A locking and unlocking mechanism for locking and unlocking multiple rudders at a single location and simultaneously unlocking multiple rudders

Abstract

The present application provides a locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple wing rudders, and relates to the technical field of aerospace wing rudder systems, including a housing, the housing including a chassis and a connecting sleeve; the connecting sleeve is provided with installation grooves and docking grooves arranged at intervals along the circumferential direction; the wing surface is fitted and installed on the outer wall of the connecting sleeve; the rudder surface is located in the installation groove, one end is rotatably connected to the connecting sleeve through a second rotating shaft, and the other end is provided with an n-shaped clamping groove; the slip ring is rotatably installed on the inner wall of the connecting sleeve, and avoidance grooves are respectively provided corresponding to the clamping groove and the wing fixing block. By providing the installation groove and the docking groove on the housing, the rudder surface and the wing surface can both dock with the internal slip ring; at the same time, the slip ring is also provided with an avoidance groove corresponding to the installation groove and the docking groove, so that the rudder surface and the wing surface can not only freely enter and exit the housing through the avoidance groove, but also be clamped with the slip ring to complete the locking; because the rudder surface and the wing surface are both locked and connected with the same slip ring, it can also ensure that the rudder surface and the wing surface are synchronously unlocked when the slip ring is driven.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace wing-rudder systems, and in particular to a locking and unlocking mechanism for locking and unlocking multiple wing-rudders at a single location simultaneously. Background Art

[0002] During the mission planning of the flight process, some aircraft are initially stored in a limited space. There is not much space to arrange the wing-rudder system on the outside of the aircraft. The wing-rudder system needs to be folded inside the aircraft. At the same time, the wing-rudder needs to be used synchronously to control the aircraft at a certain moment after the flight.

[0003] In this process, a set of locking and unlocking mechanisms is needed to achieve the ability to lock and deploy the rudders, and then control the attitude of the aircraft; the existing locking and unlocking mechanisms have risk points that affect the flight test, such as asynchrony and multiple single-point failures, which increase the cost of the entire flight test while also bringing a great risk of non-deployment, and may even ultimately lead to mission failure; therefore, the above problems need to be solved urgently. Summary of the invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desirable to provide a locking and unlocking mechanism that can lock at a single location and simultaneously unlock multiple rudders.

[0005] The present application provides a locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple rudders, comprising:

[0006] A housing, the housing comprising a circular bottom plate and a connecting sleeve coaxial with the bottom plate;

[0007] The connecting sleeve is provided with installation grooves and docking grooves arranged at intervals along the circumferential direction;

[0008] An airfoil, the airfoil being fitted on the outer wall of the connecting sleeve, one end of which is rotatably connected to the connecting sleeve via a first rotating shaft, and one end of which is provided with an airfoil fixing block corresponding to the docking groove;

[0009] A rudder surface, the rudder surface is located in the installation groove, one end of the rudder surface is rotatably connected to the connecting sleeve through a second rotating shaft, and one end of the rudder surface is provided with an N-shaped slot;

[0010] A slip ring is rotatably mounted on the inner wall of the connecting sleeve, and avoidance grooves are respectively provided corresponding to the clamping groove and the wing fixing block.

[0011] Furthermore,

[0012] One end of the avoidance groove along the circumferential direction is also provided with a clamping inclined surface;

[0013] The wall thickness of one end of the clamping inclined surface close to the avoidance groove is relatively thin, and is used to guide the clamping groove and the wing fixing block and form a clamping connection.

[0014] Furthermore,

[0015] The wing fixing block includes a base connected to the wing surface;

[0016] An L-shaped extension portion is provided on one side of the base away from the wing fixing block for clamping with the slip ring.

[0017] Furthermore,

[0018] The connecting sleeve is also provided with a limit block corresponding to the slip ring;

[0019] The limit block is L-shaped, fixedly mounted on the connecting sleeve, with its bottom parallel to the chassis, and is used to limit the axial displacement of the slip ring.

