A shock absorber for a grenade launcher used in an aircraft

Abstract

The present invention provides a shock-absorbing seat for a grenade launcher for an aircraft, comprising a base plate and a plurality of limit blocks arranged in sequence along the length direction of the base plate, a vibration space being left between each two adjacent limit blocks, two guide rods being arranged in the vibration space, and a shock-absorbing spring being sleeved on the guide rods; a base being placed in one of the vibration spaces, first sliding holes being respectively opened on both sides of the top of the base, and the two sliding holes being respectively sleeved on the two guide rods in the vibration space where the base is located, one end of the shock-absorbing spring abutting against the guide rod, and the other end abutting against the base, and the base being able to move along the guide rod. The present invention arranges the base in the shock-absorbing space to absorb the recoil generated by the grenade launch using the wire rod and the shock-absorbing spring, thereby preventing the recoil generated by the grenade launch from affecting the aircraft.

Description

Technical Field

[0001] The invention belongs to the field of launchers, and in particular relates to a shock-absorbing seat of a grenade launcher for an aircraft. Background Art

[0002] During the grenade launching process, in order to achieve multi-directional and effective strikes on the target, the grenade launcher is usually hung on an aircraft such as a drone, and the grenades are continuously launched at high altitudes to strike the target. However, during the grenade launching process, the existing launcher is prone to cause damage to the drone or other aircraft due to the recoil force generated when the grenade is launched, affecting the aircraft's mid-air flight and making it impossible to accurately strike the target. Moreover, most of the existing launchers have one launcher corresponding to one grenade warhead, which greatly limits the aircraft's ammunition load. Summary of the invention

[0003] In view of this, the present invention aims to provide a grenade launcher shock absorber for an aircraft, so as to reduce the impact of the recoil force of grenade launching on the aircraft.

[0004] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0005] A grenade launcher shock absorber for an aircraft, comprising:

[0006] A base plate and a plurality of limit blocks arranged in sequence along the length direction of the base plate, a vibration space is left between each two adjacent limit blocks, two guide rods are arranged in the vibration space, and a shock absorbing spring is sleeved on the guide rods;

[0007] A base is placed in one of the vibration spaces, and first sliding holes are respectively opened on both sides of the top of the base, and the two sliding holes are respectively sleeved on two guide rods in the vibration space where the base is located, one end of the shock-absorbing spring abuts on the guide rod, and the other end abuts on the base, and the base can move along the guide rod.

[0008] Furthermore, the launcher shock absorber seat also includes a barrel rack, which is placed in another vibration space, and guide ears are extended upward on both sides of the top of the barrel rack respectively, and a second sliding hole is opened on the guide ear. The second sliding hole is sleeved on the guide rod of the vibration space where the barrel rack is located, and one end of the shock absorbing spring on the guide rod is against the barrel rack, and the other end is against the limit block.

[0009] Furthermore, the guide rods are all sleeved with guide sleeves, which are respectively inserted into the first sliding hole or the second sliding hole, and are fixedly connected to the hole wall of the first sliding hole or the second sliding hole.

[0010] Furthermore, a magazine installation space is reserved between the barrel rack and the base, and the barrel rack and the base move synchronously along the guide rod.

[0011] Furthermore, a connecting rod is arranged between the barrel rack and the base, and two ends of the connecting rod are respectively fixedly connected to the barrel rack and the base.

[0012] Furthermore, two ends of each guide rod are respectively fixedly connected to two limit blocks.

[0013] Furthermore, a barrel fixing hole is provided in the middle of the barrel rack.

[0014] Furthermore, the guide rods in the same vibration space are parallel to each other.

[0015] Furthermore, a hammer frame is fixedly arranged on the base, and the hammer frame includes two supporting plates arranged opposite to each other, and a swinging space is reserved between the two supporting plates.

[0016] Furthermore, a magazine mounting hole is provided below the barrel fixing hole.

[0017] Furthermore, the hammer frame also includes a connecting plate fixed between the two supporting plates, and a fixing hole corresponding to the magazine mounting hole is opened in the middle of the connecting plate.

