Retractable nose landing gear structure

Abstract

The utility model relates to the technical field of space flight and aviation, in particular to a retractable nose landing gear structure which comprises a nose wheel cabin door, a fuselage body is arranged on one side of the nose wheel cabin door, screws are connected to the surface of the nose wheel cabin door in a threaded mode, and reinforcing angle aluminum is installed on the inner wall of the fuselage body through the screws. And pedal push rods are arranged on one sides of the nose wheel cabin doors. When the undercarriage structure is used, the air flight resistance can be effectively reduced, the flight efficiency is greatly improved, the fuel consumption rate is reduced, better flight experience is provided for pilots, the flight safety is greatly improved, and the undercarriage is prevented from being damaged in the flight process.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, specifically a retractable front landing gear structure. Background Technology

[0002] With my country's increasing emphasis on the development of the aviation industry in recent years, light aircraft, which are closely related to the development of aviation, have also received more and more attention and development. The landing gear structure of light aircraft is mostly fixed and cannot be moved. With the increasing requirements for the flight performance and speed of model aircraft, the impact of fixed landing gear on the aerodynamic performance of model aircraft has also increased. A retractable nose landing gear structure is needed.

[0003] The existing nose landing gear structure does not retract into the fuselage. During flight, the friction with the air generates huge drag, affecting flight efficiency and increasing fuel consumption. In addition, the safety of the existing nose landing gear structure needs further improvement. This makes the landing gear structure increase drag during flight, significantly reduce flight efficiency, increase fuel consumption, greatly reduce flight safety, and easily lead to damage to the landing gear during flight. Utility Model Content

[0004] The purpose of this invention is to provide a retractable front landing gear structure to address the issue raised in the background art that the safety of the front landing gear structure during use needs further improvement.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a retractable front landing gear structure, including a nose wheel bay door, a fuselage body is provided on one side of the nose wheel bay door, screws are threaded onto the surface of the nose wheel bay door, reinforcing angle aluminum is installed on the inner wall of the fuselage body by screws, and a foot pedal is provided on one side of the nose wheel bay door.

[0006] Preferably, one end of the screw passes through the nose wheel bay door and is threadedly fastened to the surface of the fuselage body. The inner wall of the nose wheel bay door is equipped with a nose wheel fork, and the surface of the nose wheel fork is provided with a nose wheel body. The surface of the nose wheel body and the surface of the nose wheel fork rotate in mutual engagement.

[0007] Preferably, the inner wall of each of the reinforcing angle aluminum is provided with a first hydraulic cylinder, which rotates and engages with the inner wall of the reinforcing angle aluminum. The surface of each of the nose wheel hatches is provided with a rotating rocker arm, and the surface of the rotating rocker arm is provided with a push rod body. The push rod body rotates and engages with the rotating rocker arm and the inner wall of the nose wheel hatch respectively, and the push rod body engages with the first hydraulic cylinder.

[0008] Preferably, the inner wall of each of the reinforcing angle aluminum is provided with a gas spring, the gas spring and the inner wall of the reinforcing angle aluminum are mutually rotatably engaged, the gas spring and the push rod body are mutually engaged, the inner wall of each of the reinforcing angle aluminum is equipped with a second hydraulic cylinder, and a nose wheel rotation shaft is provided on one side of the nose wheel hatch, the nose wheel rotation shaft and the inner wall of the reinforcing angle aluminum are mutually rotatably engaged.

[0009] Preferably, the foot pedal push rod and the nose wheel rotation shaft cooperate with each other, the foot pedal push rod and the nose wheel body cooperate with each other, a hydraulic shock absorber is provided between the reinforcing angle aluminum, and the hydraulic shock absorber cooperates with the nose wheel rotation shaft.

[0010] Preferably, one end of the hydraulic shock absorber is fixed to the surface of the nose wheel fork, and the inner wall of the reinforcing angle aluminum is equipped with a triangular support rod, one end of which cooperates with the surface of the hydraulic shock absorber.

