Aircraft windproof locking device

Abstract

The embodiment of the invention relates to an aircraft windproof locking device which comprises a first connecting piece used for being connected to the tail of an aircraft; the second connecting piece is detachably connected to the first connecting piece and used for being connected to a launching pad; the adjusting mechanism is connected to the second connecting piece, the adjusting mechanism has a first state and a second state, and under the condition that the aircraft is launched before being launched, the adjusting mechanism is in the first state, and the adjusting mechanism adjusts the second connecting piece to be locked to the first connecting piece; under the condition that the aircraft is ignited and launched, the adjusting mechanism is in a second state, and the adjusting mechanism adjusts the second connecting piece to be separated from the first connecting piece. In this way, on one hand, the aircraft is always fixed to the launching pad before ignition; on the other hand, it is guaranteed that after the aircraft is ignited, the aircraft can be smoothly separated from the launching pad and launched, the rocket body and the launching pad do not need to be manually separated, excessive dependence on the operation level of workers is not needed, potential safety hazards are reduced, and reliability is improved.

Description

Technical Field

[0001] The embodiments of the present application relate to the technical field of aircraft launch windproof accessories, and in particular, to an aircraft windproof locking device. Background Art

[0002] Before the launch of the aircraft, the body of the aircraft stands upright on the launch pad. To prevent the body from tilting and standing unstable due to strong winds or other reasons, windproof bolts are usually used to fix the body on the launch pad. The windproof bolts are removed by the staff just before the aircraft is ignited, and the body stands upright on the launch pad by its own weight. This fixing method is time-consuming and labor-intensive, and has safety hazards. It depends on the operating level of the staff. Moreover, if the wind is strong at the launch site after the windproof bolts are removed, the body of the aircraft will still tilt and stand unstable, and the reliability is poor. Summary of the invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art or related art.

[0004] To this end, the present invention provides an aircraft windproof locking device.

[0005] In view of this, according to an embodiment of the present application, an aircraft windproof locking device is proposed, comprising:

[0006] A first connecting member, used to connect to the tail of the aircraft;

[0007] A second connecting member, detachably connected to the first connecting member, for connecting to the launch platform;

[0008] An adjusting mechanism is connected to the second connecting member, and the adjusting mechanism has a first state and a second state, wherein, when the aircraft is before launching, the adjusting mechanism is in the first state, and the adjusting mechanism adjusts the second connecting member to be locked to the first connecting member; when the aircraft is in the ignition and launching state, the adjusting mechanism is in the second state, and the adjusting mechanism adjusts the second connecting member to be separated from the first connecting member.

[0009] In a feasible implementation manner, the first connecting member includes:

[0010] A bolt, used for being screwed to the tail of the above-mentioned aircraft;

[0011] The first connecting portion is connected to the bottom of the bolt along the axial direction of the bolt and is used to be connected to the second connecting member.

[0012] In a feasible implementation manner, the bolt and the first connecting portion are an integrated structure.

[0013] In a feasible implementation manner, the second connecting member includes:

[0014] A second connection part is connected to the adjustment mechanism, an oblique groove is provided on the peripheral side of the first connection part, and a connection block is provided on the second connection part, and the adjustment mechanism can drive the connection block to slide along the slope of the oblique groove;

[0015] A support portion, the adjustment mechanism is connected to the support portion, and the support portion is used to be connected to the launch platform;

[0016] Wherein, when the above-mentioned adjustment mechanism is in the above-mentioned first state, the above-mentioned connecting block presses against the bottom of the above-mentioned inclined groove; when the above-mentioned adjustment mechanism is in the above-mentioned second state, the above-mentioned connecting block slides out of the opening of the above-mentioned inclined groove along the slope of the above-mentioned inclined groove; the above-mentioned opening and the above-mentioned groove bottom are arranged opposite to each other.

