial hole intersects perpendicularly with the axis of the second central hole. The first radial hole and the second radial hole are the same size. The first bevel gear is mounted on the drive shaft through the first central hole, and the axes of the first radial hole and the second radial hole are coincident. By inserting the transmission pin 241 into the first radial hole and the second radial hole, the transmission pin 241 is interference-fitted with the first radial hole and the second radial hole, respectively, and the first bevel gear is fixed on the drive shaft, and the two rotate together.

[0037] like Figure 3-4 As shown, the bevel gear mechanism 3 includes a gear base 31, a rotary shaft 32, a rotary bearing 34, and a second bevel gear 33. The gear base 31 is fixed on the mounting bracket 1. The rotary shaft 32 and the rotary bearing are disposed within the gear base 31, with the rotary shaft 32 and the inner ring of the rotary bearing undergoing a transition fit. The rotary shaft 32 is also connected to the second bevel gear 33, which has a first pull ring 331. The rotary shaft 32 has a first keyway, within which a first flat key 321 is provided. A circular boss 311 is provided on the outer circumferential surface of the gear base 31. The circular boss 311 has a first circular hole 3111 and a second circular hole 3112, which communicate with each other. The first circular hole is located above the second circular hole, and the diameter of the first circular hole is smaller than that of the second circular hole. The bottom of the inner ring of the second circular hole has an internal thread.

[0038] Preferably, the bottom of the gear base 31 is provided with an annular flange 312, and bolt holes are evenly distributed on the annular flange 312. The annular flange 312 of the gear base 31 is placed on the surface of the mounting bracket 1. Bolts pass through the bolt holes on the annular flange 312 and the bolt holes on the mounting bracket 1. Nuts are screwed into the lower part of the bolts to fix the gear base 31 to the mounting bracket 1. The gear base 31 is provided with a first placement hole, and the first placement hole is provided with a first annular step and a first annular groove. The slewing bearing is disposed on the first annular step, and a first retaining ring is provided in the first annular groove to limit the axial movement of the slewing bearing.

[0039] The rotary shaft 32 is cylindrical and has an annular boss. The rotary bearing is located below the annular boss. The rotary shaft 32 has a first threaded hole at the center of its bottom surface and a rotary bearing retaining ring at its bottom. The rotary bearing retaining ring has a third center hole. A bolt 323 passes through the third center hole and is screwed into the first threaded hole on the bottom surface of the rotary shaft to press the rotary bearing retaining ring onto the inner ring of the rotary bearing. A spring washer 322 is also provided between the bolt and the rotary bearing retaining ring.

[0040] The second bevel gear 33 is an incomplete bevel gear, and the number of teeth of an incomplete bevel gear is an integer and satisfies the following:

[0041]

[0042] In the formula, Z0 is the number of teeth of the original complete bevel gear; Z is the number of teeth of the incomplete bevel gear.

[0043] like Figure 5 As shown, the rudder mechanism 5 includes a rotary support 51, which includes a connecting part 511 and a supporting part 512. The connecting part 511 is a cylindrical sleeve and is sleeved on the rotary shaft 32. The supporting part 512 includes a rectangular platform 5121 and a sector-shaped platform 5122 that transitions to the rectangular platform. The rectangular platform 5121 is provided with a stop pin hole 5123, a perforated protruding lug 5124, a first positioning hole 5125, and a bolt hole 5126. Preferably, the center of the sector-shaped platform 5122 is located on the axis of the rotary support 51.

[0044] Preferably, the connecting part 511 has a fourth center hole 5112 of the second keyway 5111 inside, and the rotating bracket 51 rotates synchronously with the rotating shaft 32 through the cooperation of the first flat key and the second keyway 5111. The rectangular platform 5121 is perpendicular to the axis of the fourth center hole 5112. The distance from the center line of the stop pin hole 5123 to the axis of the fourth center hole 5112 is less than the sector radius of the sector platform 5122. The support part 512 is located at the corresponding position without teeth in the second bevel gear 33.

[0045] like Figure 6 As shown, the rudder mechanism 5 also includes a rudder bearing housing 52, a rudder bearing 57, a rudder shaft 53, a third bevel gear 54, a rudder panel 55, and a rudder panel support 56. The rudder bearing housing 52 is fixed on the support part 512, the rudder bearing is placed inside the rudder bearing housing 52, and the rudder shaft 53 is transition-fitted with the inner ring of the rudder bearing. One end of the rudder shaft 53 is connected to the third bevel gear 54, and the other end is connected to the rudder panel support 56. The rudder panel support 56 is fixedly connected to the rudder panel 55.

