Lock and boarding ladder

Abstract

The present application relates to a kind of lock and boarding ladder, belong to boarding auxiliary instrument technical field, boarding ladder includes mounting seat, branch arm piece, pedal assembly and lock, lock includes lock seat component, lock box component and rotating reset piece, lock seat component has lock post, lock box component has the locking piece for with lock post form locking cooperation or release locking cooperation, one of two sides wall in the rotating direction of locking piece has unlocking operation part, when boarding ladder is in the state of being retracted and is locked by lock, unlocking operation part is towards the surface of the fuselage of helicopter.The present application forms the unlocking of outer gouges by setting unlocking operation part, so that when the air pressure around helicopter increases due to weapon launch, locking piece has the tendency of rotating along locking direction under the action of air pressure, more conducive to realize locking, so as to effectively prevent boarding ladder from being unlocked under the action of air pressure, to meet the military use demand.

Description

Technical Field

[0001] This invention relates to a lock and a boarding ladder, belonging to the technical field of boarding assistance devices. Background Technology

[0002] Boarding ladders are commonly used on helicopters. They are mainly divided into two types according to their purpose: one is for passengers to board the cabin, and the other is for maintenance personnel to board the fuselage for maintenance work. Helicopters usually use folding boarding ladders for personnel to board and disembark. When not in use, the boarding ladder is folded up to the fuselage surface and locked. When in use, the boarding ladder is unlocked and opened to the ground.

[0003] In existing technologies, to achieve locking of the boarding ladder in the retracted state, a locking mechanism is currently used to connect the boarding ladder to the fuselage. For ease of unlocking, this mechanism typically involves pressing inwards. However, this method has a drawback: weapon firing increases the air pressure around the helicopter, making the boarding ladder prone to mis-locking due to the increased air pressure, thus failing to meet military usage requirements.

[0004] Therefore, in order to enable boarding stairs to meet military use requirements, a new boarding stairs with an optimized structure is needed. Summary of the Invention

[0005] The purpose of this invention is to provide a lock and boarding ladder that can meet the needs of military use.

[0006] This invention provides a lock, disposed within a retractable and expandable boarding ladder, for locking the boarding ladder to the fuselage of a helicopter in its retracted state, and characterized by comprising:

[0007] A locking assembly for mounting on the fuselage surface of a helicopter, having at least a locking pin;

[0008] A lock box assembly is provided at the free end of the boarding ladder, and has at least a locking element for engaging or disengaging with the lock pin;

[0009] The locking member can rotate between a locked position where the locking member and the locking pin are locked together and an unlocked position where the locking member and the locking pin are not locked together.

[0010] One of the two side walls of the locking member in the rotation direction has an unlocking operation part. When the unlocking operation part is subjected to an external force from its side wall toward the other side wall, the locking member rotates in the unlocking direction; and

[0011] The rotating reset component is used to give the locking component a tendency to rotate in the locking direction.

[0012] When the boarding ladder is in the retracted state and locked by the lock, the unlocking operation unit faces the fuselage surface of the helicopter.

[0013] The lock provided by this invention may also have the following features:

[0014] The locking pin is fixedly disposed at one end of the locking seat assembly facing away from the helicopter fuselage surface and extends horizontally.

[0015] The side wall of the locking member where the unlocking operation part is located has a locking groove that matches the locking pin. The locking groove is formed by a portion of the side wall of the locking member being recessed inward.

[0016] As the locking member rotates along the locking direction to the locking position, the locking pin engages in the locking groove and forms an obstruction on the rotation path of the locking member.

[0017] As the locking member rotates along the unlocking direction to the unlocking position, the locking pin disengages from the locking groove.

[0018] The lock provided by this invention may also have the following features:

[0019] The locking groove has a first groove wall and a second groove wall, wherein the tangent of the first groove wall and the tangent of the second groove wall form an acute angle.

[0020] When the locking member is in the locked position, both the first groove wall and the second groove wall abut against the circumferential surface of the locking pin.

[0021] The lock provided by this invention may also have the following features:

[0022] The first groove wall extends toward the side where the locking pin is located relative to the second groove wall. The first groove wall is an arc surface, and the second groove wall is a plane or an arc surface.

[0023] This invention provides a boarding ladder, installed on the fuselage surface of a helicopter, for allowing personnel to board the helicopter for maintenance work, and features the following characteristics:

[0024] The mounting bracket is fixedly installed on the surface of the helicopter fuselage.