[0018] Compared with the prior art, the aircraft grenade launcher shock absorber of the present invention has the following advantages:

[0019] The present invention arranges the base in the shock-absorbing space and uses the wire rod and the shock-absorbing spring to absorb the recoil force generated by the grenade launch, thereby preventing the recoil force generated by the grenade launch from affecting the aircraft.

[0020] The barrel rack is arranged in another shock-absorbing space, and the shock-absorbing springs in different shock-absorbing spaces are used to respectively dampen the barrel rack and the base, so as to ensure the shock-absorbing effect;

[0021] The barrel frame and the base are fixedly connected by a connecting rod so that the barrel frame and the base can move synchronously to ensure the stability of the shock absorber during grenade launching. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0023] Figure 1 It is a schematic diagram of the overall structure of the transmitter;

[0024] Figure 2 This is a schematic diagram of the explosion of the overall structure of the launcher;

[0025] Figure 3 This is a schematic diagram of the launcher shock absorber structure;

[0026] Figure 4 This is a schematic diagram of the shock absorber explosion;

[0027] Figure 5 This is a schematic diagram of the explosion of the hammer assembly structure;

[0028] Figure 6 It is a schematic diagram of the coordination between the rotating wheel and the roulette wheel;

[0029] Figure 7 It is a schematic diagram of the wheel disc and the power storage rail structure;

[0030] Figure 8 This is a schematic diagram of the explosion of the firing pin and firing pin seat structure.

[0031] Description of reference numerals:

[0032] 1-magazine assembly; 11-wheel; 111-striker; 1111-impacting part; 1112-primer triggering part; 1113-section; 1114-limiting arc surface; 112-positioning groove; 113-through hole; 114-convex tooth; 115-striker seat; 1151-striker hole; 1152-limiting hole; 1153-limiting shaft; 116-reset spring; 12-rotating wheel; 121-loading chamber; 122-positioning strip; 123-connecting hole; 13-connecting pin; 131-pressing section; 132-through hole section; 133-connecting section; 14-power storage rail; 141-wedge surface; 1411-power storage edge; 142-fixing surface; 1421-inclined surface; 2-shock absorber seat; 2 1-base plate; 22-limiting block; 23-vibration space; 24-guide rod; 25-shock-absorbing spring; 26-guide sleeve; 27-base; 271-first sliding hole; 28-barrel frame; 281-guide ear; 282-second sliding hole; 283-barrel fixing hole; 284-magazine mounting hole; 29-connecting rod; 3-hammer frame; 31-support plate; 311-hanging hole; 32-connecting plate; 321-fixing hole; 33-swinging space; 4-hammer assembly; 41-inertia hammer head; 411-impact surface; 42-rotating shaft; 43-rotating arm; 44-shift lever; 45-protective cover; 46-torsion spring; 5-reduction motor; 51-gear; 6-barrel; 7-magazine mounting space. DETAILED DESCRIPTION

[0033] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0034] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0035] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0036] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0037] The launcher shock absorber for aircraft described in the present invention is suitable for installing a flat-shooting grenade launcher, and the flat-shooting grenade launcher includes

[0038] A magazine assembly 1 comprises a wheel disc 11 and a rotating wheel 12 which are coaxially arranged and can rotate synchronously, a plurality of loading cavities 121 are opened on the upper circumference of the rotating wheel 12, a plurality of firing pins 111 corresponding to the loading cavities 121 are arranged on the wheel disc 11, a positioning strip 122 is extended from the end surface of the rotating wheel 12 facing one end of the wheel disc 11, a plurality of positioning grooves 112 are opened on the surface of the wheel disc 11, the positioning strip 122 can be placed in one of the positioning grooves 112, and the length direction of the positioning groove 112 passes through the axis of the wheel disc 11, the length direction of the positioning strip 122 passes through the axis of the rotating wheel 12, a through hole 113 is opened on the upper axial side of the wheel disc 11, a connecting hole 123 is opened on the upper axial side of the rotating wheel 12, the connecting hole 123 is coaxially arranged with the through hole 113, a connecting pin 13 passes through the connecting hole 123 and the through hole 113 to connect the rotating wheel 12 and the wheel disc 11 as a whole;