[0046] The third bevel gear 54 is a complete bevel gear.

[0047] Preferably, the rudder bearing housing 52 is cylindrical, and a second placement hole is provided inside the rudder bearing housing 52. A second annular step is provided inside the second placement hole. Two rudder bearings are provided, and the two rudder bearings are respectively located on both sides of the second annular step. There is a bushing between the inner ring of the rudder bearing near the third bevel gear and the third bevel gear. The third bevel gear 54 can rotate around the center line of the rudder shaft 53 together with the rudder plate. A third bevel gear retaining ring 531 is provided on the rudder shaft 53 near the third bevel gear 54. A threaded hole is provided at the center of the end face of the rudder shaft near the third bevel gear 54. A screw is passed through the center hole of the third bevel gear retaining ring and screwed into the threaded hole of the rudder shaft to press the third bevel gear retaining ring onto the third bevel gear 54. A spring washer is provided between the screw and the third bevel gear retaining ring.

[0048] The bottom surface of the rudder bearing housing 52 has a threaded hole. The bottom surface of the rudder bearing housing rests on the support part 512. A bolt passes through the bolt hole on the slewing bracket 51 and is screwed into the threaded hole on the bottom surface of the rudder bearing housing 52 to fix the rudder bearing housing 52 to the slewing bracket 51. A spring washer is placed between the bolt and the slewing bracket 51. The bottom surface of the rudder bearing housing 52 has a second positioning hole with its axis perpendicular to the bottom surface. The second positioning hole has the same diameter as the first positioning hole and their axes coincide. A positioning pin is placed in both the second positioning hole and the first positioning hole.

[0049] The rudder panel support 56 is provided with a U-shaped groove 561, and the rudder panel 55 is placed in the U-shaped groove 561. The rudder panel 55 is fixedly connected to the rudder panel support 56 by fasteners.

[0050] like Figure 7 As shown, the rudder shaft 53 is provided with a third keyway, and the third bevel gear 54 is provided with a fifth center hole 544 with a fourth keyway 543. The third bevel gear 54 is mounted on the rudder shaft 53 through the fifth center hole. A second flat key is provided in the fourth keyway and the third keyway.

[0051] The third bevel gear 54 is provided with two protrusions 541, and a brake groove 542 is formed between the protrusions 541.

[0052] like Figure 8As shown, the locking device 4 includes a brake block 41, a stop pin 42, a stop pin spring, and a tension spring 44 with hooks at both ends. The brake block 41 is connected to a perforated lug 5124 via a rotating pin 45. The brake block 41 is provided with a second pull ring 411, and a tension spring 44 is provided between the second pull ring 411 and the first pull ring 331. The stop pin 42 is connected to the stop pin spring. The stop pin 42 is placed sequentially in the second round hole, the first round hole, and the stop pin hole 5123. The stop pin spring is placed in the second round hole, and one end of the stop pin spring is screwed into the internal thread of the second round hole. The brake block 41 is placed directly above the stop pin hole 5123. The brake block 41 is configured to be pushed away from the brake groove 542 by the stop pin 42 passing through the stop pin hole 5123 under the action of the tension spring 44. The distance between the center line of the stop pin hole 5123 and the axis of the fourth center hole is equal to the distance between the center line of the stop pin 42 and the center line of the fourth center hole.

[0053] Preferably, there is a gap between the stop pin 42 and the first circular hole, and the top of the stop pin 42 is spherical. The stop pin spring is a compression coil spring.