[0025] The support arm has a first end hinged to the mounting base and a second end extending upward to form the free end of the boarding ladder. The support arm can rotate between a retracted position and an open position about its hinge point with the mounting base.

[0026] The pedal assembly is connected to the support arm; and

[0027] A locking device is provided for securing the boom member to the helicopter fuselage when the boom member is in the retracted position.

[0028] When the support arm is in the retracted position, the boarding ladder is in the retracted state.

[0029] When the support arm is in the open position, the boarding ladder is in the open state.

[0030] The lock is the lock as described above.

[0031] The boarding ladder provided by this invention may also have the following features:

[0032] The lock box assembly further includes a lock box body, which is fixedly disposed at the second end of the support arm and forms a rotation space with the support arm. The rotation space has a first opening on the side facing the lock seat assembly and a second opening on the side facing the end of the support arm.

[0033] The locking member is disposed within the rotation space, and its first end forms a rotational support with the support arm through a fixed shaft, and its second end extends to the positions of the first opening and the second opening. The unlocking operation part is located at the second end of the locking member.

[0034] The boarding ladder provided by this invention may also have the following features:

[0035] The rotation limiting part is provided on the side wall opposite to the first opening in the rotation space, and the rotation limiting part is formed by the portion of the support arm that serves as the side wall of the rotation space.

[0036] When the side wall opposite to the side wall where the unlocking operation part is located in the rotation direction of the locking member abuts against the rotation limiting part, the locking member is in the unlocked position.

[0037] The boarding ladder provided by this invention may also have the following features:

[0038] The support arm is curved and matches the surface contour of the helicopter fuselage.

[0039] The lock box body has a transition portion and abutment portion on the same side as the lower surface of the support arm when it is in the open position. The transition portion is located between the support arm and the abutment portion.

[0040] The transition portion is a curved surface that matches the surface contour of the support arm, and the abutment portion is a flat surface.

[0041] When the support arm is in the open position, the abutment is in a horizontal state.

[0042] The boarding ladder provided by this invention may also have the following features:

[0043] The rotating reset component is a torsion spring, which is sleeved on the fixed shaft. One end of the spring abuts against the inner wall of the lock box body, and the other end abuts against the side wall opposite to the side wall where the unlocking operation part is located in the rotation direction of the locking component.

[0044] The boarding ladder provided by this invention may also have the following features:

[0045] The lock seat assembly includes a lock seat body and a movable seat. The lock seat body is fixedly mounted on the fuselage surface of the helicopter, and the movable seat is movably mounted on the surface of the lock seat body, allowing the movable seat to be adjusted in position relative to the lock seat body.

[0046] The movable seat has a support portion extending toward a side away from the main body of the lock seat, and the lock pin is fixedly disposed at the extended end of the support portion.

[0047] Therefore, the present invention has the following advantages compared with the prior art:

[0048] According to the present invention, the boarding ladder includes a mounting base, a support arm, a step assembly, and a lock. The lock includes a lock seat assembly, a lock box assembly, and a rotation reset member. The lock seat assembly has a lock pin, and the lock box assembly has a locking member for engaging or disengaging with the lock pin. One of the two side walls of the locking member in the rotation direction has an unlocking operation part. When the boarding ladder is in the retracted state and locked by the lock, the unlocking operation part faces the fuselage surface of the helicopter. Since the unlocking operation part faces the fuselage surface of the helicopter when the boarding ladder is in the retracted state, an external unlocking is formed. This makes it easier to achieve locking when the air pressure around the helicopter increases due to weapon firing, as the locking member tends to rotate in the locking direction under the action of air pressure. This effectively prevents the boarding ladder from mis-locking under the action of air pressure, thereby meeting the requirements of military use.

[0049] Furthermore, the side wall of the locking component where the unlocking operation part is located has a locking groove that matches the locking pin. During the process of the locking component rotating in the locking direction to the locking position, the locking pin engages in the locking groove and forms a block in the rotation path of the locking component. Through the engagement between the locking pin and the locking groove, and under the action of the rotation reset component, the locking pin and the locking groove remain engaged, thereby achieving the locking engagement between the locking pin and the locking component, thus achieving the locking connection between the helicopter fuselage and the boarding ladder. During the process of the locking component rotating in the unlocking direction to the unlocking position, the locking pin disengages from the locking groove, thereby releasing the locking engagement between the locking pin and the locking component, thus releasing the locking connection between the helicopter fuselage and the boarding ladder. By using the locking pin and locking groove engagement method, locking and unlocking operations can be performed quickly and conveniently. Attached Figure Description