[0039] The shock-absorbing seat 2 comprises a base plate 21 and a plurality of limit blocks 22 arranged in sequence along the length direction of the base plate 21, a vibration space 23 is left between each two adjacent limit blocks 22, specifically, in the present embodiment, there are three limit blocks 22 and two vibration spaces 23, a guide rod 24 is respectively provided on both sides of each vibration space 23, and a shock-absorbing spring 25 is sleeved on each guide rod 24, a base 27 is provided in one vibration space 23, a barrel rack 28 is provided in the other vibration space 23, first sliding holes 271 are respectively opened on both sides of the top of the base 27, the first sliding holes 271 are respectively sleeved on the guide rods 24 of the vibration space 23 where the base 27 is located, and one end of the shock-absorbing spring 25 in the vibration space 23 where the base 27 is located abuts against the limit block 22, and the other end abuts against the base 27 The barrel rack 28 extends upwardly with guide ears 281 on both sides, and a second sliding hole 282 is formed on the guide ear 281, and the second sliding hole 282 is sleeved on the guide rod 24 of the vibration space 23 where the barrel rack 28 is located. One end of the damping spring 25 of the vibration space 23 where the barrel rack 28 is located abuts against the limit block 22, and the other end abuts against the guide ear 281 of the barrel rack 28, and the base 27, the barrel rack 28 and the magazine assembly 1 can all move synchronously. Specifically, a magazine installation space 7 is reserved between the barrel rack 28 and the base 27, and the magazine assembly 1 is placed in the magazine installation space 7, and the base 27 and the barrel rack 28 can move synchronously along the length direction of the damping spring 25 in the vibration space 23, and when recoil is generated during grenade firing, the kinetic energy of the recoil can be converted into elastic potential energy of the spring.

[0040] A hammer frame 3 is fixedly disposed at the lower part of the base 27, and the hammer frame 3 includes two supporting plates 31 and a connecting plate 32 that are arranged opposite to each other, and a swinging space 33 is reserved between the supporting plates 31. The connecting plate 32 is fixedly disposed at one end of the connecting plate 32 close to the magazine, and a hammer assembly 4 is built in the swinging space 33, which includes a rotating shaft 42, a rotating arm 43, and an inertia hammer head 41 fixedly disposed on the rotating arm 43. The inertia hammer head 41 can swing around the rotating shaft 42, and an impact surface 411 is disposed on one end surface of the inertia hammer head 41. When the inertia hammer head 41 rotates around the rotating shaft 42, the impact surface 411 can strike the end of the firing pin 111.

[0041] A plurality of force storage rails 14 are fixedly arranged on the circumference of the disk surface of the wheel disc 11 facing the hammer assembly 4, and the striker 111 is respectively placed between two adjacent force storage rails 14, and the force storage rail 14 includes a wedge surface 141, and the wedge surface 141 is vertically arranged with the disk surface of the wheel disc 11, and the wedge surface 141 includes an inclined force storage edge 1411; the hammer assembly 4 also includes a lever 44, when the wheel disc 11 rotates, the side wall of the lever 44 can be tightly pressed against the force storage edge 1411, and drive the inertia hammer head 41 and the rotating arm 43 away from the wheel disc 11, and a torsion spring 46 is also arranged in the swing space 33, and the torsion spring 46 The main body is sleeved on the rotating shaft 42 of the pendulum, and a hanging hole 311 is respectively opened on the two support plates 31. The torsion arms at both ends of the torsion spring 46 are respectively hooked on the hanging holes 311, and the torsion arm in the middle of the torsion spring 46 is tightly against the rotating arm 43. During the rotation of the wheel disc 11, the lever 44 can move to the top of the force storage edge 1411, and the torsion spring 46 is tightened. As the wheel disc 11 continues to rotate, the lever 44 disengages from the force storage edge 1411, and the torsion spring 46 drives the rotating arm 43 and the inertia hammer head 41 to move toward the wheel disc 11, so that the impact surface 411 has enough force to knock the firing pin 111 to trigger the primer of the grenade in the magazine and launch the grenade.

