An aircraft launch system and an aircraft

Abstract

The application belongs to the field of aircraft auxiliary take-off equipment, and particularly relates to an aircraft launching system and an aircraft. The aircraft launching system comprises a driving part I and a fixed releasing mechanism. The output end of the driving part I has a circular circumferential rotation stroke or a linear movement stroke. The fixed releasing mechanism comprises a support, a fixed releasing rod and two connecting rods, and the support, the fixed releasing rod and the two connecting rods form a parallelogram mechanism. The support is arranged opposite to the fixed releasing rod. The support is connected with the output end of the driving part I. The fixed releasing rod is provided with a fixed releasing structure for fixing and releasing the aircraft. The fixed releasing mechanism formed by the parallelogram mechanism can lower the fixed releasing rod to leave a flight space when the aircraft takes off, so that the aircraft can be prevented from colliding with the fixed releasing mechanism when taking off, and the use safety of the launching system is improved.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft auxiliary take-off equipment, and in particular relates to an aircraft launching system and an aircraft. Background Art

[0002] Currently, the conventional solution for aircraft takeoff is to propel the aircraft forward using its own energy, following the runway and guide rails to reach takeoff speed. A variety of assisted takeoff devices exist, but most require complex adaption and installation mechanisms to accommodate the aircraft, reducing their applicability and increasing overall design costs. Furthermore, aircraft with tail structures are prone to collision with the assisted takeoff device, causing damage to both the aircraft and the device, posing a safety hazard. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide an aircraft launching system and an aircraft which can make room for take-off when the aircraft takes off.

[0004] The present invention provides an aircraft launching system, comprising a driving member I and a fixed release mechanism;

[0005] The output end of the driving member I has a circular rotation stroke or a linear movement stroke;

[0006] The fixing and releasing mechanism includes a support, a fixing and releasing rod, and two connecting rods, wherein the support, the fixing and releasing rod, and the two connecting rods form a parallelogram mechanism, wherein the support and the fixing and releasing rod are arranged opposite to each other;

[0007] The support is connected to the output end of the driving member I, and the fixing and releasing rod is provided with a fixing and releasing structure for fixing and releasing the aircraft.

[0008] Furthermore, the fixing and releasing mechanism also includes a driving member II for driving the parallelogram mechanism to deform.

[0009] Furthermore, the driving member II is fixedly arranged on the support, and the output end of the driving member II has a rotational stroke or a linear movement stroke, and the output end of the driving member II acts on one of the connecting rods.

[0010] Furthermore, the fixing and releasing mechanism further includes a locking member for maintaining the parallelogram mechanism state.

[0011] Furthermore, the locking member includes an electromagnet I fixedly arranged on the outside of the support and a magnetic matching structure I arranged on the corresponding connecting rod. When the electromagnet I and the magnetic matching structure I are magnetically matched, the parallelogram mechanism is in a rectangular state.

[0012] Furthermore, the fixed release structure is an electromagnet II provided at both ends of the fixed release rod, and the two electromagnet II parts corresponding to the aircraft are provided with a magnetic attraction matching structure II.

[0013] Furthermore, the driving member I includes a rotating motor and a connecting arm arranged on the output shaft of the rotating motor, and the fixing and releasing mechanism is arranged at the end of the connecting arm.

[0014] The present invention also provides an aircraft suitable for the aircraft launch system, wherein a fixing structure cooperating with the fixing release structure is provided at the bottom of the aircraft.

[0015] The aircraft further comprises a restoring mechanism, which can drive the fixed structure to retract into the fuselage of the aircraft or to retract to the inner wall of the fuselage of the aircraft.

[0016] Furthermore, the fixing structure is an arc-shaped slider, a groove is provided at the bottom of the aircraft fuselage, and a through hole is provided at the bottom of the groove that passes through the interior of the fuselage. The reset mechanism includes a sliding rod slidably arranged on the through hole and a reset spring mounted on the part of the sliding rod located inside the fuselage. The reset spring drives the sliding rod to move toward the interior of the fuselage. The arc-shaped slider is provided at the end of the sliding rod away from the reset spring, and the arc-shaped slider is adapted to the groove.