[0050] Figure 1 This is a three-dimensional structural diagram of the boarding ladder in an embodiment of the present invention;

[0051] Figure 2 This is a schematic diagram of the structure of the boarding ladder in its retracted state according to an embodiment of the present invention;

[0052] Figure 3 This is a schematic diagram of the structure of the boarding ladder in its open state according to an embodiment of the present invention;

[0053] Figure 4 This is a cross-sectional view of the lock in an embodiment of the present invention;

[0054] Figure 5 This is a schematic diagram of the cooperation structure between the locking pin and the locking element in an embodiment of the present invention;

[0055] Figure 6 This is a three-dimensional structural diagram of the free end of the boarding ladder in an embodiment of the present invention;

[0056] Figure 7 This is a partial structural diagram of the boarding ladder in its open state according to an embodiment of the present invention;

[0057] Figure 8 This is a schematic diagram of the cooperation structure between the lock seat assembly and the lock box assembly in an embodiment of the present invention;

[0058] Figure 9 This is a three-dimensional structural diagram of the lock seat assembly in an embodiment of the present invention;

[0059] Figure 10 This is a three-dimensional structural diagram of the mounting base in an embodiment of the present invention.

[0060] The markings in the attached drawings are described as follows: boarding ladder 100; mounting base 1; connecting shaft 11; rotating groove 12; first limiting part 121; second limiting part 122; support arm 2; lock 3; lock seat assembly 31; lock pin 311; lock seat body 312; movable seat 313; support part 313a; oblong hole 313b; lock box assembly 32; locking member 321; unlocking operation part 321a; lock groove 321b; first groove wall 321c; second groove wall 321d; lock box body 322; transition part 322a; abutment part 322b; rotating space 323; first opening 323a; second opening 323b; rotating limiting part 323c; fixed shaft 324; rotating reset member 33. Detailed Implementation

[0061] To make the technical means, creative features, objectives and effects of the present invention easy to understand, the lock and boarding ladder of the present invention will be specifically described below in conjunction with embodiments and accompanying drawings.

[0062] This embodiment provides a lock and a boarding ladder that can meet the needs of military use. The boarding ladder is installed on the surface of the helicopter fuselage for personnel to board the helicopter fuselage for maintenance work. The lock is used to lock the boarding ladder to the helicopter fuselage when it is in the retracted state.

[0063] Figure 1 This is a three-dimensional structural diagram of the boarding ladder in an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of the boarding ladder in its retracted state according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the boarding ladder in its open state according to an embodiment of the present invention.

[0064] like Figures 1 to 3 As shown, the boarding ladder 100 of this embodiment includes a mounting base 1, a support arm 2, a step assembly (not shown), and a lock 3. The mounting base 1 is fixedly mounted on the fuselage surface of the helicopter and is used to mount the support arm 2. A first end of the support arm 2 is hinged to the mounting base 1, and a second end extends upward to form the free end of the boarding ladder 100. The support arm 2 can rotate between a retracted position and an open position around its hinge point with the mounting base 1. When the support arm 2 is in the retracted position, the boarding ladder 100 is in the retracted state; when the support arm 2 is in the open position, the boarding ladder 100 is in the open state. The step assembly is connected to the support arm 2 and can retract and open with the support arm 2, providing a means for personnel to board and alight from the helicopter. The lock 3 is located at the free end of the boarding ladder 100 and on the fuselage surface of the helicopter, and is used to lock the support arm 2 to the helicopter fuselage when the support arm 2 is in the retracted position.

[0065] Understandably, when maintenance work is required, the operator releases the lock between the outrigger 2 and the helicopter fuselage, and rotates the outrigger 2 around its hinge point with the mounting base 1 to the open position, thereby putting the boarding ladder 100 in the open state. At this time, the free end of the boarding ladder 100 rests against the ground, allowing the operator to climb onto the helicopter fuselage through the step assembly to perform maintenance work. After the work is completed, the outrigger 2 is rotated around its hinge point with the mounting base 1 to the retracted position, and then the lock 3 is used to lock the outrigger 2 to the helicopter fuselage, thereby putting the boarding ladder 100 in the retracted state. At this time, the boarding ladder 100 is retracted to the surface of the helicopter fuselage.