[0042] In order to reduce the friction between the protective cover 45 and the force storage edge 1411, the force storage edge 1411 is rounded, and the force storage guide rail 14 also includes a fixed surface 142, which is fixedly connected to the disk surface of the wheel disc 11, and an inclined surface 1421 is provided at the end of the fixed surface 142. The angle between the inclined surface 1421 and the disk surface of the wheel disc 11 is the same as the angle between the force storage edge 1411 and the disk surface of the wheel disc 11, so as to facilitate the movement of the lever 44 and the protective cover 45 from the wheel disc 11 to the force storage guide rail 14. The lever 44 is fixed on the inertia hammer head 41, and in order to protect the lever 44, a protective cover 45 that can rotate along its axis is sleeved on the lever 44, and the outer wall of the protective cover 45 is tangent to the plane where the impact surface 411 is located.

[0043] A barrel fixing hole 283 is opened in the middle of the barrel frame 28, and the barrel fixing hole 283 is fixedly connected to the end of a barrel 6, and the barrel 6 can be connected to the loading chamber respectively. Specifically, when the impact surface 411 hits the firing pin 111, the wheel 11 needs to rotate another 1°, and the barrel 6 can be opposite to the loading chamber 121 corresponding to the struck firing pin 111, so that the grenade can be ejected from the barrel 6 after the primer is triggered.

[0044] The connecting pin 13 includes a pressing section 131, a through-hole section 132 and a connecting section 133. The diameter of the pressing section 131 is larger than that of the through-hole section 132. The connecting section 133 is threaded. The through-hole section 132 can pass through the through hole 113 and the connecting hole 123. The pressing section 131 can be tightly pressed against the end surface of the side wall of the connecting hole 123 and is screwed with the connecting section 133 through a nut so that the rotating wheel 12 and the wheel disc 11 are connected as a whole. Specifically, the barrel frame 28 has a magazine mounting hole 284 below the barrel fixing hole 283. The connecting A fixing hole 321 is formed on the connecting plate 32, the connecting pin 13 passes through the magazine mounting hole 284, the connecting hole 123, the through hole 113 and the fixing hole 321, and the pressing section 131 is tightly pressed against the barrel frame 28, the connecting section 133 is screwed with a nut, and the nut is tightly pressed against the connecting plate 32, a connecting rod 29 is arranged between the barrel frame 28 and the base 27, and the two ends of the connecting rod 29 are fixedly connected to the barrel frame 28 and the base 27 respectively, and the magazine assembly 1, the barrel frame 28 and the base 27 are connected as a whole through the two connecting rods 29 and the connecting pin 13.

[0045] The convex teeth 114 are uniformly extended outward from the circumference of the wheel disc 11 . A reduction motor 5 is fixedly disposed on the side of the wheel disc 11 . A gear 51 is coaxially fixedly disposed on the output shaft of the reduction motor 5 . The gear 51 meshes with the convex teeth 114 of the wheel disc 11 .

[0046] The wheel disc 11 is provided with a firing pin seat 115, and the firing pin seat 115 is provided with a firing pin hole 1151 corresponding to the loading chamber 121, and the firing pin hole 1151 is a stepped hole, the firing pin 111 is placed in the firing pin hole 1151, and the firing pin hole 1151 is provided with a return spring 116, the firing pin 111 includes a striking portion 1111 and a primer triggering portion 1112, and the diameter of the striking portion 1111 is larger than the primer triggering portion 1112, so that a shoulder is formed between the primer triggering portion 1112 and the striking portion 1111, one end of the return spring 116 abuts against the shoulder, and the other end abuts against the step of the firing pin hole 1151, and the striking portion 1111 is provided with a return spring 116. A section 1113 is formed on the side wall of the bolt 111 along the length direction, and the bottom end of the section 1113 is tangent to a limiting arc surface 1114. A limiting hole 1152 is formed on the firing pin seat 115 along the chord direction, and a limiting shaft 1153 passes through the limiting hole 1152. When the return spring 116 is in a relaxed state, the limiting arc surface 1114 abuts against the side wall of the limiting shaft 1153. When the firing pin 111 is not subjected to external force, the firing pin 111 limits itself through the cooperation of the limiting arc surface 1114 and the limiting shaft 1153. When the hammer assembly 4 strikes the firing pin 111, the firing pin 111 moves into the firing pin hole 1151 and strikes the primer of the grenade in the loading chamber 121.