[0017] The beneficial effect of the present invention is that, by setting a fixed release mechanism composed of a parallelogram mechanism, the present invention can realize that when the aircraft takes off, the fixed release rod descends to make flight space, thereby preventing the aircraft from colliding with the fixed release mechanism when taking off, thereby improving the safety of the launch system. In addition, by setting a fixed release mechanism composed of a parallelogram mechanism, since the fixed release rod descends to make flight space when the aircraft takes off, the launch system will not limit the structure of the aircraft.

[0018] Specifically, when the driving member I moves in a straight line, the speed will suddenly stop when the output end of the driving member I reaches the limit position. At this time, the parallelogram mechanism can be deformed by inertia, that is, after it is in place, the fixed release rod is lowered by inertia, so that the timeliness of the descent of the fixed release rod can be guaranteed without the need for a separate driving device. Similarly, when the driving member I moves in a circular motion, the fixed release mechanism releases the aircraft when the output end of the driving member I reaches the set speed, and then the driving member I quickly decelerates. At this time, the parallelogram mechanism can also be deformed by inertia, that is, after it is in place, the fixed release rod is lowered by inertia, so that the timeliness of the descent of the fixed release rod can be guaranteed without the need for a separate driving device.

[0019] The present invention has a simple and reliable overall structure, enabling small aircraft to achieve the required initial velocity for flight without consuming their own energy. For unpowered aircraft, which lack an engine and therefore do not require supporting facilities such as engine ignition devices and power supplies, this significantly reduces the aircraft's mass, allowing its flight speed to be provided by the launch system. For powered aircraft, this approach also provides the initial velocity required for flight stability, reducing the aircraft's weight while still meeting required speed and other indicators. Therefore, the present invention can also reduce the aircraft's mass and structural complexity, enabling greater flight speeds and longer distances. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Attachment Figure 1 It is a structural schematic diagram of the present invention;

[0021] Attachment Figure 2 It is a structural schematic diagram of the fixing and releasing mechanism in the present invention;

[0022] Attachment Figure 3 This is a schematic diagram of the aircraft in the present invention in preparation for takeoff;

[0023] Attachment Figure 4 This is a schematic diagram of the state of the aircraft during takeoff in the present invention;

[0024] Attachment Figure 5 This is a schematic diagram of the state of the aircraft after taking off in the present invention;

[0025] Attachment Figure 6 is a front view of the aircraft of the present invention;

[0026] Attachment Figure 7 is a front sectional view of the aircraft of the present invention;

[0027] Attachment Figure 8 for Figure 7 Schematic diagram of the pre-takeoff preparation state at A in the middle;

[0028] Attachment Figure 9 for Figure 7 Schematic diagram of the state after takeoff at point A in the middle.

[0029] In the figure, 1-driving member I; 11-rotating motor; 12-connecting arm; 13-reducer; 14-balancing mechanism; 2-fixed release mechanism; 21-support; 22-fixed release rod; 221-limiting groove; 23-connecting rod; 24-driving member II; 25-locking member; 26-electromagnet II; 3-controller; 4-aircraft; 41-arc-shaped slider; 42-groove; 43-through hole; 44-sliding rod; 441-spring fixing plate; 45-reset spring; 5-photoelectric switch transmitting end; 6-photoelectric switch receiving end. DETAILED DESCRIPTION

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0031] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the various components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0032] In addition, the terms "first," "second," and so on, used in this disclosure are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referenced. Thus, a feature specified as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of this disclosure, "plurality" means at least two, such as two or three, unless otherwise specifically defined.

[0033] In the present invention, unless otherwise specified or limited, the terms "connection" and "fixation" should be understood in a broad sense. For example, "fixation" can mean fixed connection, detachable connection, or integration; it can mean mechanical connection, electrical connection, physical connection, or wireless communication connection; it can mean direct connection or indirect connection through an intermediate medium; it can mean internal communication between two elements or interaction between two elements, unless otherwise specified. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in this field can implement it. When the combination of technical solutions is mutually contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0035] As attached Figure 1-9 As shown, the present invention provides an aircraft launching system, including a driving member I1 and a fixed release mechanism 2. The fixed release mechanism 2 is used to fix an aircraft 4 and release the aircraft 4 to allow the aircraft 4 to fly after reaching a set speed. The driving member I1 is used to provide an initial speed for the aircraft 4 fixed on the fixed release mechanism 2.