[0066] Figure 4 This is a cross-sectional view of the lock in an embodiment of the present invention; Figure 5 This is a schematic diagram of the cooperation structure between the locking pin and the locking element in an embodiment of the present invention.

[0067] like Figure 4 and Figure 5 As shown, the lock 3 includes a lock seat assembly 31, a lock housing assembly 32, and a rotation reset member 33. The lock seat assembly 31 is disposed on the fuselage surface of the helicopter and has at least a locking pin 311. The lock housing assembly 32 is disposed at the free end of the boarding ladder 100 and has at least a locking member 321 for engaging or disengaging with the locking pin 311. The locking member 321 can rotate between a locked position where the locking member 321 engages with the locking pin 311 and an unlocked position where the locking member 321 disengages from the locking pin 311. One of the two side walls of the locking member 321 in the rotation direction has an unlocking operation portion 321a. When the unlocking operation portion 321a is subjected to an external force from its side wall toward the other side wall, the locking member 321 rotates in the unlocking direction. The rotation reset member 33 is used to give the locking member 321 a tendency to rotate in the locking direction. When the boarding ladder 100 is in the retracted state and locked by the lock 3, the unlocking operation portion 321a faces the fuselage surface of the helicopter.

[0068] In this embodiment, Figure 5 The direction indicated by A is the locking direction, and the opposite direction is the unlocking direction.

[0069] Understandably, when the boarding ladder 100 needs to be switched to the retracted state, the operator first applies force to the unlocking operation part 321a to drive the locking member 321 to rotate in the unlocking direction to the unlocking position. When the locking member 321 rotates to the unlocking position, the force applied to the unlocking operation part 321a is maintained to keep the locking member 321 in the unlocking position. Then, the boarding ladder 100 is switched to the retracted state. When the boarding ladder 100 is in the retracted state, the force applied to the unlocking operation part 321a is released. At this time, the locking member 321 rotates in the locking direction to the locking position under the action of the rotation reset member 33. When the locking member 321 rotates to the locking position, the locking member 321 and the locking pin 311 form a locking engagement. At this time, the boarding ladder 100 is locked to the fuselage of the helicopter, thereby realizing the locking of the boarding ladder 100 in the retracted state.

[0070] When the boarding ladder 100 is locked in the retracted state, the operator can apply force to the unlocking operation part 321a to drive the locking member 321 to rotate in the unlocking direction to the unlocking position. When the locking member 321 rotates to the unlocking position, the locking member 321 and the locking pin 311 are released from the locking engagement. At this time, the lock between the boarding ladder 100 and the helicopter fuselage is released, so the operator can apply force to the boarding ladder 100 to switch it to the open state, and then the operator can perform maintenance work.

[0071] When the boarding ladder 100 is in the retracted state, the unlocking operation part 321a faces the fuselage surface of the helicopter, thus forming an external unlocking mechanism. As a result, when the air pressure around the helicopter increases due to weapon firing, the locking part 321 tends to rotate in the locking direction under the action of air pressure, which is more conducive to locking. This effectively prevents the boarding ladder 100 from mis-locking under the action of air pressure, thereby meeting the needs of military use.

[0072] like Figure 5 As shown, the locking pin 311 is fixedly mounted on one end of the locking seat assembly 31 facing away from the helicopter fuselage surface and extends horizontally. The side wall of the locking member 321 where the unlocking operation part 321a is located has a locking groove 321b that matches the locking pin 311. The locking groove 321b is formed by a partial inward recess of the side wall of the locking member 321.

[0073] Understandably, during the process of the locking member 321 rotating in the locking direction to the locking position, the locking pin 311 engages in the locking groove 321b and forms an obstruction in the rotation path of the locking member 321. Through the engagement between the locking pin 311 and the locking groove 321b, and under the action of the rotation reset member 33, the locking pin 311 and the locking groove 321b remain engaged, thereby achieving the locking engagement between the locking pin 311 and the locking member 321, thus achieving the locking connection between the helicopter fuselage and the boarding ladder 100. During the process of the locking member 321 rotating in the unlocking direction to the unlocking position, the locking pin 311 disengages from the locking groove 321b, thereby releasing the locking engagement between the locking pin 311 and the locking member 321, thus releasing the locking connection between the helicopter fuselage and the boarding ladder 100. By using the locking method of the locking pin 311 and the locking groove 321b, locking and unlocking operations can be performed quickly and conveniently.

