Separating and falling mechanism for booster of aircraft

Abstract

According to the separation and falling-off mechanism for the booster of the aircraft, separation of the second connecting assembly can be achieved through the separation bolt of the second connecting assembly, under the inertia effect of the aircraft, the booster slides to be separated from the aircraft, and due to the structural relation between the guide rod and the falling-off frame assembly, the separation and falling-off of the booster are achieved. The booster drives the falling-off frame assembly to rotate relative to the guide rod, when the kidney-shaped boss of the fixing rod slides out of the opening of the through hole of the falling-off frame assembly, the falling-off frame assembly is separated from the guide rod, separation and falling-off of the booster are achieved, and the booster rotates downwards along the fixing rod under the limiting effect of the falling-off frame assembly, so that the falling-off of the booster is achieved. And accidents such as collision between the booster and the aircraft are avoided.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of aircraft booster, specifically relates to a booster separation mechanism of aircraft. BACKGROUND

[0002] The booster of the aircraft needs to separate and fall off from the aircraft after completing the work. The timing of the separation and falling off of the booster influences the flight efficiency of the aircraft, and seriously influences the flight safety of the aircraft.

[0003] The installation mode of the booster determines the thrust efficiency of the booster on the aircraft. According to different flight requirements, how to adjust the thrust line angle of the booster and control the separation and falling off of the booster is a technical problem existing in the prior art. UTILITY MODEL CONTENTS

[0004] Therefore, the utility model aims at providing a booster separation mechanism of aircraft to solve at least one technical problem existing in the prior art.

[0005] The application provides a booster separation mechanism of aircraft, which comprises:

[0006] A guide rod is used to be hinged to the aircraft. One end of the guide rod away from the aircraft is provided with a fixed rod perpendicular to the length direction of the guide rod. Both ends of the fixed rod are provided with a waist-shaped boss.

[0007] A falling-off frame assembly is provided with a through hole in the length direction thereof at the first end. The through hole is provided with an opening at the end face. The falling-off frame assembly is rotationally connected to the fixed rod through the through hole. The waist-shaped boss is rotationally connected to the through hole and can slide out of the opening, so that the falling-off frame assembly is separated from the fixed rod. The second end of the falling-off frame assembly is used to hinge an extension rod of the booster.

[0008] A first connecting assembly is arranged on the booster close to the first end of the extension rod and is used to connect the aircraft. The first connecting assembly is used to slide the booster along the length direction of the first connecting assembly and install the booster on the aircraft. The first connecting assembly is used to limit the booster in the radial direction and the axial direction to the one end of the extension rod.

[0009] A second connecting assembly is arranged on the booster away from the second end of the extension rod and is used to connect the aircraft. The second connecting assembly is provided with a separation bolt and is used to control the separation of the booster from the aircraft.

[0010] Further, the guide rod is connected to the aircraft through a front support. The guide rod is hinged to the front support.

[0011] Further, a tension spring is arranged between the front support and the guide rod, and the tension spring can generate a force to rotate the guide rod towards the front of the aircraft.

[0012] Further, the falling frame assembly comprises:

[0013] A main frame plate, which has a C-shaped cross section;

[0014] A front joint connected to a first end of the main frame plate, and an opening is formed in the through hole at an end of the front joint;

[0015] The second end of the main frame plate is hingedly connected to the extension rod of the booster.

[0016] Further, the falling frame assembly further comprises:

[0017] A rear joint hingedly connected to a second end of the main frame plate;

[0018] An adapter ring comprising two abutting tile rings, each of which is provided with a radially extending ear plate at both ends in the radial direction, the adapter ring is slidingly arranged on the extension rod of the booster and is limited by the end of the extension rod, and the ear plate of the adapter ring is clamped in the through slot formed in the rear joint.

[0019] Further, the first connecting assembly comprises:

[0020] A ball socket connecting seat for connecting the aircraft, and a guide hole with a spherical end is formed in the ball socket connecting seat;

[0021] A ball head support for connecting the booster, and a ball is arranged on the ball head support, and the ball can be inserted into the guide hole;

[0022] A plurality of spacers are arranged between the ball socket connecting seat and the aircraft to adjust the distance between the booster and the aircraft.