[0017] In a feasible implementation manner, the second connecting member further includes:

[0018] A connecting rod is used to connect the first connecting part to the second connecting part.

[0019] In a feasible implementation manner, the connecting rod comprises:

[0020] A first threaded rod, screwed to the bottom of the second connecting portion;

[0021] A second threaded rod, threadedly connected to the top of the adjustment mechanism;

[0022] A column, one end of which is connected to the first threaded rod, and the other end of which is connected to the second threaded rod;

[0023] A hexagonal nut, sleeved on the column;

[0024] The slope of the connecting block abutting against the inclined groove can be adjusted by rotating the hexagonal nut.

[0025] In a feasible implementation manner, the threads of the first threaded rod and the threads of the second threaded rod have opposite rotation directions.

[0026] In a feasible implementation manner, the above-mentioned adjustment mechanism includes:

[0027] A pull rod, wherein the second threaded rod is screwed to the top end of the pull rod;

[0028] A rotating shaft, wherein one end of the pull rod close to the second connecting portion is rotatably connected to the supporting portion through the rotating shaft;

[0029] An adjusting rod, which is passed through an end of the pull rod away from the second connecting portion;

[0030] A tensioning belt connected to the adjusting rod, the tensioning belt being used to be arranged below the tail nozzle of the aircraft;

[0031] an elastic member, disposed between the support portion and the pull rod, wherein when the tensioning belt applies tensioning force to the pull rod, the elastic member is in a compressed state;

[0032] Among them, when the above-mentioned adjustment mechanism is in the above-mentioned first state, the above-mentioned tensioning band applies tensioning force to the above-mentioned pull rod through the above-mentioned adjustment rod, so that the above-mentioned connecting block is pressed against the bottom of the above-mentioned inclined groove; when the above-mentioned adjustment mechanism is in the above-mentioned second state, the flame ejected from the tail nozzle of the above-mentioned aircraft burns the above-mentioned tensioning band, and the above-mentioned elastic member rebounds, driving the above-mentioned pull rod to rotate, so that the above-mentioned connecting block slides out of the opening of the above-mentioned inclined groove.

[0033] In a feasible implementation manner, the tension belt comprises a nylon belt or a polyester belt.

[0034] In a feasible embodiment, the above-mentioned aircraft windproof locking device is provided in plurality, and the plurality of the above-mentioned aircraft windproof locking devices are used to be axially symmetrically arranged on the surrounding side of the above-mentioned launch pad with the center line of the above-mentioned launch pad as the axis of symmetry, wherein each of the above-mentioned aircraft windproof locking devices is connected to the corresponding above-mentioned aircraft windproof locking device through the above-mentioned tensioning belt, and the above-mentioned tensioning belt is in a tensioned state.

[0035] Compared with the prior art, the present invention at least includes the following beneficial effects: the aircraft windproof locking device provided in the embodiment of the present application is provided with a first connecting member, a second connecting member and an adjusting mechanism. Among them, the first connecting member can be connected to the tail of the aircraft, the second connecting member can be arranged on the launch platform, and the first connecting member and the second connecting member are connected so that the aircraft is vertically fixed on the launch platform, so as to avoid the aircraft body tilting due to the strong wind in the launch environment before the aircraft is launched, thereby improving stability. The adjusting mechanism can be connected to the second connecting member, and specifically, the adjusting mechanism can have a first state and a second state, wherein, when the aircraft is before launching, the adjusting mechanism is in the first state, in which the adjusting mechanism adjusts the second connecting member to lock on the first connecting member, so as to ensure that the arrow body is fixed on the launch platform; when the aircraft is in the ignition launch state, the adjusting mechanism is in the second state, in which the adjusting mechanism adjusts the second connecting member and the first connecting member to separate, so that the arrow body and the launch platform are separated, so as to ensure that the arrow body can be launched smoothly. This setting, on the one hand, ensures that the aircraft is always fixed to the launch pad before ignition; on the other hand, it ensures that after the aircraft is ignited, the aircraft can be smoothly separated from the launch pad and launched. There is no need to manually separate the rocket body and the launch pad, and there is no need to over-rely on the operating level of the staff, which reduces safety hazards and improves reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Also, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0037] Figure 1 A schematic structural diagram of an aircraft windproof locking device according to an embodiment of the present application;