[0074] like Figure 5 As shown, the locking groove 321b has a first groove wall 321c and a second groove wall 321d. The tangent of the first groove wall 321c and the tangent of the second groove wall 321d form an acute angle. When the locking member 321 is in the locked position, both the first groove wall 321c and the second groove wall 321d abut against the circumferential surface of the locking pin 311.

[0075] Understandably, when the first groove wall 321c and the second groove wall 321d abut against the circumferential surface of the locking pin 311, the first groove wall 321c and the second groove wall 321d remain in contact with the locking pin 311 under the action of the rotation reset member 33, thereby achieving the locking engagement between the locking pin 311 and the locking member 321, so that the boarding ladder 100 cannot be switched to the open state in this state, thereby achieving the locking of the boarding ladder 100 and the helicopter fuselage.

[0076] In this embodiment, the acute angle formed by the tangent of the first groove wall 321c and the tangent of the second groove wall 321d is α, and the value of α is 86°. The junction of the first groove wall 321c and the second groove wall 321d adopts a rounded transition.

[0077] like Figure 5 As shown, the first groove wall 321c extends towards the side where the locking pin 311 is located relative to the second groove wall 321d. The first groove wall 321c is an arc surface, and the second groove wall 321d is a plane or an arc surface. In this embodiment, the second groove wall 321d is a plane. Of course, in other alternative embodiments, the second groove wall 321d can also be a plane.

[0078] Understandably, when the locking member 321 rotates towards the locking position in the locking direction, the first groove wall 321c first abuts against the circumferential surface of the locking pin 311. When the locking member 321 rotates to the locking position, the second groove wall 321d also abuts against the circumferential surface of the locking pin 311, thereby achieving the locking action. When the locking member 321 rotates towards the unlocking position in the unlocking direction, the second groove wall 321d first disengages from the circumferential surface of the locking pin 311. When the locking member 321 rotates to the unlocking position, the first groove wall 321c also disengages from the circumferential surface of the locking pin 311, thereby achieving the unlocking action. Since the first groove wall 321c is set as an arc surface, it can be ensured that when the locking member 321 rotates in the locking or unlocking direction, the locking pin 311 can accurately engage in or disengage from the locking groove 321b, thereby completing the locking and unlocking actions.

[0079] In this embodiment, the locking position of the locking member 321 is unique, which is when both the first groove wall 321c and the second groove wall 321d are in contact with the circumferential surface of the locking pin 311. The unlocking position of the locking member 321 is not unique, which is when both the first groove wall 321c and the second groove wall 321d are disengaged from the circumferential surface of the locking pin 311. If the locking member 321 continues to rotate in the unlocking direction after disengaging, the locking member 321 will always be in the unlocking position during this process. Therefore, the locking member 321 only needs to rotate to the position where both the first groove wall 321c and the second groove wall 321d are disengaged from the circumferential surface of the locking pin 311 to achieve unlocking.

[0080] Figure 6 This is a three-dimensional structural diagram of the free end of the boarding ladder in an embodiment of the present invention.

[0081] like Figure 5 and Figure 6 As shown, the lock box assembly 32 also includes a lock box body 322, which is fixedly disposed at the second end of the support arm 2 and forms a rotation space 323 with the support arm 2. The rotation space 323 has a first opening 323a on the side facing the lock seat assembly 31 and a second opening 323b on the side facing the end of the support arm 2. The locking member 321 is disposed in the rotation space 323, and its first end forms a rotational support with the support arm 2 through a fixed shaft 324. Its second end extends to the position of the first opening 323a and the second opening 323b. The unlocking operation part 321a is located at the second end of the locking member 321.

[0082] Understandably, when the locking pin 311 and the locking member 321 form a locking engagement, the locking pin 311 and the support arm 2 can be locked together, thereby achieving a locking connection between the helicopter fuselage and the boarding ladder 100. In addition, the unlocking operation part 321a is located at the position of the first opening 323a and the second opening 323b, so that the operator can apply force to the unlocking operation part 321a to make the locking member 321 rotate in the unlocking direction.

[0083] In this embodiment, the fixed shaft 324 is fixedly mounted on the support arm 2, and the first end of the locking member 321 is rotatably supported on the fixed shaft 324, so that the locking member 321 can rotate around the fixed shaft 324. In addition, the axial direction of the fixed shaft 324 is parallel to the axial direction of the locking pin 311, so that the locking pin 311 is on the rotation path of the locking member 321, so that the locking member 321 can engage or disengage with the locking pin 311 during rotation.