[0023] Further, the second connecting assembly comprises:

[0024] A rear support for connecting to the booster;

[0025] A rear connecting seat connected to the rear support through the separation bolt, and the rear connecting seat is used to connect the aircraft.

[0026] The application has the following beneficial effects:

[0027] The booster separation and falling mechanism of the aircraft provided by the application can realize the separation of the second connecting assembly through the separation bolt of the second connecting assembly, and under the inertia effect of the aircraft, the booster slides away from the aircraft, and due to the structural relationship between the guide rod and the falling frame assembly, the booster drives the falling frame assembly to rotate relative to the guide rod, when the waist-shaped boss of the fixed rod slides out of the opening of the through hole of the falling frame assembly, the falling frame assembly is separated from the guide rod, the separation and falling of the booster are realized, and under the limiting effect of the falling frame assembly, the booster rotates downward along the fixed rod, so that the collision between the booster and the aircraft and other accidents are avoided. BRIEF DESCRIPTION OF DRAWINGS

[0028] The above and other objects, features and advantages of the present application will become more apparent from the following description of embodiments of the present application with reference to the accompanying drawings.

[0029] Figure 1 is a structural schematic view of the booster separation and falling mechanism of the aircraft according to the embodiments of the present application;

[0030] Figure 2 is a structural schematic view of the front support according to the embodiments of the present application;

[0031] Figure 3 is a structural schematic view of the guide rod according to the embodiments of the present application;

[0032] Figure 4 is a structural schematic view of the adapter ring according to the embodiments of the present application;

[0033] Figure 5 is a structural schematic view of the ball socket according to the embodiments of the present application;

[0034] Figure 6 is a structural schematic view of the ball head support according to the embodiments of the present application;

[0035] Figure 7 is a structural schematic view of the rear connecting seat according to the embodiments of the present application;

[0036] Figure 8 is a structural schematic view of the rear support according to the embodiments of the present application.

[0037] Wherein, 1-front support, 2-guide rod, 3-front joint, 4-main frame plate, 5-rear joint, 6-adapter ring, 7-ball socket, 8-ball head support, 9-rear connecting seat, 10-rear support, 11-separation bolt, 12-tension spring, 21-fixed rod, 61-ear plate, 71-guide hole, 81-ball. DETAILED DESCRIPTION

[0038] Various embodiments of the present application will be described in greater detail below with reference to the accompanying drawings. In the various drawings, the same elements are denoted by the same or similar reference numerals. For the sake of clarity, the various parts in the drawings are not drawn to scale.

[0039] Reference Figures 1 to 8 The application provides a booster separation mechanism of an aircraft, comprising: a guide rod 2 for being hinged to the aircraft, one end of the guide rod 2 away from the aircraft is provided with a fixed rod 21 perpendicular to the length direction of the guide rod 2, both ends of the fixed rod 21 are provided with a waist-shaped boss; a separation frame assembly is provided with a through hole in the length direction thereof at the first end, the through hole is provided with an opening at the first end face, the separation frame assembly is rotationally connected with the fixed rod 21 through the through hole, the waist-shaped boss is rotated relative to the through hole and can slide out of the opening, so that the separation frame assembly is separated from the fixed rod 21, the second end of the separation frame assembly is used for hinging an extension rod of the booster; a first connecting assembly is arranged on the booster close to the first end of the extension rod and is used for connecting the aircraft, the first connecting assembly is used for slidingly installing the booster to the aircraft along the length direction thereof, and the first connecting assembly is used for limiting the booster in the radial direction; a second connecting assembly is arranged on the booster away from the second end of the extension rod and is used for connecting the aircraft, the second connecting assembly is provided with a separation bolt 11 for controlling the separation of the booster from the aircraft.

[0040] In the embodiment, the separation bolt 11 is an explosive bolt, the second connecting assembly realizes the separation of the booster from the aircraft under the action of the separation bolt 11 under a preset condition or in real time, and under the connecting action of the extension rod of the booster and the separation frame assembly, the booster drives the separation frame assembly to rotate around the fixed rod 21 of the guide rod 2, when the separation frame assembly rotates to the length direction of the opening and the waist-shaped boss coincides, the waist-shaped boss slides out of the opening of the through hole, that is, the separation of the separation frame assembly is realized, as a person skilled in the art should understand that the guide rod 2 and the separation frame assembly play a constraint limiting role in the separation and separation of the booster from the aircraft. After the booster is separated from the aircraft, the booster is affected by the flight environment and collides with the aircraft.

