Airplane hanging mechanism

Abstract

The utility model relates to the field of airplane structure design, in particular to an airplane hanging mechanism which comprises a hanging mechanism body, a hanging piece, a supporting piece and a rigid frame, the hanging piece comprises a first plate face, a second plate face and a connecting plate connecting the two plate faces, and the connecting plate is composed of a third plate face and a fourth plate face which are perpendicular to each other. The side edges of the third plate surface and the fourth plate surface are connected with each other, so that a cavity is formed between the first plate surface and the second plate surface, and bolt holes are formed in the first plate surface. The number of the mounting connectors is multiple, the mounting connectors can be arranged according to needs, and the mounting requirements of the mounted objects can be met by arranging the multiple mounting connectors. The butt joint and the machine body structure joint are connected through the pin, so that the transmission of the hanging load to the machine body is realized, the hanging is simple and quick to mount and dismount, and the practicability is high.

Description

Technical Field

[0001] The utility model relates to the field of aircraft structure design, in particular to an aircraft hanging mechanism. Background Art

[0002] With the development of modern aviation industry, under the premise of meeting basic performance requirements, it is expected to realize more uses of aircraft and have stronger loading capacity or mounting capacity. For mounting, the mounting structure must meet the requirements of stiffness and strength, and have light weight and reliable safety. In the development of a certain type of aircraft, according to the use requirements of the aircraft, it is necessary to mount specific equipment on the lower part of the fuselage and put forward extremely strict requirements on the stiffness of the hanging structure. For this reason, it is necessary to design a hanging structure (hanging device) for mounting equipment. According to the functional requirements of the aircraft and combined with the characteristics of the aircraft itself, the design of the hanging structure ensures the performance of the aircraft, and the hanging can meet the requirements of the hanging, the hanging strength can meet the design requirements, the hanging stiffness can meet the design and use requirements, the hanging can have a light weight, the connection between the hanging and the fuselage is safe and reliable, the installation and disassembly are simple and quick, and the hanging will not affect the lift, drag and vibration of the aircraft.

[0003] Stealth is a specialized technology used during the development of an aircraft to reduce its detectability, making it difficult for the enemy to detect, track, and attack it. The current research focus is on radar stealth technology and shape stealth technology. The high-stealth target aircraft in the existing technology has a compact structure, and the upper hanging point of the target aircraft and the lower launch rack support point are designed separately, which creates tight space. If the hanging point protrudes from the fuselage and the support point is not designed properly, it will seriously affect the stealth performance of the aircraft.

[0004] Therefore, those skilled in the art provide an aircraft hanging mechanism to solve the problems raised in the above background technology. Utility Model Content

[0005] In order to solve the above technical problems, the utility model provides an aircraft hanging mechanism, including a hanging mechanism, a hanging member, a support member and a rigid frame, the hanging member including a first plate surface, a second plate surface and a connecting plate connecting the two plate surfaces, the connecting plate is composed of a third plate surface and a fourth plate surface that are perpendicular to each other, and the sides of the third plate surface and the fourth plate surface are connected to each other, so that a cavity is formed between the first plate surface and the second plate surface, bolt holes are arranged on the first plate surface, a rigid frame is arranged between the two hanging members and the support member, the front and rear beams of the rigid frame extend to both sides respectively to form a plurality of reinforcing beams with variable cross-sections, the ends of the reinforcing beams on both sides are respectively deformed into a butt joint, and there are four butt joints on the rigid frame.

[0006] Preferably: a support member is provided on one side of the second plate surface away from the cavity, and the support member shrinks into a straight line in a diamond shape toward the tail of the aircraft. The bolt hole has a diameter of 4 to 6 mm. In this embodiment, the hole has a diameter of 5 mm, and a corresponding support plate nut is installed, and also includes a countersunk bolt. The material of the aircraft hanging mechanism is aluminum alloy, and the hanging member and the support member are integrally formed. An external hanging plate is provided at the rear of the support member, and a mounting joint is provided at the rear of the outer scraper.

[0007] Preferably: the number of the mounting joints is several, which can be set as needed. By setting up multiple mounting joints, the requirements for mounting the mounts can be met, and they are respectively docked with the belly joint of the aircraft body. The symmetry center of the rigid frame coincides with the center of the symmetry plane of the aircraft body. The connection between the docking joint and the fuselage structure joint is completed by pins, so as to realize the transmission of the hanging load to the body, and ensure that the installation and disassembly of the hanging are simple, fast and practical. The front and rear beams on both sides of the rigid frame extend two variable-section reinforcing beams to the left and right sides respectively, so that there are four extended variable-section reinforcing beams on both sides of the rigid frame, and there are a total of eight variable-section reinforcing beams. Four tie rod joints are arranged on both sides of the rigid frame, and the tie rod joints are respectively arranged at the top position of the maximum cross-section of the outer reinforcing beam.