[0011] Compared with the prior art, the beneficial effects of this utility model are: the retractable front landing gear structure can effectively reduce the drag of the landing gear structure during flight, greatly improve flight efficiency, reduce fuel consumption, provide pilots with a better flight experience, greatly improve flight safety, and avoid damage to the landing gear during flight.

[0012] Equipped with a triangular support rod, push rod body, and gas spring, the user places the nose wheel door and reinforcing aluminum bracket at designated positions on the fuselage. The reinforcing aluminum bracket is then screwed onto the inner wall of the fuselage. Next, the user screws the nose wheel door onto the reinforcing aluminum bracket at its designated position. The extension and retraction of the second hydraulic cylinder rotates the triangular support rod, which in turn rotates the entire nose wheel body, nose wheel fork, and hydraulic shock absorber. The extension and retraction of the first hydraulic cylinder rotates the rocker arm, which in turn moves the push rod body up and down, completing the opening and closing of the nose wheel door. The nose wheel door is kept tangent to the curved surface of the fuselage when closed. At this time, the gas spring activates, providing a constant inward pressure to the nose wheel door via the push rod body, ensuring pressure throughout the flight. During the process, the nose wheel bay doors remain firmly tangent to the fuselage's curved surface without any displacement. The pilot can use a foot pedal connected to the nose wheel to steer the nose wheel, thus completing the aircraft's turning maneuver. The extension and retraction of the first hydraulic cylinder controls the nose landing gear, hydraulic shock absorbers absorb the impact load during landing, the foot pedal controls the left and right turns of the nose landing gear, and gas springs ensure the nose wheel bay doors remain firmly attached to the fuselage. This achieves a high level of safety for the landing gear structure, effectively reducing drag during flight, significantly improving flight efficiency, reducing fuel consumption, providing the pilot with a better flight experience, greatly enhancing flight safety, and preventing damage to the landing gear during flight. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0014] Figure 2 This is a three-dimensional structural diagram of the present invention;

[0015] Figure 3 This is a side view sectional structural diagram of the present invention;

[0016] Figure 4 This is a schematic diagram of the front cross-sectional structure of this utility model.

[0017] In the diagram: 1. Nose wheel bay door; 101. Nose wheel body; 102. Fuselage body; 103. Nose wheel fork; 104. Triangular support rod; 105. Push rod body; 106. Gas spring; 107. First hydraulic cylinder; 108. Second hydraulic cylinder; 109. Foot pedal push rod; 110. Nose wheel rotation shaft; 111. Reinforcing angle aluminum; 112. Hydraulic shock absorber; 113. Screw. Detailed Implementation

[0018] 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 embodiments of the present utility model, not all embodiments. In addition, the terms "first", "second", "third", "upper", "lower", "left", "right", etc. are used for descriptive purposes only and should not be construed as indicating or implying relative importance. At the same time, in the description of the present utility model, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. 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.