[0054] In the initial state, the second bevel gear 33 meshes with the first bevel gear 24. The sector platform 5122 is located above the stop pin hole 5123, and the stop pin 42 is confined within the stop pin hole 5123. Under the action of the tension spring 44, the brake block 41 abuts against the rotation of the third bevel gear 54 within the brake groove 542. Under the action of the spring force, the stop pin 42 is embedded in the stop pin hole 5123 of the rotating bracket 51, directly restricting the relative rotation between the rotating bracket 51 and the gear base 31. This can prevent the control panel from unexpectedly deflecting due to vibration or bumps during missile storage, transportation, or initial launch, ensuring the stability of the initial attitude of the control surface, preventing structural collision damage or pre-positioning deviation (such as the initial angle deviation of the control surface leading to loss of attitude control after launch), and ensuring the safety of ground operations and the accuracy of the attitude before launch. The stop pin 42 first releases the stop of the rotary bracket 51 by means of the elastic force of the stop pin spring (entering the stop pin hole → restriction released), and then overcomes the tension of the tension spring 44 to lift the brake block, so that it is disengaged from the brake groove of the third bevel gear 54. No additional drive components (such as a separate unlocking motor or electromagnet) are required, reducing the number of power sources, and the action is smooth and without delay.

[0055] Working principle:

[0056] When the second bevel gear 33 rotates to a certain angle range, the teeth on it can mesh with the teeth on the first bevel gear 24. The first bevel gear 24 drives the second bevel gear 33 to move, and through the rotary shaft 32 and the first flat key, it drives the rotary support 51 to rotate. Since the second bevel gear 33 is missing more than 2 teeth, and the overlap ratio of bevel gear transmission is generally less than 2, when the second bevel gear 33 rotates to a certain angle range, the first bevel gear 24 will disengage from the second bevel gear 33, and the rotary support 51 can be locked.

[0057] like Figure 9-10 As shown, when the missile is inside the launch tube, the control panel 55 is in a folded position and located below the motor 22. At this time, the first bevel gear 24 meshes with the second bevel gear 33, while the third bevel gear 54 disengages from the first bevel gear 24. The stop pin 42 is pressed by the fan-shaped platform 5122 on the rotary bracket 51 and is located in the stop pin hole 5123, which does not restrict the rotation of the rotary bracket 51. The rotary bracket 51 is fixed by the motor 22 and the reducer. At this time, the brake block 41 rotates counterclockwise under the tension of the tension spring 44. The brake block 41 enters the brake groove 542 on the third bevel gear 54, so that the control panel 55 is locked and cannot rotate relative to the control surface bearing seat 52.

[0058] After the missile is launched from the launch tube, the motor 22 starts rapidly, driving the first bevel gear 24 to rotate via the reducer and drive shaft 23. Since the second bevel gear 33 meshes with the first bevel gear 24 at this position, the second bevel gear 33, driven by the first bevel gear 24, rotates the slewing bracket 51. The rudder panel 55 mounted on the slewing bracket 51 begins to unfold. When the rudder panel 55 rotates to the fully unfolded position on the side of the motor 22, the second bevel gear 33 disengages from the first bevel gear 24, while the third bevel gear 54 engages with the first bevel gear 24. Simultaneously, the center line of the stop pin hole 5123 of the slewing bracket 51 aligns with the stop pin 42 on the gear base 31. When the center lines coincide, the stop pin 42 moves upward under the elastic force of the stop pin spring and enters the stop pin hole 5123 on the rotary support 51, restricting the rotation of the rotary support 51 relative to the gear base 31. The stop pin 42 continues to move upward under the push of the stop pin spring, overcoming the tension of the tension spring 44 and lifting the brake block 41, causing the brake block 41 to rotate clockwise. The brake block 41 leaves the brake groove 542 on the third bevel gear 54, releasing the lock of the control panel 55. The motor 22 rotates according to the missile flight control command, driving the control panel shaft 53 and the control panel 55 to deflect through the first bevel gear 24, thereby realizing the control of the missile's flight attitude.

[0059] Based on the general operating characteristics of missiles, after the control panel 55 is unfolded, the rotating bracket 51 does not need to reverse the movement to put the control panel 55 back into the folded state. Therefore, this invention can achieve both the unfolding and deflection of the control panel 55 using a single motor and reducer, through a bevel gear mechanism 3 and a locking device 4. It does not require a dedicated control surface unfolding mechanism, has a simple and compact structure, reliable position locking, and smooth movement during the control surface unfolding process.

[0060] This invention uses bevel gears for transmission. Bevel gear transmission has the advantages of stable transmission ratio, high torque transmission efficiency, and small backlash. It can accurately convert the rotational motion of the motor into the deflection angle of the control panel, ensuring the accuracy of attitude adjustment during missile flight and avoiding the expansion of attitude deviation due to transmission errors.