[0038] Figure 2 A schematic diagram of a working state of an aircraft windproof locking device according to an embodiment of the present application;

[0039] Figure 3 A schematic diagram of another working state of an aircraft windproof locking device according to an embodiment of the present application;

[0040] Figure 4 A schematic diagram of the assembly of an aircraft windproof locking device, a launch platform and an aircraft according to an embodiment of the present application;

[0041] Figure 5 A schematic diagram of the assembly of multiple aircraft windproof locking devices according to an embodiment of the present application.

[0042] in, Figures 1 to 5 The corresponding relationship between the reference numerals and the component names is as follows:

[0043] 100 aircraft windproof locking device, 200 aircraft, 300 launch platform;

[0044] 110 first connecting member, 111 bolt, 112 first connecting portion, 113 inclined groove, 120 second connecting member, 121 second connecting portion, 122 supporting portion, 123 connecting block, 124 connecting rod, 1241 column, 1242 hexagonal nut, 130 adjusting mechanism, 131 pull rod, 132 rotating shaft, 133 adjusting rod, 134 tensioning belt, 135 elastic member. DETAILED DESCRIPTION

[0045] In order to better understand the above-mentioned technical scheme, the technical scheme of the embodiments of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the embodiments of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments may be combined with each other.

[0046] like Figures 1 to 5As shown, according to an embodiment of the present application, an air outlet structure 100 is proposed, including: a first connecting member 110, used to be connected to the tail of the aircraft 200; a second connecting member 120, detachably connected to the above-mentioned first connecting member 110, used to be connected to the launching platform 300; an adjusting mechanism 130, connected to the above-mentioned second connecting member 120, and the above-mentioned adjusting mechanism 130 has a first state and a second state, wherein, when the above-mentioned aircraft 200 is before launching, the above-mentioned adjusting mechanism 130 is in the above-mentioned first state, and the above-mentioned adjusting mechanism 130 adjusts the above-mentioned second connecting member 120 to be locked to the above-mentioned first connecting member 110; when the above-mentioned aircraft 200 is in the ignition and launching state, the above-mentioned adjusting mechanism 130 is in the above-mentioned second state, and the above-mentioned adjusting mechanism 130 adjusts the above-mentioned second connecting member 120 and the above-mentioned first connecting member 110 to separate.

[0047] It can be understood that the windproof locking device 100 for the aircraft 200 provided in the embodiment of the present application is provided with a first connecting member 110, a second connecting member 120 and an adjusting mechanism 130. Among them, the first connecting member 110 can be connected to the tail of the aircraft 200, and the second connecting member 120 can be arranged on the launch pad 300. The first connecting member 110 and the second connecting member 120 are connected to vertically fix the aircraft 200 on the launch pad 300, so as to avoid the tilt of the body of the aircraft 200 due to the strong wind in the launch environment before the aircraft 200 is launched, thereby improving stability. The adjustment mechanism 130 can be connected to the second connection member 120. Specifically, the adjustment mechanism 130 can have a first state and a second state. When the aircraft 200 is before launching, the adjustment mechanism 130 is in the first state. In this state, the adjustment mechanism 130 adjusts the second connection member 120 to lock the first connection member 110 to ensure that the arrow body is fixed to the launch pad 300. When the aircraft 200 is in the ignition and launch state, the adjustment mechanism 130 is in the second state. In this state, the adjustment mechanism 130 adjusts the second connection member 120 and the first connection member 110 to separate so that the arrow body and the launch pad 300 are separated to ensure that the arrow body can be launched smoothly. Such a setting ensures that the aircraft 200 is always fixed to the launch pad 300 before ignition. On the other hand, it ensures that after the aircraft 200 is ignited, the aircraft 200 can be smoothly separated from the launch pad 300 and launched, without the need to manually separate the arrow body from the launch pad 300, and without over-reliance on the operating level of the staff, thereby reducing safety hazards and improving reliability.