[0019] The present invention provides a retractable front landing gear structure, as follows: Figure 2 and Figure 3As shown, the system includes a nose wheel hatch 1, with a fuselage body 102 located on one side of the nose wheel hatch 1. Screws 113 are threaded onto the surface of the nose wheel hatch 1, with one end of each screw 113 penetrating the nose wheel hatch 1 and being threadedly fastened to the surface of the fuselage body 102. Nose wheel forks 103 are installed on the inner wall of the nose wheel hatch 1, and nose wheel bodies 101 are mounted on the surface of each nose wheel fork 103. The surfaces of the nose wheel bodies 101 and the nose wheel forks 103 rotate in relation to each other. The inner wall of the fuselage body 102 is connected via… All screws are fitted with reinforcing angle aluminum 111s. Each reinforcing angle aluminum 111 has a first hydraulic cylinder 107 mounted on its inner wall. The first hydraulic cylinder 107 rotates and engages with the inner wall of the reinforcing angle aluminum 111. Each nose wheel hatch 1 has a rotating rocker arm on its surface, and a push rod body 105 is mounted on the surface of the rotating rocker arm. The push rod body 105 rotates and engages with both the rotating rocker arm and the inner wall of the nose wheel hatch 1. The push rod body 105 engages with the first hydraulic cylinder 107. The reinforcing angle aluminum 111... Each of the following components has a gas spring 106 installed on its inner wall. The gas spring 106 rotates and engages with the inner wall of the reinforcing angle aluminum 111. The gas spring 106 also engages with the push rod body 105. A second hydraulic cylinder 108 is installed on the inner wall of each of the reinforcing angle aluminum 111. A nose wheel rotation shaft 110 is installed on one side of the nose wheel door 1. The nose wheel rotation shaft 110 rotates and engages with the inner wall of the reinforcing angle aluminum 111. A foot pedal push rod 109 is installed on one side of each of the nose wheel door 1. The foot pedal push rod 109 engages with the inner wall of the reinforcing angle aluminum 111. The nose wheel rotation shafts 110 are mutually engaged, the foot pedal push rod 109 is mutually engaged with the nose wheel body 101, and a hydraulic shock absorber 112 is provided between the reinforcing angle aluminum 111. The hydraulic shock absorber 112 is mutually engaged with the nose wheel rotation shaft 110, and one end of the hydraulic shock absorber 112 is fixed to the surface of the nose wheel fork 103. Triangular support rods 104 are installed on the inner wall of the reinforcing angle aluminum 111, and one end of the triangular support rod 104 is mutually engaged with the surface of the hydraulic shock absorber 112.

[0020] In practice, the user places the nose wheel hatch 1 and the reinforcing angle aluminum 111 at designated positions on the fuselage body 102, and installs the reinforcing angle aluminum 111 on the inner wall of the fuselage body 102 with screws. Then, the user installs the nose wheel hatch 1 at the designated position of the reinforcing angle aluminum 111 with screws 113. The extension and retraction of the second hydraulic cylinder 108 drives the rotation of the triangular support rod 104, thereby driving the rotation of the entire nose wheel body 101, nose wheel fork 103, and hydraulic shock absorber 112. Under the extension and retraction of the first hydraulic cylinder 107, the rocker arm rotates, thereby driving the push rod body 105 to move up and down, completing the opening and closing action of the nose wheel hatch 1, keeping the nose wheel hatch 1 closed and the fuselage body closed. When the nose wheel is tangent to the curved surface of fuselage 102, the gas spring 106 starts to work, and the push rod body 105 continuously applies an inward pressure to the nose wheel door 1, ensuring that the nose wheel door 1 remains firmly tangent to the curved surface of fuselage 102 throughout the entire flight without displacement. The pilot can use the foot pedal push rod 109 connected to the nose wheel body 101 to turn the nose wheel body 101, thereby completing the aircraft's turning behavior. The extension and retraction of the nose landing gear is completed by the extension and retraction of the first hydraulic cylinder 107, the hydraulic shock absorber 112 is used to absorb the impact load during landing, the foot pedal push rod 109 is used to turn the nose landing gear left and right, and the gas spring 106 is used to ensure that the nose wheel door 1 remains close to the fuselage.