[0036] The output end of the driving member I1 has a circular rotation stroke or a linear movement stroke, that is, the driving member I1 can be a circular rotation, such as a motor, which causes the aircraft 4 to rotate circularly and accelerate before taking off, or it can be a linear movement, such as an electric cylinder, a pneumatic cylinder or a hydraulic cylinder, which causes the aircraft 4 to accelerate linearly and take off;

[0037] The fixing and releasing mechanism 2 includes a support 21, a fixing and releasing rod 22 and two connecting rods 23. The support 21, the fixing and releasing rod 22 and the two connecting rods 23 form a parallelogram mechanism, wherein the support 21 and the fixing and releasing rod 22 are arranged opposite to each other;

[0038] The support 21 is connected to the output end of the driving member I1 , and the fixing and releasing rod 22 is provided with a fixing and releasing structure for fixing and releasing the aircraft 4 .

[0039] The present invention provides a fixed release mechanism 2 composed of a parallelogram mechanism, which can realize that when the aircraft 4 takes off, the fixed release rod 22 drops to make flight space, thereby preventing the aircraft 4 from colliding with the fixed release mechanism 2 during takeoff, thereby improving the safety of the launch system. In addition, by providing a fixed release mechanism 2 composed of a parallelogram mechanism, since the fixed release rod 22 drops to make flight space when the aircraft 4 takes off, the launch system will not limit the structure of the aircraft 4. For example, when using a rocket, the tail fin at the tail of the rocket can be retained.

[0040] Specifically, when the driving member I1 moves in a straight line, the speed will stop suddenly when the output end of the driving member I1 reaches the limit position. At this time, the parallelogram mechanism can be deformed by inertia, that is, after it is in place, the fixed release rod 22 is lowered by inertia, so that the timeliness of the descent of the fixed release rod 22 can be guaranteed without the need for a separate driving device. Similarly, when the driving member I1 moves in a circular motion, when the output end of the driving member I1 reaches the set speed, the fixed release mechanism 2 releases the aircraft 4, and then the driving member I1 quickly decelerates. At this time, the parallelogram mechanism can also be deformed by inertia, that is, after it is in place, the fixed release rod 22 is lowered by inertia, so that the timeliness of the descent of the fixed release rod 22 can be guaranteed without the need for a separate driving device.

[0041] The present invention has a simple and reliable overall structure, enabling a small aircraft 4 to achieve the required initial flight velocity, typically approximately 30 m / s, without consuming its own energy. For unpowered aircraft 4, which lack an engine and therefore do not require supporting facilities such as engine ignition devices and power supplies, this significantly reduces the weight of the aircraft 4, allowing its flight velocity to be provided by the launch system. For powered aircraft 4, this approach also provides the initial velocity required for flight stability, reducing the weight of the aircraft 4 while still meeting the required speed and other indicators. Therefore, the present invention can also reduce the weight and structural complexity of the aircraft 4, enabling greater flight speeds and longer distances.

[0042] In the above embodiment, a limiting structure can be provided on the parallelogram mechanism downstream of the driving member I1 in its moving direction. This limiting structure maintains the parallelogram mechanism in a rectangular state when the driving member I1 is accelerated. When electromagnet I is provided, it also serves as a limiting structure. Furthermore, during deceleration, the parallelogram mechanism is only deformed upstream of the driving member I1 in its moving direction. This ensures that the fixed release rod 22 in the fixed release mechanism 2 descends when the aircraft 4 is released from the fixed release mechanism 2.