[0061] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

Claims

1. A folding rudder surface combined motion mechanism, characterized in that, The system includes a mounting bracket, a drive mechanism, a bevel gear mechanism, a locking device, and a rudder surface mechanism. The drive mechanism and the bevel gear mechanism are both mounted on the mounting bracket. The bevel gear mechanism is connected to the rudder surface mechanism. The drive mechanism is configured to drive the bevel gear mechanism to synchronously rotate the rudder surface mechanism to the drive mechanism, and then drive the rudder surface mechanism to rotate around its own centerline. The locking device is configured to lock the rudder surface mechanism and restrict its rotation when the rudder surface mechanism is not rotating around its own centerline.

2. The folding rudder surface combined motion mechanism according to claim 1, characterized in that, The drive mechanism includes a motor bracket, a motor, a reducer, a drive shaft, and a first bevel gear. The reducer is fixed on the motor bracket, the motor is fixed at the rear end of the reducer, and the drive shaft is fixed on the output component of the reducer. The motor bracket has a first through hole, and the drive shaft passes through the first through hole to connect with the first bevel gear.

3. The folding rudder surface combined motion mechanism according to claim 1, characterized in that, The bevel gear mechanism includes a gear base, a rotary shaft, a rotary bearing, and a second bevel gear. The gear base is fixed on a mounting bracket. The rotary shaft and the rotary bearing are disposed inside the gear base. The rotary shaft and the inner ring of the rotary bearing are transition-fitted. The rotary shaft is also connected to the second bevel gear, and the second bevel gear is provided with a first pull ring.

4. The folding rudder surface combined motion mechanism according to claim 3, characterized in that, A circular boss is provided on the outer circular surface of the gear base. The circular boss has a first circular hole and a second circular hole. The first circular hole and the second circular hole are connected, and the first circular hole is located above the second circular hole. The diameter of the first circular hole is smaller than the diameter of the second circular hole. The bottom of the inner ring of the second circular hole is provided with an internal thread.

5. A folding rudder surface combined motion mechanism according to claim 4, characterized in that, The second bevel gear is an incomplete bevel gear, and the number of teeth of an incomplete bevel gear is an integer and satisfies the following: In the formula, Z0 is the number of teeth of the original complete bevel gear; Z is the number of teeth of the incomplete bevel gear.

6. The folding rudder surface combined motion mechanism according to claim 5, characterized in that, The rudder mechanism includes a slewing bracket, which includes a connecting part and a supporting part. The connecting part is a cylindrical sleeve and is sleeved on the slewing shaft. The supporting part includes a rectangular platform and a fan-shaped platform that is transitionally connected to the rectangular platform. The rectangular platform is provided with a stop pin hole, a perforated protruding lug, a first positioning hole, and a bolt hole.

7. A folding rudder surface combined motion mechanism according to claim 6, characterized in that, The support is located at the corresponding position in the second bevel gear where there are no teeth.

8. A folding rudder surface combined motion mechanism according to claim 6, characterized in that, The rudder mechanism further includes a rudder bearing housing, a rudder bearing, a rudder shaft, a third bevel gear, a rudder panel, and a rudder panel support. The rudder bearing housing is fixed on the support, the rudder bearing is placed inside the rudder bearing housing, and the rudder shaft is transition-fitted with the inner ring of the rudder bearing. One end of the rudder shaft is connected to the third bevel gear, and the other end is connected to the rudder panel support. The rudder panel support is fixedly connected to the rudder panel.

9. A folding rudder surface combined motion mechanism according to claim 8, characterized in that, The third bevel gear has two protrusions, and a braking groove is formed between the protrusions.

10. A folding rudder surface combined motion mechanism according to claim 9, characterized in that, The locking device includes a brake block, a stop pin, a stop pin spring, and a tension spring with hooks at both ends. The brake block is connected to a perforated lug via a rotating pin. The brake block has a second pull ring, and a tension spring is provided between the second pull ring and the first pull ring. The stop pin is connected to the stop pin spring. The stop pin is sequentially placed in a second circular hole, a first circular hole, and a stop pin hole. The stop pin spring is placed in the second circular hole, and one end of the stop pin spring is screwed into the internal thread of the second circular hole. The brake block is positioned directly above the stop pin hole, and the brake block is configured to be lifted away from the brake groove by the stop pin passing through the stop pin hole under the action of the tension spring.

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