[0008] Technical effects and advantages of the utility model:

[0009] The material of the aircraft hanging mechanism 1 in the utility model is aluminum alloy, and the hanging member 2 and the supporting member 3 are integrally formed, and are designed and manufactured in an integrated manner, thereby solving the problem of tight space for separate design of the upper hanging point of the target aircraft and the lower launcher supporting point.

[0010] 1. The number of mounting joints set is several and can be set as needed. By setting multiple mounting joints, the requirements for mounting the mounts can be met.

[0011] 2. The connection between the butt joint and the machine body structure joint is completed by pins, so that the suspension load is transferred to the machine body, and the installation and disassembly of the suspension are simple, fast and practical.

[0012] 3. The tie rod is connected to the tie rod joint on the aircraft body structure through a pin to achieve the transmission of the hanging load to the body, and ensure that the installation and disassembly of the hanging structure are simple, fast and practical. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the structure of an aircraft hanging mechanism provided in an embodiment of the present application. Figure 1 ;

[0014] Figure 2 It is a schematic structural diagram of a top view of an aircraft hanging mechanism provided in an embodiment of the present application;

[0015] Figure 3 It is a structural schematic diagram of a rigid frame, a butt joint and a reinforcing beam in an aircraft hanging mechanism provided in an embodiment of the present application;

[0016] Figure 4 It is a structural schematic diagram of a hanging member, a supporting member, a first plate surface, a second plate surface, a third plate surface, a fourth plate surface and a cavity in an aircraft hanging mechanism provided by an embodiment of the present application;

[0017] Figure 5 It is a structural schematic diagram of a bolt hole in an aircraft hanging mechanism provided by an embodiment of the present application;

[0018] Figure 6 This is an aircraft hanging mechanism provided in the embodiment of the present application Figure 4 The structural diagram at A in the middle;

[0019] Figure 7 This is an aircraft hanging mechanism provided in the embodiment of the present application Figure 1 Schematic diagram of the structure at B in the figure.

[0020] In the figure: 1. hanging mechanism; 2. hanging parts; 3. supporting parts; 4. first plate surface; 5. second plate surface; 6. third plate surface; 7. fourth plate surface; 8. cavity; 9. bolt hole; 10. external plate; 11. mounting joint; 12. rigid frame; 13. butt joint; 14. reinforcing beam; 15. tie rod joint. DETAILED DESCRIPTION

[0021] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention are provided for the purpose of illustration and description, and are not intended to be exhaustive or to limit the present invention to the disclosed forms. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present invention, and to enable those of ordinary skill in the art to understand the present invention and thereby design various embodiments with various modifications suitable for specific purposes. Example 1

[0022] See also Figures 1 to 7In the present embodiment, an aircraft hanging mechanism is provided, including a hanging mechanism 1, a hanging component 2, a support component 3 and a rigid frame 12, wherein the hanging component 2 includes a first plate surface, a second plate surface 5 and a connecting plate connecting the two plate surfaces, wherein the connecting plate is composed of a third plate surface 6 and a fourth plate surface 7 which are perpendicular to each other, and the sides of the third plate surface 6 and the fourth plate surface 7 are connected to each other, so that a cavity 8 is formed between the first plate surface and the second plate surface 5, a bolt hole 9 is arranged on the first plate surface, and a support component 3 is arranged on a side of the second plate surface 5 away from the cavity 8, and the support component 3 shrinks into a straight line in a rhombus shape toward the tail direction of the aircraft, and the bolt hole 9 has a diameter of 4 to 6 mm. In the present embodiment, the hole has a diameter of 5 mm, and a corresponding support plate nut is installed, and a countersunk bolt is also included. When the aircraft is not hoisted, the bolt is installed in the bolt hole 9. When hoisting, the bolt is removed and replaced with a hanging rope for body hoisting. The material of the aircraft hanging mechanism 1 is aluminum alloy, and the hanging component 2 and the support component 3 are integrated into one body The structure is of integrated design and manufacturing, which solves the problem of tight space for separate design of upper hanging point of target aircraft and lower launcher support point. An external hanging plate 10 is arranged at the rear of the support member 3, and a mounting joint 11 is arranged at the rear of the external hanging plate 10. The number of mounting joints 11 is several and can be set as required. By setting a plurality of mounting joints 11, the requirements for mounting objects can be met. A rigid frame 12 is arranged between the two hanging members 2 and the support member 3. The front and rear beams of the rigid frame 12 extend to both sides to form a plurality of reinforcing beams 14 with variable cross-sections. The ends of the reinforcing beams 14 on both sides are respectively deformed into a butt joint 13. There are four butt joints 13 on the rigid frame 12, which are respectively butt jointed with the belly joint of the aircraft body. The symmetry center of the rigid frame 12 coincides with the symmetry plane center of the aircraft body. The connection between the butt joint 13 and the body structure joint is completed by pins, so as to realize the transmission of hanging load to the body, and ensure that the installation and disassembly of the hanging are simple, fast and practical.