[0048] In some examples, such as Figures 1 to 3 As shown, the first connecting member 110 includes: a bolt 111 for being screwed to the tail of the aircraft 200; a first connecting portion 112 connected to the bottom of the bolt 111 along the axial direction of the bolt 111, and used to be connected to the second connecting member 120.

[0049] It is understandable that the first connecting member 110 may be provided with a bolt 111 and a first connecting portion 112. The tail of the body of the aircraft 200 is provided with a mounting edge, and a mounting hole may be provided along the axial direction of the body. The bolt 111 may be passed through the mounting hole and threadedly connected with a nut to fix the first connecting member 110 to the body. Along the axial direction of the bolt 111, the first connecting portion 112 may be connected to an end of the bolt 111 away from the tail of the flight, and the first connecting portion 112 may be connected to the second connecting member 120. The connection relationship between the second connecting member 120 and the first connecting portion 112 may be adjusted by the adjustment mechanism 130. Before the aircraft 200 is ignited, the second connecting member 120 may be locked and connected to the first connecting portion 112; when the aircraft 200 is ignited, the second connecting member 120 may be separated from the first connecting portion 112.

[0050] In some examples, the bolt 111 and the first connecting portion 112 are an integrated structure.

[0051] It is understandable that the bolt 111 and the first connecting part 112 can be processed into an integrated structure through a casting process to improve the overall structural strength of the first connecting member 110, avoid the connection between the bolt 111 and the first connecting part 112 from breaking due to strong outdoor winds when the rocket body is fixed to the launch pad 300, and improve reliability.

[0052] In some examples, such as Figures 1 to 3 As shown, the second connecting member 120 includes: a second connecting portion 121, connected to the adjusting mechanism 130, an inclined groove 113 is provided on the peripheral side of the first connecting portion 112, and the second connecting portion 121 is provided with a connecting block 123, and the adjusting mechanism 130 can drive the connecting block 123 to slide along the slope of the inclined groove 113; a supporting portion 122, and the adjusting mechanism 130 is connected to the supporting portion 122, and the supporting portion 122 is used to be connected to the launching platform 300; wherein, when the adjusting mechanism 130 is in the first state, the connecting block 123 presses against the bottom of the inclined groove 113; when the adjusting mechanism 130 is in the second state, the connecting block 123 slides out of the opening of the inclined groove 113 along the slope of the inclined groove 113; the opening and the bottom of the groove are arranged relative to each other.