[0041] In the embodiment, with reference to Figure 1 , Figure 2 and Figure 3 , the guide rod 2 is connected to the aircraft through a front support 1, and the guide rod 2 is hinged to the front support 1. It can be understood that the hinged guide rod 2 can rotate around the front support 1, and the length direction of the guide rod 2 and the aircraft can be consistent.

[0042] In the embodiment, a tension spring 12 is arranged between the front support 1 and the guide rod 2, and the tension spring 12 can generate a force to rotate the guide rod 2 towards the front of the aircraft. It can be understood that, after the shedding rack assembly is separated from the fixed rod 21, the guide rod 2 is rotated around the front support 1 under the action of the tension spring 12, so that the guide rod 2 is consistent with the length direction of the aircraft, or the guide rod 2 is attached to the aircraft.

[0043] In the embodiment, referring to Figure 1 and Figure 4 , the shedding rack assembly comprises a main rack plate 4 with a C-shaped cross section, and a front joint 3 connected to a first end of the main rack plate 4, and an opening is arranged in the through hole at an end of the front joint 3. A second end of the main rack plate 4 is hingedly connected to an extension rod of the booster.

[0044] The shedding rack assembly further comprises a rear joint 5 hingedly connected to a second end of the main rack plate 4, and an adapter ring 6 comprising two abutting tiles, each tile being provided with a radially extending ear plate 61 at two ends in the radial direction, the adapter ring 6 being slidingly arranged on the extension rod of the booster and being limited by an end of the extension rod, and the ear plate 61 of the adapter ring 6 being clamped in a through slot arranged in the rear joint 5.

[0045] As can be understood by those skilled in the art, the main rack plate 4 and the front joint 3 can be connected together by a bolt assembly, and the rear joint 5 can also be connected by a pin shaft, so as to ensure that the rear joint 5 is hingedly connected to the main rack plate 4 and the rear joint 5 can rotate around the pin shaft. The cross section of the adapter ring 6 includes but is not limited to a circular shape, and the cross section of each tile is semicircular, so as to realize that the two tiles are abuttingly arranged on the extension rod and the ear plate 61 of the adapter ring 6 is fixed by the through slot in the rear joint 5, and the two tiles are also abuttingly arranged together.

[0046] In an optional embodiment, a circular hole is arranged in each ear plate 61, and a pin can be used to fix the adapter ring 6 by using a bolt assembly.

[0047] In the embodiment, referring to Figure 1 , Figure 5 and Figure 6The first connecting assembly includes: a ball-and-socket connector 7 for connecting the aircraft, the ball-and-socket connector 7 having a guide hole 71 with a spherical end; a ball-head support 8 for connecting the booster, the ball-head support 8 having a ball 81 that can extend into the guide hole 71; and several gaskets disposed between the ball-and-socket connector 7 and the aircraft for adjusting the distance between the booster and the aircraft. During booster installation, the ball 81 structure at one end of the ball-head support 8 extends into the guide hole 71 of the ball-and-socket connector 7 and abuts against the spherical guide hole 71, allowing the booster to rotate only around the guide hole 71 or exit the guide hole 71. The connection between the booster and the landing gear assembly, as well as the connection of the second connecting assembly, secures the booster. When the second connecting assembly is disconnected, the landing gear assembly limits the booster, allowing it to retract only along the guide hole 71, thus disconnecting the first connecting assembly.

[0048] In addition, the adapter ring 6 and the end limit of the extension rod are provided with a movable margin. The length of this movable margin is greater than the retraction length of the ball head support 8 from the ball socket connection seat 7, that is, the retraction distance of the booster along the guide hole 71.

[0049] In this embodiment, reference Figure 1 , Figure 7 and Figure 8 The second connection assembly includes: a rear support 10 for connection to the booster; and a rear connector 9 for connection to the rear support 10 via the release bolt 11, the rear connector 9 being used to connect to the aircraft.