[0020] Furthermore,

[0021] The slip ring is provided with a first strip-shaped hole penetrating along the circumferential direction;

[0022] A limit bolt for limiting the rotational travel of the slip ring is arranged in the first strip-shaped hole;

[0023] The limiting bolt is fixedly mounted on the connecting sleeve.

[0024] Furthermore,

[0025] A limit bearing is provided on the chassis corresponding to the slip ring;

[0026] The limit bearing is connected to the chassis via a mounting seat, is rotatably connected to the mounting seat, and abuts against the slip ring;

[0027] The mounting seat is fixedly mounted on the chassis.

[0028] Furthermore,

[0029] An energy storage mechanism is provided on the chassis corresponding to the slip ring;

[0030] The energy storage mechanism comprises an energy storage seat fixedly mounted on the chassis;

[0031] The energy storage seat is hinged with a first spring seat for installing an energy storage spring;

[0032] One end of the first spring seat away from the energy storage seat is provided with a matching mounting rod corresponding to the energy storage spring.

[0033] Furthermore,

[0034] The slip ring is provided with a docking seat corresponding to the energy storage seat;

[0035] The docking seat is fixedly mounted on the slip ring, and a second spring seat is provided corresponding to the energy storage spring;

[0036] The second spring seat is hingedly mounted on the docking seat, and a mounting sleeve is provided corresponding to the energy storage spring;

[0037] The inner diameter of the mounting sleeve matches the outer diameter of the mounting rod, and the outer diameter matches the inner diameter of the energy storage spring.

[0038] Furthermore,

[0039] The energy storage seat and the first spring seat are hinged via a first hinge shaft;

[0040] The docking seat and the second spring seat are hingedly connected via a second hinge shaft;

[0041] A driving mechanism is detachably mounted between the first hinge shaft and the second hinge shaft;

[0042] The driving mechanism comprises a base body and an operating rod;

[0043] The base body is provided with a second strip-shaped hole penetrating along the length direction, one end of the base body is provided with a matching hinge hole corresponding to the second hinge shaft, and the other end of the base body is provided with a matching mounting hole corresponding to the operating rod;

[0044] The operating rod is threadedly connected to the mounting hole, and an abutment block is provided at the end corresponding to the first hinge shaft, which is used to drive the first spring seat and the second spring seat to compress the energy storage spring.

[0045] Furthermore,

[0046] The housing is also provided with a locking mechanism corresponding to the slip ring;

[0047] The locking mechanism comprises a fixing seat fixedly mounted on the chassis and a pin puller fixedly mounted on the connecting sleeve;

[0048] A matching docking block is provided on the slip ring corresponding to the fixing seat;

[0049] The docking block and the fixing seat are provided with coaxial pin holes corresponding to the pin puller;

[0050] The pin puller is provided with a matching pin corresponding to the pin hole, which is used to fix the slip ring and the housing.

[0051] The advantages and positive effects of this application are:

[0052] The technical solution provides mounting grooves and docking grooves on the shell, so that both the rudder surface and the wing surface can dock with the internal slip ring; at the same time, the slip ring is also provided with avoidance grooves corresponding to the mounting grooves and the docking grooves, so that the rudder surface and the wing surface can not only freely enter and exit the shell through the avoidance grooves, but also be locked with the slip ring; because the rudder surface and the wing surface are both locked and connected with the same slip ring, it can also ensure that the rudder surface and the wing surface are unlocked synchronously when the slip ring is driven, thereby meeting the use requirements of existing aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Figure 1 A schematic diagram of the structure of a locking and unlocking mechanism for locking and unlocking multiple rudders at a single location and simultaneously unlocking multiple rudders provided in an embodiment of the present application;

[0054] Figure 2 A schematic diagram of the structure of the energy storage mechanism of the locking and unlocking mechanism for locking at a single location and simultaneously unlocking multiple rudders provided in an embodiment of the present application;

[0055] Figure 3 A schematic diagram of the structure of a driving mechanism of a locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple rudders provided in an embodiment of the present application.