[0053] It can be understood that the second connecting member 120 can be provided with a second connecting portion 121 and a supporting portion 122. Among them, the supporting portion 122 can be connected to the peripheral side of the launch platform 300, the adjustment mechanism 130 is connected to the supporting portion 122, and the second connecting portion 121 is connected to the adjustment mechanism 130, and the supporting portion 122 provides support force for the adjustment mechanism 130 and the second connecting portion 121. The overall shape of the first connecting portion 112 can be consistent with the shape of the bolt 111, which is a column 1241. The column 1241 of the first connecting portion 112 can be provided with an inclined groove 113 on the peripheral side. Specifically, a slope is provided on the side of the inclined groove 113 close to the second connecting portion 121, and the opening of the inclined groove 113 and the groove bottom of the inclined groove 113 are correspondingly arranged, and the opening size of the inclined groove 113 is larger than the groove bottom size of the inclined groove 113, that is, along the axial direction of the first connecting portion 112, the height of the slope close to the opening is lower than the height of the slope close to the groove bottom. The second connection part 121 is provided with a mounting groove, the first connection part 112 is inserted into the mounting groove, and a connection block 123 is provided on the top of the second connection part 121, and the connection block 123 protrudes from the inner side wall of the mounting groove. When the first connection part 112 is inserted into the mounting groove, the connection block 123 can abut against the slope and can move along the slope toward the opening or the bottom of the groove. The adjustment mechanism 130 can adjust the position of the connection block 123 relative to the inclined groove 113. Specifically, when the adjustment mechanism 130 is in the first state, the connection block 123 abuts against the slope and moves toward the bottom of the inclined groove 113 until the connection block 123 presses against the bottom of the groove. The connection block 123 is maintained in the locking position by the adjustment mechanism 130, so as to ensure that the second connection member 120 can be locked with the first connection member 110, and ensure that the windproof locking device 100 of the aircraft 200 can stably lock the rocket body to the launch platform 300. When the adjustment mechanism 130 is in the second state, the connecting block 123 can slide along the slope from the bottom of the inclined groove 113 to the opening until it slides out of the inclined groove 113 from the opening, so that the connecting block 123 and the inclined groove 113 are separated, and the second connecting member 120 and the first connecting member 110 are separated, so that the rocket body can be completely separated from the launching platform 300 during ignition and launch, thereby ensuring a smooth launching process.

[0054] In some examples, such as Figures 1 to 3 As shown, the second connecting member 120 further includes a connecting rod 124 , and the first connecting portion 112 is connected to the second connecting portion 121 via the connecting rod 124 .

[0055] It is understandable that the second connecting member 120 may also be provided with a connecting rod 124, and the first connecting portion 112 is connected to the second connecting portion 121 through the connecting rod 124. The position of the connecting block 123 in the height direction of the inclined groove 113 can be adjusted by adjusting the size of the connecting rod 124 between the first connecting portion 112 and the second connecting portion 121, so as to ensure that the connecting block 123 abuts against the slope of the inclined groove 113 and can slide along the slope, so as to ensure that the adjusting mechanism 130 adjusts the movement of the connecting block 123 smoothly.

[0056] In some examples, such as Figures 1 to 3 As shown, the connecting rod 124 includes: a first threaded rod, screwed to the bottom of the second connecting portion 121; a second threaded rod, screwed to the top of the adjusting mechanism 130; a column 1241, one end of the column 1241 is connected to the first threaded rod, and the other end is connected to the second threaded rod; a hexagonal nut 1242, sleeved on the column 1241; wherein, the connecting block 123 can be adjusted to abut against the slope of the inclined groove 113 by rotating the hexagonal nut 1242.

[0057] It is understandable that the connecting rod 124 may be provided with a first threaded rod, a second threaded rod, a column 1241 and a hexagonal nut 1242. The first threaded rod and the second threaded rod are respectively located at the two ends of the column 1241, and a threaded hole may be provided at the bottom end of the second connecting portion 121, and the first threaded rod may be screwed into the threaded hole to be connected to the second connecting portion 121. A threaded hole may be provided at the top of the adjusting mechanism 130, and the second threaded rod may be screwed into the threaded hole to be connected to the adjusting mechanism 130, so that the second connecting portion 121 is connected to the adjusting mechanism 130 through the connecting rod 124. The hexagonal nut 1242 may be welded to the column 1241, and by rotating the hexagonal nut 1242 with a hexagonal wrench, the first threaded rod may be rotated relative to the second connecting portion 121, and the second threaded rod may be rotated relative to the adjusting mechanism 130. In this way, the height distance between the second connecting member 120 and the adjusting mechanism 130 is adjusted to ensure that the connecting block 123 can abut against the slope of the inclined groove 113 .

[0058] In some examples, the threads of the first threaded rod and the threads of the second threaded rod have opposite directions of rotation.

