Aircraft throwing structure and aircraft

Abstract

The utility model discloses an aircraft throwing structure and an aircraft. The aircraft throwing structure comprises a throwing body, a driving part, a clamping assembly and a connecting assembly. The throwing main body is connected to the aircraft main body; the fixed end of the driving part is connected to the throwing main body, and the output end of the driving part is configured to rotationally abut against one end of the clamping assembly and drive the clamping assembly to rotate; the other end of the clamping assembly is rotationally clamped with one end of the connecting assembly, and the other end of the connecting assembly is rotationally connected with the throwing main body; when the throwing structure is in a locking state, the output end of the driving part is far away from the clamping assembly, and at the moment, the connecting assembly is clamped with the clamping assembly; when throwing is needed, the output end of the driving part drives the clamping assembly to rotate, and at the moment, one end of the connecting assembly is separated from the clamping assembly. According to the invention, the aircraft throwing structure is simplified, the control flexibility and reliability are improved, and the cost is also reduced.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to an aircraft launching structure and an aircraft. Background Technology

[0002] As the demand for aircraft continues to grow, the types of payloads they can carry are also becoming increasingly diverse. As a key mechanism for releasing aircraft payloads, the launch device must meet the usage requirements of various mission environments.

[0003] Currently, some throwing structures suffer from problems such as complex structure, inflexible control, and high cost, which limit their application in various scenarios.

[0004] Therefore, there is an urgent need for a throwing structure that is simple in structure and flexible in control, and can realize multiple throwing modes. Utility Model Content

[0005] This application provides an aircraft launching structure and an aircraft, which solves the problems of complex structure and inflexible control in the existing aircraft launching structures.

[0006] In a first aspect, this utility model provides an aircraft launching structure, including a launching body, a driving component, a snap-fit ​​assembly, and a connecting assembly; the launching body is connected to the aircraft body; the fixed end of the driving component is connected to the launching body, and the output end of the driving component is configured to rotatably abut against one end of the snap-fit ​​assembly, thereby driving the snap-fit ​​assembly to rotate; the other end of the snap-fit ​​assembly is rotatably snapped against one end of the connecting assembly, and the other end of the connecting assembly is rotatably connected to the launching body; when the launching structure is in a locked state, the output end of the driving component is away from the snap-fit ​​assembly, and at this time, the connecting assembly is snapped against the snap-fit ​​assembly; when launching is required, the output end of the driving component drives the snap-fit ​​assembly to rotate, and at this time, the connecting assembly disengages from the snap-fit ​​assembly.

[0007] In conjunction with the first aspect, one possible implementation also includes a rocker arm; the rocker arm is connected to the output end of the drive member and is configured to drive the snap-fit ​​assembly to rotate.

[0008] In conjunction with the first aspect, in one possible implementation, the snap-fit ​​assembly includes a snap-fit, an elastic element, and a first rotating shaft; the throwing body has an installation groove configured to connect the rocker arm and the connecting assembly; the snap-fit ​​is disposed in the installation groove, the middle portion of the snap-fit ​​is rotatably connected to the throwing body via the first rotating shaft, one end of the snap-fit ​​extends out of the installation groove, and the rocker arm is configured to rotatably abut against the snap-fit ​​and drive the snap-fit ​​to rotate; the other end of the snap-fit ​​is rotatably snapped into one end of the connecting assembly; one end of the elastic element is connected to the snap-fit, and the other end of the elastic element is connected to the throwing body.

[0009] In conjunction with the first aspect, in one possible implementation, the connecting component includes a strap buckle, an anti-slip strap, and a second rotating shaft; one end of the anti-slip strap is connected to the strap buckle, and the other end of the anti-slip strap is rotatably connected to the second rotating shaft; the buckle is rotatably engaged with the strap buckle; and the second rotating shaft is connected to the throwing body.

[0010] In conjunction with the first aspect, one possible implementation also includes a cover plate; the cover plate is connected to the end of the launching body away from the connecting assembly, and the cover plate is connected to the aircraft body.

[0011] In conjunction with the first aspect, in one possible implementation, the buckle has a first limiting groove; the throwing body has a second limiting groove; one end of the elastic element is disposed in the first limiting groove, and the other end of the elastic element is disposed in the second limiting groove.