[0050] The distance between the booster and the aircraft at the connection point can be adjusted by increasing or decreasing the number of shims between the ball socket connector 7 and the booster. This allows for adjustment of the angle between the booster's thrust line and the aircraft's flight direction, meeting the needs of different flight missions and improving the booster's efficiency.

[0051] The booster separation and detachment mechanism for the aircraft provided in this application can separate the second connecting component through the separation bolt 11 of the second connecting component. Under the inertia of the aircraft, the booster slides away from the aircraft. Due to the structural relationship between the guide rod 2 and the detachment assembly, the booster drives the detachment assembly to rotate relative to the guide rod 2. When the waist-shaped boss of the fixed rod 21 slides out of the opening of the through hole of the detachment assembly, the detachment assembly separates from the guide rod 2, realizing the separation and detachment of the booster. Under the limiting action of the detachment assembly, the booster rotates downward along the fixed rod 21, avoiding accidents such as collisions between the detachment assembly and the aircraft.

[0052] It is to be noted that, in the present document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0053] Finally, it should be noted that the above-mentioned embodiments are merely intended for the purpose of illustration rather than limiting the present application. Based on the above description, other different forms of changes or modifications can be made by those skilled in the art. Here, it is not necessary or possible to enumerate all the embodiments. The obvious changes or modifications derived therefrom are still within the scope of the present application.

Claims

1. A booster separation and detachment mechanism for an aircraft, characterized in that, include: A guide rod is used to be hinged to the aircraft. A fixed rod perpendicular to the length direction of the guide rod is provided at the end of the guide rod away from the aircraft. Both ends of the fixed rod are provided with waist-shaped bosses. The first end of the detachment frame assembly has a through hole in the radial direction of its length. The through hole and the end face of the first end are provided with an opening. The detachment frame assembly is rotatably connected to the fixed rod through the through hole. The waist-shaped boss rotates relative to the through hole and can slide out from the opening to separate the detachment frame assembly from the fixed rod. The second end of the detachment frame assembly is used to hinge the extension rod of the booster. A first connecting component is disposed on the booster near the first end of the extension rod and is used to connect the aircraft. The first connecting component is used to allow the booster to be slidably mounted onto the aircraft along its length direction. The first connecting component is used to limit the booster radially and axially toward one end of the extension rod. A second connecting assembly, located at the second end of the booster away from the extension rod, is used to connect the aircraft. The second connecting assembly is provided with a separation bolt for controlling the separation of the booster from the aircraft.

2. The booster separation and detachment mechanism for an aircraft according to claim 1, characterized in that, The guide rod is connected to the aircraft via a front support, and the guide rod is hinged to the front support.

3. The booster separation and detachment mechanism for an aircraft according to claim 2, characterized in that, A tension spring is provided between the front support and the guide rod, and the tension spring can exert a force that causes the guide rod to rotate toward the front of the aircraft.

4. The booster separation and detachment mechanism for an aircraft according to claim 1, characterized in that, The drop-out frame assembly includes: The main frame plate has a C-shaped cross-section. A front connector is connected to the first end of the main frame plate, and the end of the front connector is provided with a through hole with an opening; The extension rod of the booster is hinged at the second end of the main frame plate.

5. The booster separation and detachment mechanism for an aircraft according to claim 4, characterized in that, The drop-out frame assembly also includes: The rear connector is hinged to the second end of the main frame plate; The adapter ring includes two mating rings, each of which has radially extending lugs at both ends. The adapter ring is slidably mounted on the extension rod of the booster and is limited by the end of the extension rod. The lugs of the adapter ring are engaged in a through groove on the rear connector.

6. The booster separation and detachment mechanism for an aircraft according to claim 1, characterized in that, The first connection component includes: A ball-and-socket connector for connecting the aircraft, wherein the ball-and-socket connector has a guide hole with a spherical end; A ball head support for connecting the booster, wherein a ball is provided on the ball head support and the ball can extend into the guide hole; Gaskets, a plurality of such gaskets are disposed between the ball-and-socket connector and the spacecraft, for adjusting the distance between the booster and the spacecraft.

7. The booster separation and detachment mechanism for an aircraft according to claim 1, characterized in that, The second connection component includes: A rear support for connecting to the booster; A rear connector is connected to the rear support via the release bolt, and the rear connector is used to connect the aircraft.

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