[0084] like Figure 6 As shown, a rotation limiting part 323c is provided on the side wall of the rotation space 323 opposite to the first opening 323a. The part of the support arm 2 that serves as the side wall of the rotation space 323 constitutes the rotation limiting part 323c. When the side wall of the locking member 321 opposite to the side wall where the unlocking operation part 321a is located abuts against the rotation limiting part 323c in the rotation direction, the locking member 321 is in the unlocked position.

[0085] Understandably, the setting of the rotation limit part 323c makes it easier for operators to perform unlocking operations and saves more effort. At the same time, it can serve as a prompt when the locking part 321 is rotated to the unlock position, and can also prevent excessive force from causing the locking part 321 to rotate too much, thereby extending the service life of the rotation reset part 33.

[0086] Figure 7 This is a partial structural diagram of the boarding ladder in its open state according to an embodiment of the present invention.

[0087] like Figure 1 and Figure 7 As shown, the support arm 2 is curved and matches the surface contour of the helicopter fuselage. The lock box body 322 has a transition part 322a and abutment part 322b on the same side as the lower surface of the support arm 2 when it is in the open position. The transition part 322a is located between the support arm 2 and the abutment part 322b. The transition part 322a is a curved surface that matches the surface contour of the support arm 2. The abutment part 322b is a plane. When the support arm 2 is in the open position, the abutment part 322b is horizontal.

[0088] Understandably, this design ensures a high degree of fit between the boarding ladder 100 and the helicopter fuselage surface when the ladder is retracted, which is not only aesthetically pleasing but also provides high safety. When the boarding ladder 100 is open, it can stably rest against the ground via the abutment part 322b, and the boarding ladder 100 has a large contact area with the ground. At the same time, the contact surface is flat, which can improve the load-bearing capacity of the boarding ladder 100. In addition, the design of the transition part 322a can enhance the overall aesthetics of the boarding ladder 100 and avoid the generation of sharp corners.

[0089] Figure 8 This is a schematic diagram of the cooperation structure between the lock seat assembly and the lock box assembly in an embodiment of the present invention.

[0090] like Figure 8 As shown, the rotation reset member 33 is a torsion spring, which is sleeved on the fixed shaft 324. One end of the spring abuts against the inner wall of the lock box body 322, and the other end abuts against the side wall opposite to the side wall where the unlocking operation part 321a is located in the rotation direction of the locking member 321. When the locking member 321 is in the locked position, the rotation reset member 33 is in a compressed state.

[0091] Understandably, when the locking member 321 is in the locked position, the spring force of the rotating reset member 33 causes the locking pin 311 to remain engaged with the locking groove 321b, thereby locking the boarding ladder 100 in the retracted state. When the external force on the locking member 321 is removed, the locking member 321 rotates in the locking direction under the spring force of the rotating reset member 33 until the locking pin 311 is engaged in the locking groove 321b, thereby achieving automatic locking.

[0092] Figure 9 This is a three-dimensional structural diagram of the lock seat assembly in an embodiment of the present invention.

[0093] like Figure 9 As shown, the lock seat assembly 31 also includes a lock seat body 312 and a movable seat 313. The lock seat body 312 is fixedly mounted on the fuselage surface of the helicopter, and the movable seat 313 is movably mounted on the surface of the lock seat body 312. The movable seat 313 can be adjusted in position relative to the lock seat body 312. The movable seat 313 has a support portion 313a extending toward the side away from the lock seat body 312, and the lock pin 311 is fixedly mounted on the extension end of the support portion 313a.

[0094] Understandably, the locking pin 311 is located at the extension end of the support 313a, which facilitates the engagement of the locking pin 311 with the locking member 321 and avoids interference. In addition, when the position of the movable seat 313 is adjusted, it can drive the locking pin 311 to move synchronously, thereby adjusting the position of the locking pin 311 relative to the locking member 321, thus eliminating errors generated during installation or use, thereby ensuring the accuracy and smoothness of locking.

[0095] In this embodiment, the lock seat body 312 and the movable seat 313 are connected by screws. The movable seat 313 has a waist-shaped hole 313b for the screw to pass through. The waist-shaped hole 313b extends radially parallel to the lock pin 311, so that after the screw is loosened, the movable seat 313 can move radially parallel to the lock pin 311, thereby changing the height position of the lock pin 311 relative to the locking member 321, so as to achieve accurate engagement between the lock pin 311 and the locking member 321.