[0012] In conjunction with the first aspect, in one possible implementation, the buckle has an arc-shaped protrusion at one end near the strap buckle, the arc-shaped protrusion being configured to engage with the strap buckle.

[0013] Secondly, embodiments of the present invention provide an aircraft, including the aircraft launching structure of the first aspect or any implementation thereof.

[0014] One or more technical solutions provided in this application have at least the following technical effects:

[0015] This utility model embodiment employs an aircraft launching structure, including a launching body, a driving component, a snap-fit ​​assembly, and a connecting assembly. The launching body is connected to the aircraft body. The fixed end of the driving component is connected to the launching body and also includes a rocker arm connected to the output end of the driving component. The snap-fit ​​assembly includes a buckle and an elastic element. The middle part of the buckle is rotatably connected to the launching body via a first rotating shaft. One end of the buckle extends out of the mounting groove, and the rocker arm is configured to drive the buckle to rotate. The other end of the buckle is rotatably snapped into one end of the connecting assembly. The other end of the connecting assembly is rotatably connected to the launching body. When the launching structure is in a locked state, the rocker arm moves away from the buckle, and at this time, the connecting assembly snaps into the buckle. When launching is required, the rocker arm drives the snap-fit ​​assembly to rotate, and at this time, the connecting assembly disengages from the buckle. This application achieves the function of automatically untying the strap lock by driving the buckle to rotate through the driving component. Furthermore, by changing the shape and structure of the rocker arm, it is possible to flexibly switch between single, double, or four-strike launching modes. This application addresses the problems of complex structure and inflexible control in existing aircraft launch structures. It simplifies the aircraft launch structure, improves control flexibility and reliability, offers multiple launch modes, and reduces costs. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments of this utility model will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 An isometric view of an aircraft launch structure provided in an embodiment of this application;

[0018] Figure 2 A top view of an aircraft launching structure provided in an embodiment of this application;

[0019] Figure 3 for Figure 2 AA section view;

[0020] Figure 4 A bottom view of an aircraft launching structure provided in an embodiment of this application;

[0021] Figure 5 This is an isometric view of the snap-fit ​​assembly and the connecting assembly provided in the embodiments of this application;

[0022] Figure 6 A top view of the snap-fit ​​assembly and the connecting assembly provided in an embodiment of this application;

[0023] Figure 7 for Figure 6BB cross-sectional view;

[0024] Figure 8 Axonometric view of the buckle and strap lock provided in the embodiments of this application;

[0025] Figure 9 A schematic diagram of the rocker arm provided in an embodiment of this application;

[0026] Figure 10 This is a schematic diagram of a rocker arm provided in an embodiment of this application.

[0027] Icons: 1-Throwing body; 11-Mounting slot; 2-Drive component; 3-Snap-fit ​​assembly; 31-Snap buckle; 312-Arc-shaped protrusion; 32-Elastic component; 33-First pivot; 4-Connecting assembly; 41-Strap lock; 42-Anti-slip strap; 43-Second pivot; 5-Rocker arm; 6-Cover plate. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of the present utility model. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present utility model.

[0029] In the description of the embodiments of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing the embodiments of this utility model and simplifying the description. They do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this utility model can be understood according to the specific circumstances.

[0030] This utility model embodiment provides an aircraft launching structure, such as Figure 1-10As shown, the system includes a launching body 1, a driving component 2, a locking assembly 3, and a connecting assembly 4. The launching body 1 is connected to the main body of the aircraft. The fixed end of the driving component 2 is connected to the launching body 1, and the output end of the driving component 2 is configured to rotatably abut against one end of the locking assembly 3, thereby driving the locking assembly 3 to rotate. The other end of the locking assembly 3 is rotatably locked to one end of the connecting assembly 4, and the other end of the connecting assembly 4 is rotatably connected to the launching body 1. When the launching structure is in a locked state, the output end of the driving component 2 moves away from the locking assembly 3, and at this time, the connecting assembly 4 is locked to the locking assembly 3. When launching is required, the output end of the driving component 2 drives the locking assembly 3 to rotate, and at this time, the connecting assembly 4 disengages from the locking assembly 3.

[0031] For example, the bottom of the throwing body 1 is evenly provided with multiple load installation positions, and each load installation position is provided with a snap-fit ​​component 3 and a connecting component 4.

[0032] For example, the drive unit 2 is preferably a servo motor, which is fixedly connected to the throwing body 1 by screws. The output end of the servo motor is connected to a rocker arm 5, which can be replaced according to the required throwing mode.