[0056] The text markings in the figure are as follows: 100-chassis; 110-connecting sleeve; 111-installing groove; 112-docking groove; 113-limiting block; 120-limiting bearing; 121-mounting seat; 130-energy storage seat; 131-first spring seat; 140-energy storage spring; 150-base; 151-second strip hole; 160-operating rod; 161-abutment block; 170-fixing seat; 180-pin puller; 200-wing surface; 210-wing fixing block; 300-rudder surface; 400-slip ring; 401-first strip hole; 410-avoidance groove; 420-limiting bolt; 430-docking seat; 431-second spring seat; 440-docking block. DETAILED DESCRIPTION

[0057] In order to enable those skilled in the art to better understand the technical solution of the present application, the present application is described in detail below in conjunction with the accompanying drawings. The description in this section is only exemplary and explanatory and should not have any limiting effect on the scope of protection of the present application.

[0058] Please refer to Figure 1-3The present embodiment provides a locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple wing rudders, comprising a shell, the shell comprising a circular chassis 100 and a connecting sleeve 110 coaxial with the chassis 100; the connecting sleeve 110 is provided with mounting grooves 111 and docking grooves 112 arranged at intervals along the circumferential direction; a wing surface 200, the wing surface 200 is fittedly mounted on the outer wall of the connecting sleeve 110, one end of the wing surface 200 is rotatably connected to the connecting sleeve 110 through a first rotating shaft, and the other end is provided with a wing fixing block 210 through the corresponding docking groove 112; a rudder surface 300, the rudder surface 300 is located in the mounting groove 111, one end of the rudder surface 300 is rotatably connected to the connecting sleeve 110 through a second rotating shaft, and the other end is provided with an n-shaped clamping groove; a slip ring 400, the slip ring 400 can be rotatably mounted on the inner wall of the connecting sleeve 110, and avoidance grooves 410 are respectively provided corresponding to the clamping groove and the wing fixing block 210.

[0059] In this embodiment, the wing surface 200 and the rudder surface 300 are respectively connected to the connecting sleeve 110 through a rotating shaft; the rotating shaft is located at the end of the connecting sleeve 110 away from the chassis 100, and the axial direction is tangent to the circumference of the connecting sleeve 110; the ends of the wing surface 200 and the rudder surface 300 are at the same height as the ends of the connecting sleeve 110, and are hingedly installed with the corresponding rotating shaft.

[0060] In this embodiment, a docking groove 112 is provided on the connecting sleeve 110 corresponding to the wing surface 200; at the same time, a wing fixing block 210 is provided on the wing surface 200 corresponding to the docking groove 112; one end of the wing fixing block 210 is fixedly installed on the wing surface 200, and the other end extends to the interior of the connecting sleeve 110 through the docking groove 112.

[0061] In this embodiment, a mounting groove 111 is provided on the connecting sleeve 110 corresponding to the control surface 300 ; the control surface 300 is located in the mounting groove 111 , and an n-shaped slot is provided at the end portion located inside one side of the connecting sleeve 110 .

[0062] In this embodiment, the slip ring 400 can be rotatably installed inside the connecting sleeve 110, and the corresponding card slot and the wing fixing block 210 are respectively provided with an avoidance groove 410, so that the wing surface 200 and the control surface 300 can be locked and unlocked by rotation.

[0063] In a preferred embodiment, a clamping slope is further provided at one circumferential end of the avoidance groove 410; the wall thickness of the clamping slope at one end close to the avoidance groove 410 is relatively thin, which is used to guide the clamping groove and the wing fixing block 210 and form a clamping connection.

