Fixing structure for nose landing gear of airplane

Abstract

The utility model discloses an aircraft nose landing gear fixing structure, and belongs to the field of nose landing gears. Comprising a machine body; the machine body bottom plate is arranged at the bottom of the machine body; the two fuselage front transverse ribs are arranged at the bottom of the fuselage bottom plate; the machine body longitudinal ribs are arranged on the machine body front transverse ribs, are arranged in front of the bottom of the machine body bottom plate, and are arranged between the two machine body front transverse ribs; the front screwdriver fixing frame is arranged on the front screwdriver fixing box; the connecting assembly is used for connecting the front lifting fixing box, the two fuselage front transverse ribs and the front lifting fixing frame; the front wheel set is arranged below the front lifting fixing frame; the front wheel supporting rod is arranged between the two front lifting fixing frames and the front wheel set. The aircraft nose landing gear fixing structure has the beneficial effect that the aircraft nose landing gear fixing structure is provided.

Description

TECHNICAL FIELD

[0001] The application relates to the field of front landing gears, in particular to a fixing structure of an airplane front landing gear. BACKGROUND

[0002] The landing gear is an accessory device for supporting an airplane during takeoff and landing or ground (water) taxiing, and is used for ground (water) movement. The landing gear is the only component supporting the whole airplane, and thus is an indispensable part of the airplane. Without the landing gear, the airplane cannot move on the ground. After the airplane takes off, the landing gear can be retracted according to the flight performance. The landing gear is an important component of the aircraft with load-bearing and steering functions, and undertakes an extremely important mission in the safe takeoff and landing process of the aircraft. The landing gear is a support system necessary for the takeoff, landing, taxiing, ground movement and parking of the airplane, and is one of the main components of the airplane. The performance of the landing gear is directly related to the use and safety of the airplane. With the development of aviation technology, the landing gear is increasingly widely used. Therefore, there is an increasing demand for a fixing and supporting structure of an airplane landing gear.

[0003] The structure of the product can refer to the fixing and supporting structure of an airplane landing gear disclosed in Chinese Patent Document 202022351500.3, which comprises a cement plate and a load-bearing plate. The bottom end face of the cement plate is fixedly connected with a bottom plate. The inner side of the load-bearing plate is fixedly connected with a first motor. The main shaft end of the first motor is fixedly connected with a first threaded rod. The outer side of the first threaded rod is fixedly connected with a driving wheel. The outer side of the driving wheel is meshingly connected with a chain. The other end of the chain is meshingly connected with a driven wheel. The inner side of the driven wheel is fixedly connected with a first threaded rod. The bottom end face of the load-bearing plate is fixedly connected with a vertical plate. In the utility model, the height adjustment of the fixing mechanism of the landing gear is realized by the setting of the load-bearing plate, the push rod, the sliding groove and the clamping plate. The fixing plate is easy to install and disassemble, the work efficiency is improved, the landing gear is fixed, the movement of the landing gear is prevented, the damage to the machine body or external articles is prevented, and the safety of the landing gear fixing is improved.

[0004] The airplane front landing gear is installed by multiple parts. When installing, the parts need to be connected together by welding or fixed bolts. However, the patent does not set a limiting connection before welding, and the staff need to manually limit, which may affect the subsequent welding.

[0005] Now a fixing structure of an airplane front landing gear is provided. Content of the utility model

[0006] This Background section is intended to introduce the main concepts of the present application, which is further described in the DETAILED DESCRIPTION section. This Background section is not intended to

[0007] To solve the technical problems mentioned in the background section, some embodiments of the present application provide an aircraft nose landing gear fixing structure, comprising: a fuselage body; a fuselage bottom plate arranged at the bottom of the fuselage body; two fuselage front cross ribs arranged at the bottom of the fuselage bottom plate; fuselage longitudinal ribs arranged on the fuselage front cross ribs and at the bottom of the fuselage bottom plate; a front landing fixing box arranged between the two fuselage front cross ribs; a front landing fixing frame arranged on the front landing fixing box; a connecting assembly for connecting the front landing fixing box, the two fuselage front cross ribs and the front landing fixing frame; a front wheel set arranged below the front landing fixing frame; and a front wheel support rod arranged between the two front landing fixing frames and the front wheel set.