[0059] It is understandable that the thread rotation direction of the first threaded rod and the thread rotation direction of the second threaded rod can be set oppositely. In this way, the second threaded rod can be rotated to loosen while the first threaded rod is rotated to tighten. Conversely, the first threaded rod can be rotated to loosen while the second threaded rod is rotated to tighten. This avoids loosening at the same time, which causes the connecting rod 124 to fall off, and improves stability.

[0060] In some examples, such as Figures 1 to 5As shown, the adjustment mechanism 130 includes: a pull rod 131, the second threaded rod is screwed to the top of the pull rod 131; a rotating shaft 132, the end of the pull rod 131 close to the second connecting portion 121 is rotatably connected to the support portion 122 through the rotating shaft 132; an adjustment rod 133, which is passed through the end of the pull rod 131 away from the second connecting portion 121; a tensioning belt 134, which is connected to the adjustment rod 133, and the tensioning belt 134 is used to be arranged below the tail nozzle of the aircraft 200; an elastic member 135, which is arranged between the support portion 122 and the pull rod 131, and the elastic member 135 is arranged between the tensioning belt 134 and the support portion 122. When a tensioning force is applied to the pull rod 131, the elastic member 135 is in a compressed state; wherein, when the adjustment mechanism 130 is in the first state, the tensioning band 134 applies a tensioning force to the pull rod 131 through the adjustment rod 133, so that the connecting block 123 is pressed against the bottom of the inclined groove 113; when the adjustment mechanism 130 is in the second state, the flame ejected from the tail nozzle of the aircraft 200 burns the tensioning band 134, and the elastic member 135 rebounds, driving the pull rod 131 to rotate, so that the connecting block 123 slides out of the opening of the inclined groove 113.

[0061] It is understandable that the adjustment mechanism 130 may be provided with a pull rod 131, a rotating shaft 132, an adjustment rod 133, a tensioning belt 134 and an elastic member 135. Among them, the top and side of the support portion 122 may be provided with openings, and the rotating shaft 132 may be provided through the side of the support portion 122. A threaded hole is provided at the top of the pull rod 131, and the second threaded rod may be screwed into the threaded hole. The pull rod 131 may be rotated relative to the support portion 122 through the rotating shaft 132, and the connecting rod 124 may be driven to rotate by rotating the pull rod 131, thereby driving the second connecting portion 121 to move relative to the first connecting portion 112. Since the connecting block 123 abuts against the slope, the slope limits the degree of freedom of the connecting block 123, so that rotating the pull rod 131 may cause the connecting block 123 to move along the slope toward the opening or the bottom of the inclined groove 113. The adjusting rod 133 may be inserted through the end of the pull rod 131 away from the second connecting member 120, and the tensioning belt 134 may be connected to the adjusting rod 133, and the tensioning belt 134 is located directly below the tail nozzle of the aircraft 200, and when the adjusting mechanism 130 is in the first state, the tensioning belt 134 may be in a tensioning state, so as to apply tensioning force to the pull rod 131 through the adjusting rod 133. The tensioning direction of the tensioning belt 134 is consistent with the opening direction of the inclined groove 113, and when the end of the pull rod 131 away from the second connecting member 120 is subjected to the tensioning force, it rotates toward the tensioning direction of the tensioning belt 134, so that the end of the pull rod 131 close to the second connecting member 120 rotates away from the tensioning direction, so that the connecting block 123 moves in the direction close to the bottom of the groove until the connecting block 123 is subjected to the tensioning force and is pressed against the bottom of the groove, so that the first connecting member 110 and the second connecting member 120 are locked. Meanwhile, an elastic member 135 may be provided between the pull rod 131 and the support portion 122. When the adjustment mechanism 130 is in the first state, the elastic member 135 is in a compressed state under the action of the tension force. When the aircraft 200 is ignited and launched, the tail nozzle of the aircraft 200 ejects flames to burn the tension belt 134, and the tension belt 134 instantly loses the tension force. The elastic member 135 rebounds to drive the end of the pull rod 131 away from the second connecting member 120 to rotate in a direction away from the support portion 122. At the same time, the end of the pull rod 131 close to the second connecting member 120 is acted upon by the rebound force, so that the connecting block 123 moves along the slope toward the notch direction of the inclined slot 113 until the connecting block 123 is disengaged from the notch, so that the first connecting member 110 and the second connecting member 120 are separated, so that the aircraft 200 is launched smoothly.