[0064] In this embodiment, a snap-in bevel is provided at one end of the avoidance groove 410 along the circumferential direction; when the slip ring 400 is rotated, when the avoidance groove 410 is aligned with the mounting groove 111 and the docking groove 112, the rudder surface 300 and the wing surface 200 can be freely flipped; when the snap-in bevel is aligned with the mounting groove 111 and the docking groove 112, it can be docked with the wing fixing block 210 and the snap-in groove, thereby locking the rudder surface 300 and the wing surface 200.

[0065] In a preferred embodiment, the wing fixing block 210 includes a base connected to the wing surface 200 ; an L-shaped extension portion is provided on a side of the base away from the wing fixing block 210 for clamping with the slip ring 400 .

[0066] In this embodiment, the wing fixing block 210 is fixedly connected to the wing surface 200 via a base, and extends to the inside of the connecting sleeve 110 through an L-shaped extension portion, so as to be clamped with the avoidance groove 410 of the slip ring 400 .

[0067] In a preferred embodiment, a limit block 113 is further provided on the connecting sleeve 110 corresponding to the slip ring 400 ; the limit block 113 is L-shaped, fixedly mounted on the connecting sleeve 110 , with its bottom parallel to the chassis 100 , and is used to limit the axial displacement of the slip ring 400 .

[0068] In this embodiment, the limit block 113 is fixedly mounted on the inner wall of the connecting sleeve 110 , and the bottom surface abuts against the top of the slip ring 400 . Together with the chassis 100 , it can not only limit the axial displacement of the slip ring 400 , but also will not limit the rotation of the slip ring 400 .

[0069] In a preferred embodiment, a first strip hole 401 is circumferentially provided on the slip ring 400 ; a limiting bolt 420 for limiting the rotational travel of the slip ring 400 is provided in the first strip hole 401 ; the limiting bolt 420 is fixedly mounted on the connecting sleeve 110 .

[0070] In a preferred embodiment, a limit bearing 120 is provided on the chassis 100 corresponding to the slip ring 400; the limit bearing 120 is connected to the chassis 100 through a mounting seat 121, is rotatably connected to the mounting seat 121, and abuts against the slip ring 400; the mounting seat 121 is fixedly installed on the chassis 100.

[0071] In a preferred embodiment, an energy storage mechanism is provided on the chassis 100 corresponding to the slip ring 400; the energy storage mechanism includes an energy storage seat 130 fixedly mounted on the chassis 100; a first spring seat 131 is hinged on the energy storage seat 130 for mounting an energy storage spring 140; a matching mounting rod is provided at one end of the first spring seat 131 away from the energy storage seat 130 corresponding to the energy storage spring 140.

[0072] In this embodiment, the energy storage seat 130 is fixedly mounted on the chassis 100 and is connected to the slip ring 400 via the energy storage spring 140; by rotating the slip ring 400, not only the wing surface 200 and the rudder surface 300 can be locked, but also the energy storage spring 140 can be compressed and stored with energy; conversely, the energy storage spring 140 releases energy to reversely drive the slip ring 400 to rotate, thereby unlocking the wing surface 200 and the rudder surface 300.

[0073] In a preferred embodiment, a docking seat 430 is provided on the slip ring 400 corresponding to the energy storage seat 130; the docking seat 430 is fixedly installed on the slip ring 400, and a second spring seat 431 is provided corresponding to the energy storage spring 140; the second spring seat 431 is hingedly installed on the docking seat 430, and a mounting sleeve is provided corresponding to the energy storage spring 140; the inner diameter of the mounting sleeve matches the outer diameter of the mounting rod, and the outer diameter matches the inner diameter of the energy storage spring 140.

[0074] In this embodiment, the docking seat 430 is fixedly mounted on the slip ring 400, and a second spring seat 431 is provided corresponding to the energy storage spring 140; the second spring seat 431 is hingedly mounted on the docking seat 430, so that it can be used for the installation of the energy storage spring 140 and can rotate with the expansion and contraction of the energy storage spring 140.