[0008] When installation is needed, the connecting rod can be installed first, the connecting rod is inserted into the front landing fixing box, then the connecting piece is installed on the front landing fixing box by the fixing bolt, then the second installation rod on the fuselage front cross rib is inserted into the front landing fixing box and the second installation rod is inserted into the installation slot, then the knob can be rotated, so that the adjusting screw rod is rotated, so that the sliding plate is moved, so that the fixed bar is moved, so that the fixed bar is moved to the fixed slot, so that the second installation rod is fixed, so that the connecting rod, the front landing fixing box and the fuselage front cross rib are connected together, thereby facilitating the subsequent welding of the front landing fixing box and the fuselage front cross rib, and the connecting frame and the installation frame can be connected together by the fixing bolt, the fuselage longitudinal rib and the fuselage front cross rib are preliminarily limited, then the fuselage longitudinal rib is welded to the fuselage front cross rib, and the overall stability is improved by arranging the connecting bar, the stability of the installation of the fuselage longitudinal rib is further improved, the overall connection stability is improved, then the front wheel support rod and the front wheel set can be installed by the fixing bolt, thereby facilitating installation and improving installation efficiency.

[0009] Further, the front landing fixing frame comprises a connecting rod, the connecting rod is fixedly connected with a connecting piece, and the connecting piece is arranged on the front landing fixing box.

[0010] Further, the connecting assembly comprises a first installation rod, the first installation rod is fixedly connected to the connecting rod and passes through the front landing fixing box, two second installation rods are respectively fixedly connected to the ends of the two fuselage front cross ribs close to each other, the second installation rods pass through the front landing fixing box, and a fixing assembly is arranged between the first installation rod and the two second installation rods.

[0011] Further, the fixing assembly comprises a mounting groove, the mounting groove is arranged on the first mounting rod, the second mounting rod is arranged on the mounting groove, the first mounting rod is provided with a sliding cavity, the sliding plate is slidably arranged on the sliding cavity, the fixing strip is fixedly connected to the sliding plate, the second mounting rod is provided with a fixing groove, the fixing strip is corresponding to the fixing groove, and the first mounting rod is provided with an adjusting assembly.

[0012] Further, the adjusting assembly comprises an adjusting screw, the adjusting screw is rotatably arranged on the inner wall of the sliding cavity, the adjusting screw extends to the outside, and the adjusting screw is threadedly connected to the sliding plate.

[0013] Further, the adjusting screw is fixedly connected with a knob.

[0014] Further, the connecting rod is fixedly connected with a connecting strip, and the connecting strip is arranged on the fuselage longitudinal rib.

[0015] Further, the connecting strip is fixedly connected with a connecting frame, the fuselage longitudinal rib is fixedly connected with a mounting frame, the connecting frame is movably connected to the mounting frame, and the connecting frame is arranged on the mounting frame.

[0016] Further, the fixing strip and the fixing groove are both provided with two.

[0017] The beneficial effects of the present application are that an aircraft front landing gear fixing structure is provided. BRIEF DESCRIPTION OF DRAWINGS

[0018] The drawings constituting a part of this application are used to provide a further understanding of the present application, so that other features, objects and advantages of the present application become more apparent. The illustrative embodiment drawings of the present application and their descriptions are used to explain the present application, and do not constitute an improper limitation on the present application.

[0019] In addition, throughout the drawings, the same or similar reference numerals represent the same or similar elements. It should be understood that the drawings are schematic, and the elements and elements are not necessarily drawn according to the scale.

[0020] In the drawings.

[0021] Figure 1 is a schematic view of the front landing gear mounted to the fuselage body.

[0022] Figure 2 is an exploded view.

[0023] Figure 3 is a schematic view of the present patent.

[0024] Figure 4 is a sectional view.

[0025] Figure 5 is Figure 3 is an enlarged view of A of the present patent.

[0026] Figure 6 is Figure 4 an enlarged view of B part of

[0027] Reference signs:

[0028] 1, body; 2, bottom plate; 3, front lifting fixing box; 4, front wheel support rod; 5, front wheel sleeve; 6, front lifting fixing frame; 7, connecting frame; 8, body longitudinal rib; 9, body front cross rib; 10, mounting frame; 11, connecting strip; 12, connecting piece; 13, sliding cavity; 14, fixing strip; 15, fixing groove; 16, adjusting screw; 17, knob; 18, first mounting rod; 19, second mounting rod; 20, sliding plate; 21, connecting rod; 22, mounting groove. DETAILED DESCRIPTION

[0029] Embodiments of the present disclosure will be described in more detail with reference to the drawings. Although certain embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments set forth herein. Rather, these embodiments are provided so that the present disclosure will be more thoroughly and completely understood. It should be understood that the drawings of the present disclosure are only for illustrative purposes and are not intended to limit the scope of protection of the present disclosure.