[0021] Working principle: In use, first place the nose wheel hatch 1 in the designated position. The user places the nose wheel hatch 1 and the reinforcing angle aluminum 111 in the designated positions of the fuselage body 102, respectively. The reinforcing angle aluminum 111 is then installed on the inner wall of the fuselage body 102 with screws. Subsequently, the user installs the nose wheel hatch 1 in the designated position of the reinforcing angle aluminum 111 with screws 113. The extension and retraction of the second hydraulic cylinder 108 drives the rotation of the triangular support rod 104, thereby driving the rotation of the entire nose wheel body 101, nose wheel fork 103, and hydraulic shock absorber 112. Under the extension and retraction of the first hydraulic cylinder 107, the rocker arm rotates, thereby driving the push rod body 105 to move up and down, completing the opening and closing action of the nose wheel hatch 1. The nose wheel hatch 1 is kept in a closed state tangent to the curved surface of the fuselage body 102. At this time, the gas spring 106 starts to work, and the push rod body 105 continuously applies an inward pressure to the nose wheel hatch 1. The system ensures that the nose wheel door 1 remains firmly tangent to the curved surface of the fuselage body 102 throughout the entire flight, without any displacement. The pilot can use the foot pedal 109 connected to the nose wheel body 101 to turn the nose wheel body 101, thus completing the aircraft's turning behavior. The extension and retraction of the nose landing gear are achieved by the extension and retraction of the first hydraulic cylinder 107. The hydraulic shock absorber 112 absorbs the impact load during landing. The foot pedal 109 is used to turn the nose landing gear left and right. The gas spring 106 ensures that the nose wheel door 1 remains close to the fuselage, thus achieving the high safety function of the landing gear structure. This allows the landing gear structure to effectively reduce drag during flight, significantly improve flight efficiency, reduce fuel consumption, provide the pilot with a better flight experience, greatly improve flight safety, and prevent damage to the landing gear during flight, ultimately completing the use of the nose landing gear structure.

[0022] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A retractable nose landing gear structure comprising a nose wheel bay door (1), characterized in that: One side of the nose wheel cabin door (1) is provided with a fuselage body (102), the surface of the nose wheel cabin door (1) is screw connected with a screw (113), the inner wall of the fuselage body (102) is screw connected with a reinforced aluminum angle (111), and one side of the nose wheel cabin door (1) is provided with a foot pedal push rod (109).

2. A retractable nose landing gear arrangement according to claim 1, characterised in that: One end of the screw (113) penetrates the nose wheel cabin door (1) and is threadedly fastened with the surface of the fuselage body (102), the inner wall of the nose wheel cabin door (1) is provided with a nose wheel fork (103), and the surface of the nose wheel fork (103) is provided with a nose wheel body (101).

3. A retractable nose landing gear arrangement according to claim 1, wherein: The inner wall of the reinforced aluminum angle (111) is provided with a first hydraulic cylinder (107), the first hydraulic cylinder (107) is rotatably connected with the inner wall of the reinforced aluminum angle (111), the surface of the nose wheel cabin door (1) is provided with a rotary rocker arm, the surface of the rotary rocker arm is provided with a push rod body (105), the push rod body (105) is rotatably connected with the rotary rocker arm and the inner wall of the nose wheel cabin door (1), and the push rod body (105) is rotatably connected with the first hydraulic cylinder (107).

4. A retractable nose landing gear arrangement according to claim 1, wherein: The inner wall of the reinforced aluminum angle (111) is provided with a gas spring (106), the gas spring (106) is rotatably connected with the inner wall of the reinforced aluminum angle (111), the gas spring (106) is rotatably connected with the push rod body (105), the inner wall of the reinforced aluminum angle (111) is provided with a second hydraulic cylinder (108), one side of the nose wheel cabin door (1) is provided with a nose wheel rotating shaft (110), and the nose wheel rotating shaft (110) is rotatably connected with the inner wall of the reinforced aluminum angle (111).

5. A retractable nose landing gear arrangement according to claim 1, wherein: The foot pedal push rod (109) is rotatably connected with the nose wheel rotating shaft (110), the foot pedal push rod (109) is rotatably connected with the nose wheel body (101), the reinforced aluminum angles (111) are provided with a hydraulic shock absorber (112), and the hydraulic shock absorber (112) is rotatably connected with the nose wheel rotating shaft (110).

6. A retractable front landing gear arrangement according to claim 5, wherein: One end of the hydraulic shock absorber (112) is fixedly connected with the surface of the nose wheel fork (103), the inner wall of the reinforced aluminum angle (111) is provided with a triangular support rod (104), and one end of the triangular support rod (104) is rotatably connected with the surface of the hydraulic shock absorber (112).

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