[0033] For example, the launching body 1 has a mounting hole for a servo motor and a cable guide hole for the servo motor.

[0034] In the embodiments of this application, such as Figure 1-10 As shown, it also includes a rocker arm 5; the rocker arm 5 is connected to the output end of the drive unit 2 and is configured to drive the snap-fit ​​assembly 3 to rotate.

[0035] For example, the rocker arm 5 includes a single-arm structure, a double-arm structure, and a four-arm structure. Different rocker arms 5 can be replaced according to the required throwing mode, thereby flexibly switching between single, double, or four-shot throwing modes.

[0036] For example, the rocker arm 5 is provided with a connection hole, and the rocker arm 5 is connected to the output end of the drive unit 2 through the connection hole. The inside of the connection hole is treated with anti-slip treatment to prevent the rocker arm 5 from slipping.

[0037] For example, the servo motor can be set with torque and angle parameters to meet the requirements of throwing control.

[0038] For example, the throwing body 1 is equipped with a sensor, which can transmit the position of the rocker arm 5 to the user.

[0039] In the embodiments of this application, such as Figure 1-10As shown, the snap-fit ​​assembly 3 includes a snap-fit ​​31, an elastic element 32, and a first rotating shaft 33; the throwing body 1 has an installation groove 11, which is configured to connect the rocker arm 5 and the connecting assembly 4; the snap-fit ​​31 is disposed in the installation groove 11, and the middle part of the snap-fit ​​31 is rotatably connected to the throwing body 1 through the first rotating shaft 33. One end of the snap-fit ​​31 extends out of the installation groove 11, and the rocker arm 5 is configured to rotatably abut against the snap-fit ​​31 and drive the snap-fit ​​31 to rotate; the other end of the snap-fit ​​31 is rotatably snapped into one end of the connecting assembly 4; one end of the elastic element 32 is connected to the snap-fit ​​31, and the other end of the elastic element 32 is connected to the throwing body 1.

[0040] For example, one end of the buckle 31 is provided with a force-receiving part that contacts the rocker arm 5, and the other end of the buckle 31 is provided with an arc-shaped protrusion 312, which can be engaged with the strap buckle 41.

[0041] For example, the elastic element 32 is configured as a spring, which can provide a preload force to the latch 31 to keep the latch 31 in a locked state.

[0042] In the embodiments of this application, such as Figure 1-10 As shown, the connecting component 4 includes a strap buckle 41, an anti-slip strap 42, and a second rotating shaft 43; one end of the anti-slip strap 42 is connected to the strap buckle 41, and the other end of the anti-slip strap 42 is rotatably connected to the second rotating shaft 43; the buckle 31 is rotatably engaged with the strap buckle 41; the second rotating shaft 43 is connected to the throwing body 1.

[0043] For example, the end of the strap buckle 41 near the buckle 31 is provided with a snap-fit ​​portion that matches the arc-shaped protrusion 312, and the end of the strap buckle 41 near the anti-slip strap 42 is provided with a metal clip.

[0044] In the embodiments of this application, such as Figure 1-10 As shown, it also includes a cover plate 6; the cover plate 6 is connected to the end of the throwing body 1 away from the connecting component 4, and the cover plate 6 is connected to the aircraft body.

[0045] For example, the cover plate 6 is connected to the top of the launching body 1 by screws. The entire launching structure can be installed on the aircraft body by the cover plate 6, and the cover plate 6 can protect the launching structure.

[0046] For example, the cover plate 6 has a servo cable pass hole to meet the protection and installation requirements of the throwing structure.

[0047] In the embodiments of this application, such as Figure 1-10 As shown, the buckle 31 has a first limiting groove; the throwing body 1 has a second limiting groove; one end of the elastic member 32 is disposed in the first limiting groove, and the other end of the elastic member 32 is disposed in the second limiting groove.

[0048] In the embodiments of this application, such as Figure 1-10 As shown, the buckle 31 has an arc-shaped protrusion 312 at one end near the strap buckle 41, and the arc-shaped protrusion 312 is configured to engage with the strap buckle 41.