[0096] Figure 10 This is a three-dimensional structural diagram of the mounting base in an embodiment of the present invention.

[0097] like Figure 10 As shown, the mounting base 1 is fixedly installed on the skin of the helicopter fuselage. The mounting base 1 has a rotating groove 12 with openings on both sides. A connecting shaft 11 is fixedly provided between the two end walls of the rotating groove 12. The first end of the support arm 2 extends into the rotating groove 12 and is rotatably connected to the connecting shaft 11, so that the support arm 2 can rotate around the connecting shaft 11, thereby enabling the support arm 2 to rotate between the retracted position and the open position.

[0098] In this embodiment, the two side walls of the rotating groove 12 in the rotation direction of the support arm 2 respectively form a first limiting part 121 and a second limiting part 122. The first limiting part and the second limiting part can block the support arm 2 in the rotation path, thereby limiting the maximum angle of rotation of the support arm 2 around the connecting shaft 11, so that the operator can rotate the support arm 2 to the retracted position or the open position.

[0099] The role and effect of the embodiments

[0100] According to the lock and boarding ladder involved in this embodiment, the boarding ladder includes a mounting base, a support arm, a step assembly, and a lock. The lock includes a lock seat assembly, a lock box assembly, and a rotation reset member. The lock seat assembly has a lock pin, and the lock box assembly has a locking member for engaging or disengaging with the lock pin. One of the two side walls of the locking member in the rotation direction has an unlocking operation part. When the boarding ladder is in the retracted state and locked by the lock, the unlocking operation part faces the fuselage surface of the helicopter. Since the unlocking operation part faces the fuselage surface of the helicopter when the boarding ladder is in the retracted state, an external unlocking is formed. This makes it easier to achieve locking when the air pressure around the helicopter increases due to weapon firing. Under the action of air pressure, the locking member tends to rotate in the locking direction, which is more conducive to achieving locking. This can effectively prevent the boarding ladder from mis-locking under the action of air pressure, thereby meeting the needs of military use.

[0101] Furthermore, the side wall of the locking component where the unlocking operation part is located has a locking groove that matches the locking pin. During the process of the locking component rotating in the locking direction to the locking position, the locking pin engages in the locking groove and forms a block in the rotation path of the locking component. Through the engagement between the locking pin and the locking groove, and under the action of the rotation reset component, the locking pin and the locking groove remain engaged, thereby achieving the locking engagement between the locking pin and the locking component, thus achieving the locking connection between the helicopter fuselage and the boarding ladder. During the process of the locking component rotating in the unlocking direction to the unlocking position, the locking pin disengages from the locking groove, thereby releasing the locking engagement between the locking pin and the locking component, thus releasing the locking connection between the helicopter fuselage and the boarding ladder. By using the locking pin and locking groove engagement method, locking and unlocking operations can be performed quickly and conveniently.

[0102] The above embodiments are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Therefore, all equivalent changes made in accordance with the structure, shape, and principle of the present invention should be covered within the scope of protection of the present invention.

Claims

1. A locking device, disposed within a retractable and openable boarding ladder, for locking the boarding ladder to the fuselage of a helicopter in the retracted state, characterized in that, include: A locking assembly (31) is provided on the fuselage surface of a helicopter and has at least a locking pin (311). A lock box assembly (32) is provided at the free end of the boarding ladder, having at least a locking element (321) for engaging or disengaging with the lock pin (311); The locking member (321) can rotate between the locked position where the locking member (321) and the locking pin (311) form a locking engagement and the unlocked position where the locking member (321) and the locking pin (311) are released from the locking engagement; One of the two side walls of the locking member (321) in the rotation direction has an unlocking operation part (321a). When the unlocking operation part (321a) is subjected to an external force from its side wall toward the other side wall, the locking member (321) rotates in the unlocking direction; and Rotate the reset member (33) to give the locking member (321) a tendency to rotate in the locking direction. When the boarding ladder is in the retracted state and locked by the lock (3), the unlocking operation part (321a) faces the fuselage surface of the helicopter; The locking pin (311) is fixedly disposed at one end of the locking seat assembly (31) facing away from the surface of the helicopter fuselage and extends horizontally. The side wall of the locking member (321) where the unlocking operation part (321a) is located has a locking groove (321b) that matches the locking pin (311). The locking groove (321b) is formed by a portion of the side wall of the locking member (321) being recessed inward. During the process of the locking member (321) rotating to the locking position along the locking direction, the locking pin (311) engages in the locking groove (321b) and forms an obstruction on the rotation path of the locking member (321). As the locking member (321) rotates to the unlocking position along the unlocking direction, the locking pin (311) disengages from the locking groove (321b).