[0023] In the present application, the reinforcing beam 14 is designed as a variable cross-section structure, which not only solves the problem of the rigidity of the suspension structure satisfying the minimum impact on the vibration of the aircraft, but also ensures sufficient strength and lightest weight. The front and rear beams on both sides of the rigid frame 12 extend two variable cross-section reinforcing beams 14 to the left and right sides respectively, so that there are four extended variable cross-section reinforcing beams 14 on both sides of the rigid frame 12, and there are a total of eight variable cross-section reinforcing beams 14. Four tie rod joints 15 are arranged on both sides of the rigid frame 12. The tie rod joints 15 are respectively arranged at the top position of the maximum cross-section of the outer reinforcing beam 14, and are connected to the tie rod joints 15 on the aircraft body structure through tie rods through pins, so as to realize the transmission of the suspension load to the body, and ensure that the installation and disassembly of the suspension structure are simple, quick and practical.

[0024] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field and related fields without creative work should fall within the scope of protection of the present invention. Structures, devices and operating methods not specifically described and explained in the present invention shall be implemented according to conventional means in the field unless otherwise specified and limited.

Claims

1. An aircraft hanging mechanism, comprising a hanging mechanism (1), a hanging member (2), a support member (3) and a rigid frame (12), characterized in that: The hanging component (2) comprises a first plate surface (4), a second plate surface (5) and a connecting plate connecting the two plate surfaces, wherein the connecting plate is composed of a third plate surface (6) and a fourth plate surface (7) which are perpendicular to each other, and the side edges of the third plate surface (6) and the fourth plate surface (7) are connected to each other, so that a cavity (8) is formed between the first plate surface (4) and the second plate surface (5), and a bolt hole (9) is provided on the first plate surface (4). A rigid frame (12) is provided between the two hanging components (2) and the supporting component (3), and the front and rear beams of the rigid frame (12) extend to both sides respectively to form a plurality of reinforcing beams (14) with variable cross-sections, and the ends of the reinforcing beams (14) on both sides are respectively deformed into a butt joint (13), and there are four butt joints (13) on the rigid frame (12).

2. The aircraft hanging mechanism according to claim 1, characterized in that: A support member (3) is provided on a side of the second plate surface (5) away from the cavity (8), and the support member (3) shrinks in a diamond shape to form a straight line towards the tail of the aircraft.

3. The aircraft hanging mechanism according to claim 1, characterized in that: The bolt hole (9) has a diameter of 4 to 6 mm, and the hole has a diameter of 5 mm, and is used to mount a corresponding support plate nut, and also includes a countersunk bolt.

4. The aircraft hanging mechanism according to claim 1, characterized in that: The material of the aircraft hanging mechanism (1) is aluminum alloy, and the hanging component (2) and the supporting component (3) are integrally formed.

5. The aircraft hanging mechanism according to claim 4, characterized in that: An external hanging plate (10) is provided at the rear of the support member (3), and a mounting joint (11) is provided at the rear of the external scraper.

6. The aircraft hanging mechanism according to claim 5, characterized in that: The number of the mounting joints (11) is several and can be set as required.

7. The aircraft hanging mechanism according to claim 1, characterized in that: The symmetry center of the rigid frame (12) coincides with the center of the symmetry plane of the aircraft body.

8. The aircraft hanging mechanism according to claim 1, characterized in that: The connection between the butt joint (13) and the machine body structure joint is completed by means of pins.

9. The aircraft hanging mechanism according to claim 7, characterized in that: The front and rear beams on both sides of the rigid frame (12) extend two variable-section reinforcing beams (14) to the left and right sides respectively, so that there are four extended variable-section reinforcing beams (14) on both sides of the rigid frame (12), and there are eight variable-section reinforcing beams (14) in total. Four tie rod joints (15) are arranged on both sides of the rigid frame (12), and the tie rod joints (15) are respectively arranged at the top position of the maximum cross-section of the outer reinforcing beam (14).

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