[0043] In one embodiment, the fixed release mechanism 2 further includes a driving member II 24 for driving the deformation of the parallelogram mechanism. In this embodiment, the deformation of the parallelogram mechanism is actively controlled by the driving member II 24, so that the descent of the fixed release rod 22 can be started before the aircraft 4 is separated from the fixed release mechanism 2, so that the separation of the aircraft 4 and the descent of the fixed release rod 22 are carried out simultaneously, further reducing the possibility of the aircraft 4 colliding with the fixed release mechanism 2 during takeoff. At the same time, a higher initial velocity of the aircraft 4 can also be provided, avoiding the possibility of collision caused by the initial velocity of the aircraft 4 being too fast and the descent speed of the fixed release rod 22 being too slow when the parallelogram mechanism is passively descended.

[0044] In one embodiment, the driving member II 24 is fixedly provided on the support 21, and the output end of the driving member II 24 has a rotational stroke or a linear movement stroke. The output end of the driving member II 24 acts on one of the connecting rods 23. The driving member II 24 can be a linear moving member or a rotary driving member. In a preferred embodiment, the driving member II 24 is a micro switch, and the rotating driving piece of the micro switch is fitted with the connecting rod 23, thereby driving the connecting rod 23 to rotate.

[0045] In one embodiment, the fixed release mechanism 2 further includes a locking member 25 for maintaining the state of the parallelogram mechanism, which can keep the parallelogram mechanism in a constant state when the driving member I1 accelerates, thereby improving the stability of the aircraft 4 during the acceleration process.

[0046] In one embodiment, the locking member 25 includes an electromagnet I fixedly arranged on the outside of the support 21 and a magnetic matching structure I arranged on the corresponding connecting rod 23. When the electromagnet I and the magnetic matching structure I are magnetically matched, the parallelogram mechanism is in a rectangular state, wherein the magnetic matching structure I can be a metal block fixedly arranged on the connecting rod 23. When the connecting rod 23 itself is made of metal, the magnetic matching structure I can be the connecting rod 23 itself. The electromagnet is used for fixing and releasing. The structure is simple and reliable, and the control is convenient and quick.

[0047] Among them, the fixing and releasing structure can be a structure such as a buckle or a clamp that can actively or passively fix and release the aircraft 4. In one preferred embodiment, the fixing and releasing structure is an electromagnet II 26 arranged at both ends of the fixing and releasing rod 22, and the two electromagnet II 26 parts corresponding to the aircraft 4 are provided with a magnetic attraction matching structure II. At this time, only two metal blocks are provided on the aircraft 4 to complete the fast and reliable fixing and release with the fixing and releasing structure, reducing the adaptability improvement of the aircraft 4. When the fuselage of the aircraft 4 is made of metal material, the fuselage of the aircraft 4 can be used as the magnetic attraction matching structure II, without the need for an additional fixing structure, further reducing the adaptability improvement of the aircraft 4. At the same time, the use of the electromagnet is stable and reliable, and the control is convenient and fast.

[0048] In one embodiment, the driving member I1 includes a rotating motor 11 and a connecting arm 12 arranged on the output shaft of the rotating motor 11, and the fixed release mechanism 2 is arranged at the end of the connecting arm 12. In this embodiment, the driving member I1 adopts a rotating motor 11. Compared with the linear drive method, the circular rotation drive is adopted, which can provide a higher speed under the same structural size, thereby providing a higher initial speed for the aircraft 4. In a specific embodiment, the driving member I1 also includes a reducer 13 arranged between the rotating motor 11 and the connecting arm 12, and a balancing mechanism 14 corresponding to the connecting arm 12 is also provided at the output end of the reducer 13 to ensure the stability of the overall rotation.

[0049] The present invention also provides an aircraft, wherein the bottom of the aircraft 4 is provided with a fixing structure that cooperates with the fixing release structure, thereby being adapted for use with the present launch system.