[0062] In some examples, the tensioning strap 134 includes a nylon strap or a polyester strap.

[0063] It is understandable that the tensioning belt 134 may be made of nylon or polyester, etc., so as to have a certain elasticity and sufficient tension in the stretched state to ensure that the connecting block 123 is kept pressed against the bottom of the groove, and can be quickly broken under the action of the flame ejected from the tail nozzle of the aircraft 200 to avoid affecting the launch of the aircraft 200.

[0064] In some examples, a plurality of the above-mentioned windproof locking devices 100 for the aircraft 200 are provided, and the plurality of the above-mentioned windproof locking devices 100 for the aircraft 200 are used to be symmetrically arranged on the surrounding side of the above-mentioned launch pad 300 with the center line of the above-mentioned launch pad 300 as the axis of symmetry, wherein each of the above-mentioned windproof locking devices 100 for the aircraft 200 is connected to the corresponding above-mentioned windproof locking devices 100 for the aircraft 200 through the above-mentioned tensioning belt 134, and the above-mentioned tensioning belt 134 is in a tensioned state.

[0065] It can be understood that there can be multiple windproof locking devices 100 for the aircraft 200, and the multiple windproof locking devices 100 for the aircraft 200 are arranged in an even number, and the multiple windproof locking devices 100 for the aircraft 200 are arranged axially symmetrically on the surrounding side of the launch pad 300 with the center line of the launch pad 300 as the symmetry axis. And every two windproof locking devices 100 for the aircraft 200 form a group, and the windproof locking devices 100 for the aircraft 200 in a group are connected by a tensioning belt 134, and the tensioning belt 134 is in a tensioned state, so as to apply tensioning force to the windproof locking devices 100 of the two aircraft 200 at the same time, so as to ensure that the first connecting member 110 and the second connecting member 120 of the windproof locking device 100 of each aircraft 200 are locked. When the aircraft 200 is ignited, the tensioning belt 134 will be quickly burned off to separate the first connecting member 110 and the second connecting member 120 of the windproof locking devices 100 of the corresponding group of two aircraft 200. Such a configuration ensures that the fixing force applied by the windproof locking devices 100 of multiple aircraft 200 to the aircraft 200 is evenly distributed, thereby improving stability, and can quickly and simultaneously burn off multiple tensioning belts 134 during ignition to ensure that the windproof locking devices 100 of multiple aircraft 200 can be unlocked at the same time, thereby ensuring that the aircraft 200 can be launched quickly.

[0066] Exemplarily, four windproof locking devices 100 of the aircraft 200 may be provided, and the angle between adjacent windproof locking devices 100 of the aircraft 200 is 90°.

[0067] In the present invention, the terms "first", "second", and "third" are used for descriptive purposes only and should not be understood as indicating or implying relative importance; the term "plurality" refers to two or more, unless otherwise clearly defined. The terms "installed", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "connected" can be a direct connection or an indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0068] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by terms such as “upper”, “lower”, “left”, “right”, “front” and “back” are based on the directions 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 unit referred to must have a specific direction, be constructed and operated in a specific orientation, and therefore, cannot be understood as a limitation on the present invention.