[0030] It should also be noted that, for the sake of brevity, only the parts of the drawings that are relevant to the present application are shown. The embodiments in the present disclosure and the features in the embodiments can be combined with each other without conflict.

[0031] It should be noted that the terms "first", "second", and the like in the present disclosure are only used to distinguish different devices, modules or units, and are not intended to limit the order or interdependence of the functions performed by these devices, modules or units.

[0032] It should be noted that the terms "one", "multiple" in the present disclosure are illustrative and not restrictive, and those skilled in the art should understand that unless otherwise explicitly stated in the context, it should be understood as "one or more".

[0033] The present disclosure will be described in detail below with reference to the drawings and in conjunction with the embodiments.

[0034] Reference Figures 1-6The application discloses an aircraft front landing gear fixing structure, which comprises a fuselage body 1, a fuselage bottom plate 2, fuselage front ribs 9, fuselage longitudinal ribs 8, a front landing fixing box 3, a connecting assembly, a front wheel set 5 and a front wheel support rod 4. The fuselage bottom plate 2 is arranged at the bottom of the fuselage body 1. The two fuselage front ribs 9 are arranged at the bottom of the fuselage bottom plate 2. The fuselage longitudinal ribs 8 are arranged on the fuselage front ribs 9 and at the bottom of the fuselage bottom plate 2. The front landing fixing box 3 is arranged between the two fuselage front ribs 9.

[0035] The front landing fixing frame 6 is arranged on the front landing fixing box 3. The connecting assembly is used for connecting the front landing fixing box 3, the two fuselage front ribs 9 and the front landing fixing frame 6. The front wheel set 5 is arranged below the front landing fixing frame 6. The front wheel support rod 4 is arranged between the two front landing fixing frames 6 and the front wheel set 5.

[0036] The front landing fixing frame 6 comprises a connecting rod 21, the connecting rod 21 is fixedly connected with a connecting plate 12, and the connecting plate 12 is arranged on the front landing fixing box 3.

[0037] The connecting assembly comprises a first mounting rod 18, the first mounting rod 18 is fixedly connected with the connecting rod 21, the first mounting rod 18 penetrates through the front landing fixing box 3, a second mounting rod 19 is fixedly connected with each of the two ends of the two fuselage front ribs 9 which are close to each other, the second mounting rod 19 penetrates through the front landing fixing box 3, and a fixing assembly is arranged between the first mounting rod 18 and the two second mounting rods 19.

[0038] The fixing assembly comprises a mounting groove 22, the mounting groove 22 is arranged on the first mounting rod 18, the second mounting rod 19 is arranged on the mounting groove 22, a sliding cavity 13 is arranged on the first mounting rod, a sliding plate 20 is slidingly arranged on the sliding cavity 13, a fixing strip 14 is fixedly connected with the sliding plate 20, a fixing groove 15 is arranged on the second mounting rod, the fixing strip 14 corresponds to the fixing groove 15, and an adjusting assembly is arranged on the first mounting rod.

[0039] The adjusting assembly comprises an adjusting screw 16, the adjusting screw 16 is rotationally arranged on the inner wall of the sliding cavity 13, the adjusting screw 16 extends to the outside, and the adjusting screw 16 is in threaded connection with the sliding plate 20. A knob 17 is fixedly connected with the adjusting screw 16.

[0040] The connecting rod 21 is fixedly connected with a connecting strip 11, and the connecting strip 11 is arranged on the fuselage longitudinal rib 8. A connecting frame 7 is fixedly connected with the connecting strip 11. An installation frame 10 is fixedly connected with the fuselage longitudinal rib 8, the connecting frame 7 is movably connected with the installation frame 10, and the connecting frame 7 is arranged on the installation frame 10. The fixing strip 14 and the fixing groove 15 are both provided with two.