[0075] In a preferred embodiment, the energy storage seat 130 and the first spring seat 131 are hinged through a first hinge axis; the docking seat 430 and the second spring seat 431 are hinged through a second hinge axis; a driving mechanism is detachably installed between the first hinge axis and the second hinge axis; the driving mechanism includes a base 150 and an operating rod 160; a second strip hole 151 is provided on the base 150 along the length direction, a matching hinge hole is provided at one end corresponding to the second hinge axis, and a matching mounting hole is provided at the other end corresponding to the operating rod 160; the operating rod 160 is threadedly connected to the mounting hole, and an abutment block 161 is provided at the end corresponding to the first hinge axis, which is used to drive the first spring seat 131 and the second spring seat 431 to compress the energy storage spring 140.

[0076] In this embodiment, the driving mechanism is detachably installed between the energy storage seat 130 and the docking seat 430, and is used to shorten the distance between the energy storage seat 130 and the docking seat 430, and drive the slip ring 400 to rotate relative to each other, thereby locking the rudder surface 300 and the wing surface 200.

[0077] In this embodiment, the base 150 is plugged into the second hinge shaft through the hinge hole, and is movably connected to the first hinge shaft through the second strip hole 151; the abutment block 161 is located on the side of the second hinge shaft away from the first hinge shaft. When the driving operating rod 160 is rotated, the threaded connection relationship between the base 150 can effectively drive the first hinge shaft and the second hinge shaft to approach each other.

[0078] In a preferred embodiment, a locking mechanism is further provided on the shell corresponding to the slip ring 400; the locking mechanism includes a fixing seat 170 fixedly mounted on the chassis 100 and a pin puller 180 fixedly mounted on the connecting sleeve 110; a matching docking block 440 is provided on the slip ring 400 corresponding to the fixing seat 170; coaxial pin holes are provided on the docking block 440 and the corresponding pin puller 180 on the fixing seat 170; matching pins are provided on the corresponding pin holes on the pin puller 180 for fixing the slip ring 400 and the shell.

[0079] In this embodiment, the pin puller 180 is fixedly installed on the connecting sleeve 110, and the output end can effectively control the pin to move up and down along the axial direction of the connecting sleeve 110; when the energy storage mechanism completes energy storage, the pin hole on the fixing seat 170 and the pin hole and the pin on the docking block 440 will be in a coaxial state, and the pin puller 180 can control the pin to be inserted into the pin hole below, thereby completing the locking; conversely, when the pin puller 180 controls the pin to be out of the pin hole, the energy storage mechanism will automatically release energy.

[0080] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the concept and technical solution of the application to other occasions without improvement, should be regarded as the scope of protection of this application.

Claims

1. A locking and unlocking mechanism for locking at a single location and unlocking multiple rudders synchronously, characterized in that: include: A housing, the housing comprising a circular bottom plate (100) and a connecting sleeve (110) coaxial with the bottom plate (100); The connecting sleeve (110) is provided with installation grooves (111) and docking grooves (112) arranged at intervals along the circumferential direction; A wing surface (200), the wing surface (200) being fitted on the outer wall of the connecting sleeve (110), one end of the wing surface being rotatably connected to the connecting sleeve (110) via a first rotating shaft, and one end of the wing surface being provided with a wing fixing block (210) corresponding to the docking groove (112); A rudder surface (300), the rudder surface (300) being located in the installation groove (111), one end of which is rotatably connected to the connection sleeve (110) via a second rotating shaft, and one end of which is provided with an n-shaped slot; A slip ring (400), the slip ring (400) being rotatably mounted on the inner wall of the connecting sleeve (110), and having avoidance grooves (410) respectively corresponding to the clamping groove and the wing fixing block (210); An energy storage mechanism is provided on the chassis (100) corresponding to the slip ring (400); The energy storage mechanism comprises an energy storage seat (130) fixedly mounted on the chassis (100); The energy storage seat (130) is hingedly connected to a first spring seat (131) for mounting an energy storage spring (140); A docking seat (430) is provided on the slip ring (400) corresponding to the energy storage seat (130); The docking seat (430) is fixedly mounted on the slip ring (400), and a second spring seat (431) is provided corresponding to the energy storage spring (140); The energy storage seat (130) and the first spring seat (131) are hingedly connected via a first hinge shaft; The docking seat (430) and the second spring seat (431) are hingedly connected via a second hinge shaft; A driving mechanism is detachably mounted between the first hinge shaft and the second hinge shaft; The driving mechanism comprises a base (150) and an operating rod (160), and is used to drive the first spring seat (131) and the second spring seat (431) to compress the energy storage spring (140); The housing is also provided with a locking mechanism corresponding to the slip ring (400); The locking mechanism comprises a fixing seat (170) fixedly mounted on the chassis (100) and a pin puller (180) fixedly mounted on the connecting sleeve (110); A matching docking block (440) is provided on the slip ring (400) corresponding to the fixing seat (170); The docking block (440) and the fixing seat (170) are provided with coaxial pin holes corresponding to the pin puller (180); The pin puller (180) is provided with a matching pin corresponding to the pin hole, and is used to fix the slip ring (400) and the housing.