[0069] In the description of this specification, the description of the terms "one embodiment", "some embodiments", "specific embodiments", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0070] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft windproof locking device, characterized in that: include: A first connecting member, used to connect to the tail of the aircraft; A second connecting member, detachably connected to the first connecting member, for connecting to a launching platform; an adjusting mechanism connected to the second connecting member, the adjusting mechanism having a first state and a second state, wherein when the aircraft is before launching, the adjusting mechanism is in the first state, and the adjusting mechanism adjusts the second connecting member to be locked to the first connecting member; When the aircraft is in the state of being ignited for launch, the adjusting mechanism is in the second state, and the adjusting mechanism adjusts the second connecting member to separate from the first connecting member.

2. The aircraft windproof locking device according to claim 1, characterized in that: The first connecting member comprises: A bolt, used for being screwed to the tail of the aircraft; The first connecting portion is connected to the bottom of the bolt along the axial direction of the bolt and is used to be connected to the second connecting member.

3. The aircraft windproof locking device according to claim 2, characterized in that: The bolt and the first connecting portion are an integrated structure.

4. The aircraft windproof locking device according to claim 2, characterized in that: The second connecting member comprises: A second connection part is connected to the adjustment mechanism, an oblique groove is provided on the peripheral side of the first connection part, and a connection block is provided on the second connection part, and the adjustment mechanism can drive the connection block to slide along the slope of the oblique groove; A support portion, the adjustment mechanism is connected to the support portion, and the support portion is used to be connected to the launch platform; Wherein, when the adjusting mechanism is in the first state, the connecting block presses against the bottom of the inclined slot; when the adjusting mechanism is in the second state, the connecting block slides out of the opening of the inclined slot along the slope of the inclined slot; the opening and the bottom of the slot are arranged opposite to each other.

5. The aircraft windproof locking device according to claim 2, characterized in that: The second connecting member further comprises: A connecting rod is used to connect the first connecting part to the second connecting part.

6. The aircraft windproof locking device according to claim 5, characterized in that: The connecting rod comprises: a first threaded rod, threadedly connected to the bottom of the second connecting portion; a second threaded rod, threadedly connected to the top of the adjustment mechanism; A column, one end of which is connected to the first threaded rod, and the other end of which is connected to the second threaded rod; A hexagonal nut, sleeved on the column; The slope of the connecting block abutting against the inclined groove can be adjusted by rotating the hexagonal nut.

7. The aircraft windproof locking device according to claim 6, characterized in that: The threads of the first threaded rod and the threads of the second threaded rod have opposite rotation directions.

8. The aircraft windproof locking device according to claim 4, characterized in that: The regulating mechanism comprises: A pull rod, wherein the second threaded rod is screwed to a top end of the pull rod; A rotating shaft, wherein one end of the pull rod close to the second connecting portion is rotatably connected to the supporting portion through the rotating shaft; An adjusting rod, passing through an end of the pull rod away from the second connecting portion; A tensioning belt connected to the adjusting rod, wherein the tensioning belt is used to be arranged below the tail nozzle of the aircraft; an elastic member, disposed between the support portion and the pull rod, wherein the elastic member is in a compressed state when the tensioning belt applies a tensioning force to the pull rod; Wherein, when the adjusting mechanism is in the first state, the tensioning belt applies tensioning force to the pulling rod through the adjusting rod, so that the connecting block is pressed against the bottom of the inclined slot; when the adjusting mechanism is in the second state, the flame ejected from the tail nozzle of the aircraft burns the tensioning belt, and the elastic member rebounds, driving the pulling rod to rotate, so that the connecting block slides out of the opening of the inclined slot.

9. The aircraft windproof locking device according to claim 8, characterized in that: The tension belt comprises a nylon belt or a polyester belt.

10. The aircraft windproof locking device according to claim 8, characterized in that: There are multiple aircraft windproof locking devices, and the multiple aircraft windproof locking devices are used to be symmetrically arranged on the surrounding side of the launch pad with the center line of the launch pad as the axis of symmetry, wherein each aircraft windproof locking device is connected to the corresponding aircraft windproof locking device through the tensioning belt, and the tensioning belt is in a tensioned state.

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