[0041] Working process: When installation is required, first install the connecting rod 21 by inserting it into the front starter mounting box 3. Then, install the connecting piece 12 into the front starter mounting box 3 by using the fixing bolts. Next, insert the second mounting rod 19 on the front cross rib 9 of the machine body into the front starter mounting box 3 and into the mounting groove 22. Then, rotate the knob 17 to rotate the adjusting screw 16, thereby moving the slide plate 20 and driving the fixing strip 14 to move into the fixing groove 15, thus fixing the second mounting rod 19. This secures the connecting rod 21... The front starting fixing box 3 and the front transverse rib 9 of the fuselage are connected together, which facilitates the subsequent welding of the front starting fixing box 3 and the front transverse rib 9 of the fuselage. At the same time, the connecting bracket 7 and the mounting bracket 10 can be connected together by fixing bolts to initially limit the longitudinal rib 8 and the front transverse rib 9 of the fuselage. Then, the longitudinal rib 8 of the fuselage can be welded to the front transverse rib 9 of the fuselage. The overall stability is improved by setting the connecting strip 11, which further improves the installation stability of the longitudinal rib 8 of the fuselage and the overall connection stability. Then, the front wheel strut 4 and the front wheel kit 5 can be installed by fixing bolts, which facilitates installation and improves installation efficiency.

[0042] The above description is merely a selection of preferred embodiments of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention involved in the embodiments of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described inventive concept. For example, technical solutions formed by substituting the above-described features with (but not limited to) technical features with similar functions disclosed in the embodiments of this disclosure.

Claims

1. An aircraft nose landing gear fixing structure, comprising: a fuselage body; a fuselage bottom plate arranged at the bottom of the fuselage body; characterized in that: the aircraft nose landing gear fixing structure further comprises: two fuselage front cross ribs arranged at the bottom of the fuselage bottom plate; a fuselage longitudinal rib arranged on the fuselage front cross ribs and at the bottom of the fuselage bottom plate; a front landing fixing box arranged between the two fuselage front cross ribs; a front landing fixing frame arranged on the front landing fixing box; a connecting assembly for connecting the front landing fixing box, the two fuselage front cross ribs and the front landing fixing frame; a front wheel set arranged below the front landing fixing frame; and a front wheel support rod arranged between the two front landing fixing frames and the front wheel set.

2. The aircraft nose landing gear fixing structure according to claim 1, characterized in that: the front landing fixing frame comprises a connecting rod, a connecting plate is fixedly connected to the connecting rod, and the connecting plate is arranged on the front landing fixing box.

3. The aircraft nose landing gear fixing structure according to claim 2, characterized in that: the connecting assembly comprises a first mounting rod fixedly connected to the connecting rod, the first mounting rod passes through the front landing fixing box, a second mounting rod is fixedly connected to each end of the two fuselage front cross ribs that are close to each other, the second mounting rod passes through the front landing fixing box, and a fixing assembly is arranged between the first mounting rod and the two second mounting rods.

4. The aircraft nose landing gear fixing structure according to claim 3, characterized in that: the fixing assembly comprises a mounting groove arranged on the first mounting rod and in which the second mounting rod is arranged, a sliding cavity is arranged on the first mounting rod, a sliding plate is slidingly arranged in the sliding cavity, a fixing strip is fixedly connected to the sliding plate, a fixing groove is arranged on the second mounting rod, the fixing strip corresponds to the fixing groove, and an adjusting assembly is arranged on the first mounting rod.

5. The aircraft nose landing gear fixing structure according to claim 4, characterized in that: the adjusting assembly comprises an adjusting screw that is rotationally arranged on the inner wall of the sliding cavity, extends to the outside, and is threadedly connected to the sliding plate.

6. The aircraft nose landing gear fixing structure according to claim 5, characterized in that: a knob is fixedly connected to the adjusting screw.

7. The aircraft nose landing gear fixing structure according to claim 2, characterized in that: a connecting strip is fixedly connected to the connecting rod and arranged on the fuselage longitudinal rib.

8. The aircraft nose landing gear fixing structure according to claim 7, characterized in that: a connecting frame is fixedly connected to the connecting strip, a mounting frame is fixedly connected to the fuselage longitudinal rib, the connecting frame is movably connected to the mounting frame, and the connecting frame is arranged on the mounting frame.

9. The aircraft nose landing gear fixing structure according to claim 4, characterized in that: the fixing strip and the fixing groove are each provided with two.

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