[0049] This utility model embodiment provides an aircraft launching structure, the working principle of which is as follows:

[0050] When the throwing structure is in the locked state, the elastic force of the elastic element 32 causes the arc-shaped protrusion 312 of the buckle 31 to engage with the locking part of the strap buckle 41, thereby fixing the load by the anti-slip strap 42. When throwing is required, the drive element 2 receives a control signal, thereby driving the rocker arm 5 to rotate. When the rocker arm 5 rotates, it can push the force-bearing end of the buckle 31. The buckle 31 can overcome the elastic force of the elastic element 32, thereby causing the buckle 31 to rotate around the first rotating shaft 33. At this time, the arc-shaped protrusion 312 disengages from the strap buckle 41, and the strap buckle 41 quickly disengages under the action of the load gravity or external force, completing the throwing. This application can achieve selective throwing of single, double, or four loads by replacing the rocker arm 5 with different shapes and structures and simultaneously triggering the action of one or more buckles 31.

[0051] For example, the aircraft launching structure of this application is simple, has multiple launching modes, has low manufacturing cost, and is suitable for mass production.

[0052] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, please refer to each other. Each embodiment focuses on describing the differences from other embodiments.

[0053] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of this application.

Claims

1. A launching structure for an aircraft, characterized in that, It includes a throwing body (1), a driving component (2), a snap-fit ​​assembly (3), and a connecting assembly (4); The launching body (1) is connected to the main body of the aircraft; The fixed end of the driving component (2) is connected to the throwing body (1), and the output end of the driving component (2) is configured to rotatably abut against one end of the snap-fit ​​assembly (3) and drive the snap-fit ​​assembly (3) to rotate. The other end of the snap-fit ​​component (3) is rotatably snapped into one end of the connecting component (4), and the other end of the connecting component (4) is rotatably connected to the throwing body (1); When the throwing structure is in the locked state, the output end of the drive component (2) is away from the snap-fit ​​component (3), and at this time, the connecting component (4) snaps into the snap-fit ​​component (3); When it is necessary to throw, the output end of the drive component (2) drives the snap-fit ​​assembly (3) to rotate. At this time, the connecting component (4) disengages from the snap-fit ​​assembly (3).

2. The aircraft launching structure according to claim 1, characterized in that, It also includes a rocker arm (5); The rocker arm (5) is connected to the output end of the drive unit (2) and is configured to drive the snap-fit ​​assembly (3) to rotate.

3. The aircraft launching structure according to claim 2, characterized in that, The snap-fit ​​assembly (3) includes a snap-fit ​​(31), an elastic element (32), and a first pivot (33). The throwing body (1) is provided with a mounting groove (11), which is configured to connect the rocker arm (5) and the connecting component (4). The buckle (31) is disposed in the mounting groove (11). The middle part of the buckle (31) is rotatably connected to the throwing body (1) through the first rotating shaft (33). One end of the buckle (31) extends out of the mounting groove (11). The rocker arm (5) is configured to rotatably abut against the buckle (31) and drive the buckle (31) to rotate. The other end of the buckle (31) is rotatably engaged with one end of the connecting assembly (4); One end of the elastic element (32) is connected to the buckle (31), and the other end of the elastic element (32) is connected to the throwing body (1).

4. The aircraft launching structure according to claim 3, characterized in that, The connecting component (4) includes a strap buckle (41), an anti-slip strap (42), and a second pivot (43). One end of the anti-slip strap (42) is connected to the strap buckle (41), and the other end of the anti-slip strap (42) is rotatably connected to the second rotating shaft (43); The buckle (31) and the strap lock (41) are rotatably engaged; The second rotating shaft (43) is connected to the throwing body (1).

5. The aircraft launching structure according to claim 1, characterized in that, It also includes a cover plate (6); The cover plate (6) is connected to the end of the throwing body (1) away from the connecting assembly (4), and the cover plate (6) is connected to the aircraft body.

6. The aircraft launching structure according to claim 3, characterized in that, The buckle (31) has a first limiting groove; The throwing body (1) is provided with a second limiting groove; One end of the elastic element (32) is disposed in the first limiting groove, and the other end of the elastic element (32) is disposed in the second limiting groove.

7. The aircraft launching structure according to claim 4, characterized in that, The buckle (31) has an arc-shaped protrusion (312) at one end near the strap buckle (41), and the arc-shaped protrusion (312) is configured to engage with the strap buckle (41).

8. An aircraft, characterized in that, Includes the aircraft launching structure as described in any one of claims 1-7.

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