2. The lock according to claim 1, characterized in that: in, The locking groove (321b) has a first groove wall (321c) and a second groove wall (321d), wherein the tangent of the first groove wall (321c) and the tangent of the second groove wall (321d) form an acute angle. When the locking member (321) is in the locked position, both the first groove wall (321c) and the second groove wall (321d) abut against the circumferential surface of the locking pin (311).

3. The lock according to claim 2, characterized in that: in, The first groove wall (321c) extends toward the side where the locking pin (311) is located relative to the second groove wall (321d). The first groove wall (321c) is an arc surface, and the second groove wall (321d) is a plane or an arc surface.

4. A boarding ladder, installed on the fuselage surface of a helicopter, for allowing personnel to board the helicopter fuselage for maintenance work, characterized in that... include: Mounting bracket (1) is fixedly installed on the surface of the helicopter fuselage; The support arm (2) has a first end hinged to the mounting base (1) and a second end extending upward to form the free end of the boarding ladder. The support arm (2) can rotate between the retracted position and the open position around its hinge point with the mounting base (1). The pedal assembly is connected to the support arm (2); as well as Lock (3) for locking the boom member (2) to the fuselage of the helicopter when the boom member (2) is in the retracted position. When the support arm (2) is in the retracted position, the boarding ladder is in a retracted state. When the support arm (2) is in the open position, the boarding ladder is in the open state. The lock (3) is the lock as described in any one of claims 1-3.

5. The boarding ladder according to claim 4, characterized in that: in, The lock box assembly (32) further includes a lock box body (322), which is fixedly disposed at the second end of the support arm (2) and forms a rotation space (323) with the support arm (2). The rotation space (323) has a first opening (323a) on the side facing the lock seat assembly (31) and a second opening (323b) on the side facing the end of the support arm (2). The locking member (321) is disposed in the rotation space (323), and its first end forms a rotational support with the support arm (2) through a fixed shaft (324), and its second end extends to the positions of the first opening (323a) and the second opening (323b). The unlocking operation part (321a) is located at the second end of the locking member (321).

6. The boarding ladder according to claim 5, characterized in that: in, A rotation limiting part (323c) is provided on the side wall of the rotation space (323) opposite to the first opening (323a). The rotation limiting part (323c) is formed by the part of the support arm (2) that serves as the side wall of the rotation space (323). When the side wall opposite to the side wall where the unlocking operation part (321a) is located in the rotation direction of the locking member (321) abuts against the rotation limiting part (323c), the locking member (321) is in the unlocked position.

7. The boarding ladder according to claim 5 or 6, characterized in that: in, The support arm (2) is curved and matches the surface contour of the helicopter fuselage. The lock box body (322) has a transition portion (322a) and an abutment portion (322b) on the same side as the lower surface of the support arm (2) when it is in the open position. The transition portion (322a) is located between the support arm (2) and the abutment portion (322b). The transition portion (322a) is a curved surface that matches the surface contour of the support arm (2), and the abutment portion (322b) is a flat surface. When the support arm (2) is in the open position, the abutment (322b) is in a horizontal state.

8. The boarding ladder according to claim 5 or 6, characterized in that: in, The rotating reset member (33) is a torsion spring, which is sleeved on the fixed shaft (324). One end of the spring abuts against the inner wall of the lock box body (322), and the other end abuts against the side wall opposite to the side wall where the unlocking operation part (321a) is located in the rotation direction of the locking member (321).

9. The boarding ladder according to claim 4, 5, or 6, characterized in that: in, The lock seat assembly (31) also includes a lock seat body (312) and a movable seat (313). The lock seat body (312) is fixedly mounted on the fuselage surface of the helicopter, and the movable seat (313) is movably mounted on the surface of the lock seat body (312). The movable seat (313) can be adjusted in position relative to the lock seat body (312). The movable seat (313) has a support portion (313a) extending toward a side away from the lock seat body (312), and the lock pin (311) is fixedly disposed at the extended end of the support portion (313a).

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