2. The locking and unlocking mechanism for locking at a single location and unlocking at multiple locations of rudders synchronously according to claim 1, characterized in that: One end of the avoidance groove (410) along the circumferential direction is also provided with a clamping inclined surface; The wall thickness of one end of the clamping inclined surface close to the avoidance groove (410) is relatively thin, and is used to guide the clamping groove and the wing fixing block (210) and form a clamping connection.

3. The locking and unlocking mechanism for locking at a single location and unlocking at multiple locations of rudders synchronously according to claim 1, characterized in that: The wing fixing block (210) comprises a base connected to the wing surface (200); An L-shaped extension portion is provided on a side of the base away from the wing fixing block (210) and is used for clamping with the slip ring (400).

4. The locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple rudders according to claim 1, characterized in that: A limit block (113) is further provided on the connecting sleeve (110) corresponding to the slip ring (400); The limit block (113) is L-shaped, fixedly mounted on the connecting sleeve (110), with a bottom portion parallel to the chassis (100), and is used to limit the axial displacement of the slip ring (400).

5. The locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple rudders according to claim 1, characterized in that: The slip ring (400) is provided with a first strip-shaped hole (401) penetrating along the circumferential direction; A limiting bolt (420) for limiting the rotational travel of the slip ring (400) is provided in the first strip-shaped hole (401); The limiting bolt (420) is fixedly mounted on the connecting sleeve (110).

6. The locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple rudders according to claim 1, characterized in that: A limit bearing (120) is provided on the chassis (100) corresponding to the slip ring (400); The limit bearing (120) is connected to the chassis (100) via a mounting seat (121), is rotatably connected to the mounting seat (121), and is in abutment with the slip ring (400); The mounting seat (121) is fixedly mounted on the chassis (100).

7. The locking and unlocking mechanism for locking and unlocking multiple rudders at a single location and unlocking them synchronously according to claim 1, characterized in that: One end of the first spring seat (131) away from the energy storage seat (130) is provided with a matching mounting rod corresponding to the energy storage spring (140).

8. The locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple rudders according to claim 7, characterized in that: The second spring seat (431) is hingedly mounted on the docking seat (430), and a mounting sleeve is provided corresponding to the energy storage spring (140); The inner diameter of the mounting sleeve matches the outer diameter of the mounting rod, and the outer diameter matches the inner diameter of the energy storage spring (140).

9. The locking and unlocking mechanism for locking at a single location and synchronously unlocking multiple rudders according to claim 1, characterized in that: The base body (150) is provided with a second strip-shaped hole (151) penetrating along the length direction, one end of which is provided with a matching hinge hole corresponding to the second hinge shaft, and the other end of which is provided with a matching mounting hole corresponding to the operating rod (160); The operating rod (160) is threadedly connected to the mounting hole, and an abutment block (161) is provided at the end thereof corresponding to the first hinge shaft.

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