[0050] In one embodiment, the aircraft 4 also includes a reset mechanism, which can drive the fixed structure to retract into the fuselage of the aircraft 4 or retract to the inner wall of the fuselage of the aircraft 4. By setting the reset mechanism, the fixed structure is retracted after the fixed release structure releases the fixed structure, thereby ensuring the aerodynamic shape of the aircraft 4. In this embodiment, the fixed structure is protruding from the fuselage of the aircraft 4 when in use, so that the aircraft 4 is at a certain height away from the fixed release rod 22, which can avoid contact between other structures on the aircraft 4 and the fixed release rod 22, and can also improve the stability during fixation. By setting the reset mechanism, the fixed structure protruding from the fuselage of the aircraft 4 can be prevented from affecting the aerodynamic shape of the aircraft 4.

[0051] In one embodiment, the fixing structure is an arc-shaped slider 41, a groove 42 is provided at the bottom of the fuselage of the aircraft 4, and a through hole 43 is provided at the bottom of the groove 42, which penetrates into the interior of the fuselage. The reset mechanism includes a sliding rod 44 slidably provided on the through hole 43 and a reset spring 45 sleeved on the sliding rod 44 located inside the fuselage. In addition, a spring fixing plate 441 is further provided at the end of the sliding rod 44 located inside the fuselage. One end of the reset spring 45 abuts against the spring fixing plate 441, and the other end abuts against the inner wall of the fuselage. The return spring 45 drives the sliding rod 44 to move toward the inside of the fuselage. The arc-shaped slider 41 is arranged at the end of the sliding rod 44 away from the return spring 45, and the arc-shaped slider 41 is adapted to the groove 42. With the above structure, there is no need to equip an additional driving mechanism, and the arc-shaped slider 41 can be driven to reset by the return spring 45, so that the fuselage of the aircraft 4 remains intact and the aerodynamic shape is guaranteed. In addition, when the fixed release structure is the electromagnet II 26, the arc-shaped slider 41 is made of metal, and the arc-shaped slider 41 is the magnetic attraction matching structure II.

[0052] In addition, limiting grooves 221 adapted to the arc-shaped slider 41 can be provided at both ends of the fixed release rod 22. The limiting groove 221 is located at the upstream part of the moving direction of the driving member I1 and is provided with an opening. After the electromagnet II 26 is powered off, the arc-shaped slider 41 can be allowed to move forward. In this embodiment, the electromagnet II 26 is provided at the bottom of the limiting groove 221. Therefore, when the arc-shaped slider 41 is adsorbed on the electromagnet II 26, the arc-shaped slider 41 will protrude from the fuselage and be inserted into the limiting groove 221. At this time, when the aircraft 4 moves at high speed, its main fixing force is borne by the abutting side of the arc-shaped slider 41 and the limiting groove 221, and there is no need to rely solely on the adsorption force of the electromagnet II 26. In addition, after the electromagnet II 26 is powered off, the arc-shaped slider 41 can directly move forward through the opening to disengage from the fixed release rod 22 to complete the separation.

[0053] In one embodiment, the present invention further includes a controller 3 and a photoelectric switch, wherein the photoelectric switch transmitting end 5 is arranged on the reducer 13, the photoelectric switch receiving end 6 is arranged on the connecting arm 12, and the photoelectric switch, the driving part II 24, the electromagnet I and the electromagnet II 26 are all electrically connected to the controller 3.

[0054] The electromagnet mentioned in the present invention is preferably a power-off type electromagnet, that is, the electromagnet maintains suction force continuously when not powered, and loses magnetic force when powered, so as to maintain suction force for a long time and reduce the power consumption required for control.

[0055] The specific workflow of the present invention is:

[0056] During the preparation process before the aircraft 4 takes off, when the arc-shaped slider 41 on the aircraft 4 is attached to the electromagnet II 26, the electromagnet II 26 is in a power-off state and continuously maintains the magnetic attraction. The electromagnet II 26 firmly adsorbs the arc-shaped slider 41 to complete the fixation of the aircraft 4. At the same time, the electromagnet I is in a power-off state and continuously maintains the magnetic attraction to firmly adsorb the magnetic attraction matching structure I on the connecting rod 23, so that the parallelogram mechanism maintains a rectangular state.