[0047] A guide sleeve 26 is sleeved on each guide rod 24, and the guide sleeve 26 is respectively inserted into the first sliding hole 271 or the second sliding hole 282, and the guide sleeve 26 is fixed to the hole wall of the first sliding hole 271 or the second sliding hole 282, and two guide rods 24 are arranged in the same vibration space 23, and the two guide rods 24 are parallel to each other.

[0048] During use of the flat-fire grenade launcher described in the present invention, grenades are filled into the loading chamber 121, and then the rotating wheel 12 is placed in the magazine installation space 7, and the positioning strip 122 of the rotating wheel 12 corresponds to the positioning groove 112 of the wheel disc 11, so that each firing pin 111 can correspond to a loading chamber 121 respectively, and then the rotating wheel 12 and the wheel disc 11 are connected as a whole by the connecting pin 13 to prevent the rotating wheel 12 from falling off; when it is necessary to launch a grenade, the reduction motor 5 drives the wheel disc 11 and the rotating wheel 12 to rotate. During this process, as the wheel disc 11 rotates, the lever 44 drives the inertia hammer 41 away from the wheel disc 11 along the power storage edge 1411 of the power storage guide rail 14, until the lever 44 moves to the end of the power storage edge 1411, and the lever 44 is disengaged from the power storage guide rail 14, and the torsion spring 46 drives the inertia hammer 41 to strike the firing pin 111, triggering the primer of the grenade to launch the grenade.

[0049] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A shock absorber for a grenade launcher for an aircraft, Features: include A base plate (21) and a plurality of limit blocks (22) arranged in sequence along the length direction of the base plate (21), a vibration space (23) being reserved between each two adjacent limit blocks (22), two guide rods (24) being arranged in the vibration space (23), and a shock absorbing spring (25) being sleeved on the guide rods (24); A base (27) is placed in one of the vibration spaces (23), and first sliding holes (271) are respectively opened on both sides of the top of the base (27), and the two first sliding holes (271) are respectively sleeved on two guide rods (24) of the vibration space (23) where the base (27) is located, one end of the damping spring (25) abuts against the guide rod (24), and the other end abuts against the base (27), and the base (27) can move along the guide rod (24); It also includes a gun barrel frame (28) which is placed in another vibration space (23), and guide ears (281) are extended upwards on both sides of the top of the gun barrel frame (28), and a second sliding hole (282) is formed on the guide ear (281), and the second sliding hole (282) is sleeved on a guide rod (24) of the vibration space (23) where the gun barrel frame (28) is located, and a damping spring (25) on the guide rod (24) has one end abutting against the gun barrel frame (28) and the other end abutting against the limit block (22); A magazine installation space (7) is reserved between the barrel frame (28) and the base (27), and the barrel frame (28) and the base (27) move synchronously along the guide rod (24); The guide rods (24) are each sleeved with a guide sleeve (26), the guide sleeve (26) being inserted into the first sliding hole (271) or the second sliding hole (282) respectively, and the guide sleeve (26) is fixedly connected to the hole wall of the first sliding hole (271) or the second sliding hole (282).

2. A shock absorber for a grenade launcher for an aircraft according to claim 1, Features: A connecting rod (29) is arranged between the gun barrel frame (28) and the base (27), and two ends of the connecting rod (29) are respectively fixedly connected to the gun barrel frame (28) and the base (27).

3. The shock absorber for a grenade launcher for an aircraft according to claim 1, Features: Both ends of each guide rod (24) are respectively fixedly connected to two limit blocks (22).

4. The shock absorber for a grenade launcher for an aircraft according to claim 1, Features: A gun barrel fixing hole (283) is formed in the middle of the gun barrel frame (28).

5. The shock absorber for a grenade launcher for an aircraft according to claim 1, Features: A hammer frame (3) is fixedly arranged on the base (27), and the hammer frame (3) comprises two supporting plates (31) arranged opposite to each other, and a swinging space (33) is reserved between the two supporting plates (31).

6. A shock absorber for a grenade launcher for an aircraft according to claim 4, Features: A magazine mounting hole (284) is provided below the gun barrel fixing hole (283).

7. A shock absorber for a grenade launcher for an aircraft according to claim 6, Features: The hammer frame (3) also includes a connecting plate (32) fixedly arranged between the two supporting plates (31), and a fixing hole (321) corresponding to the magazine mounting hole (284) is opened in the middle of the connecting plate (32).

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