[0057] During the takeoff process of the aircraft 4, the controller 3 controls the rotation of the rotary motor 11, and the rotary motor 11 drives the connecting arm 12 to rotate, thereby driving the fixed release mechanism 2 and the aircraft 4 to rotate in a circle. When the rotary motor 11 reaches the set speed, the connecting arm 12 and the aircraft 4 reach the set speed. At this time, in the next rotation cycle, when the photoelectric switch receiving end 6 receives the signal from the photoelectric switch transmitting end 5, the controller 3 controls the electromagnet I to be energized, and the electromagnet I loses its magnetism, and at the same time controls the driving part II 24 to work. When the driving part II 24 drives the fixed release rod 22 to descend, the controller 3 controls the electromagnet II 26 to be energized, and the electromagnet II 26 loses its magnetism, the fixed release mechanism 2 and the aircraft 4 are released, and the aircraft 4 completes takeoff at the set speed.

[0058] The contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

Claims

1. An aircraft launch system, characterized in that: It comprises a driving member I (1) and a fixing and releasing mechanism (2); The output end of the driving member I (1) has a circular rotation stroke or a linear movement stroke; The fixing release mechanism (2) comprises a support (21), a fixing release rod (22) and two connecting rods (23), wherein the support (21), the fixing release rod (22) and the two connecting rods (23) form a parallelogram mechanism, wherein the support (21) and the fixing release rod (22) are arranged opposite to each other; The support (21) is connected to the output end of the driving member I (1), and the fixing and releasing rod (22) is provided with a fixing and releasing structure for fixing and releasing the aircraft (4); When the aircraft (4) takes off, the parallelogram mechanism can deform to cause the fixed release rod (22) to descend, thereby making room for flight.

2. The aircraft launch system according to claim 1, wherein: The fixing and releasing mechanism (2) further comprises a driving member II (24) for driving the parallelogram mechanism to deform.

3. The aircraft launch system according to claim 2, wherein: The driving member II (24) is fixedly arranged on the support (21), and the output end of the driving member II (24) has a rotation stroke or a linear movement stroke, and the output end of the driving member II (24) acts on one of the connecting rods (23).

4. The aircraft launch system according to claim 1, wherein: The fixing and releasing mechanism (2) further comprises a locking member (25) for maintaining the parallelogram mechanism state.

5. The aircraft launch system according to claim 4, characterized in that: The locking member (25) comprises an electromagnet I fixedly arranged on the outside of the support (21) and a magnetic attraction matching structure I arranged on the corresponding connecting rod (23). When the electromagnet I and the magnetic attraction matching structure I are magnetically matched, the parallelogram mechanism is in a rectangular state.

6. The aircraft launch system according to claim 1, wherein: The fixed release structure is an electromagnet II (26) arranged at both ends of the fixed release rod (22), and the two electromagnet II (26) parts corresponding to the aircraft (4) are provided with a magnetic attraction matching structure II.

7. The aircraft launch system according to any one of claims 1 to 6, characterized in that: The driving member I (1) comprises a rotating motor (11) and a connecting arm (12) arranged on an output shaft of the rotating motor (11), and the fixing and releasing mechanism (2) is arranged at an end of the connecting arm (12).

8. An aircraft suitable for the aircraft launch system according to any one of claims 1 to 7, characterized in that: The bottom of the aircraft (4) is provided with a fixing structure that cooperates with the fixing release structure.

9. The aircraft according to claim 8, characterized in that: It also includes a reset mechanism, which can drive the fixed structure to retract into the fuselage of the aircraft (4) or retract to the inner wall of the fuselage of the aircraft (4).

10. The aircraft according to claim 9, characterized in that: The fixing structure is an arc-shaped slider (41), a groove (42) is provided at the bottom of the fuselage of the aircraft (4), a through hole (43) is provided at the bottom of the groove (42) and passes through the interior of the fuselage, the reset mechanism includes a sliding rod (44) slidably arranged on the through hole (43) and a reset spring (45) sleeved on the sliding rod (44) located in the interior of the fuselage, the reset spring (45) drives the sliding rod (44) to move toward the interior of the fuselage, the arc-shaped slider (41) is provided at one end of the sliding rod (44) away from the reset spring (45), and the arc-shaped slider (41) is adapted to the groove (42).

Images