CN102139757A - Framed front center fuselage suitable for unmanned plane and model plane - Google Patents

Abstract

Provided is a framed front center fuselage suitable for unmanned aerial vehicles and model aircraft, comprising: a plurality of bulkheads, which form and maintain the outline of the front center fuselage; longitudinally arranged along the outline of the front center fuselage A number of carbon fiber beams connect the bulkheads to form the main structure of the front center fuselage. The advantages of the present invention include: 1) the structure adopts a frame type, the common partition frame and the reinforced frame are alternated, the former is three-dimensional, and the latter is also used to connect the wings, landing gear, rear fuselage, front fuselage, etc. The leather, girders and stringers play a supporting role; 2) The layered design of the internal space can meet the needs of loading and delivery. The upper and lower layers are used to arrange fuel tanks and pipelines, etc., and the middle is used to place goods to be delivered. and airborne equipment, with high space utilization; 3) In the middle of the fuselage, the reinforcement frame is reasonably arranged, and the installation of wings and landing gear is realized by connecting the lugs; 4) The front fuselage and the middle fuselage are connected by hinges, which can be opened. Convenient maintenance and loading and unloading of goods.

Description

A framed front-middle fuselage suitable for UAVs and model aircraft

technical field

The invention relates to the design of a framed front-middle fuselage suitable for unmanned aerial vehicles and large-scale model aircraft, and belongs to the field of aviation vehicle component design.

Background technique

The fuselage is the base for installing various structural components and functional systems of the aircraft. In addition to providing the installation foundation for other components (such as wings, empennage, and landing gear, etc.) and the installation space for airborne equipment, the fuselage also bears the loads from these components, and needs to meet mechanical requirements such as strength and stiffness. And it is required to achieve the lightest structural mass to improve structural efficiency.

Modern drones and large-scale model aircraft have high design requirements for the fuselage, often requiring large internal space and light structure weight. It is a better solution to use a framed fuselage with high structural efficiency on this type of aircraft.

Contents of the invention

According to one aspect of the present invention, there is provided a frame type front center fuselage suitable for unmanned aerial vehicles and model aircraft, which is characterized in that it comprises:

a plurality of bulkheads forming and maintaining the profile of the front center fuselage,

A plurality of carbon fiber beams longitudinally arranged along the outline of the front center fuselage are used to connect each of the bulkheads to form the main structure of the front center fuselage.

Description of drawings

Figure 1 shows the position of the mid-fuselage in the aircraft structure according to one embodiment of the invention.

Fig. 2 shows the structural composition of the mid-fuselage according to an embodiment of the present invention.

Fig. 3 shows a schematic cross-sectional view of the space division of the middle fuselage of the embodiment shown in Fig. 2 .

Fig. 4 shows a schematic diagram of the arrangement of the fuel tank in the middle fuselage according to an embodiment of the present invention.

Fig. 5 shows a schematic diagram of connecting tabs between the mid-fuselage and the wing according to an embodiment of the present invention.

Fig. 6 shows a schematic diagram of connecting lugs between the middle fuselage and the main landing gear according to an embodiment of the present invention.

Fig. 7 shows a schematic diagram of the connection between the middle fuselage and the front nose according to an embodiment of the present invention.

Fig. 8 shows a schematic diagram of the connection between the middle fuselage and the rear fuselage according to an embodiment of the present invention.

Detailed ways

Aiming at the design requirements of large internal space fuselage required by large-scale transport aircraft and airliner scale-down verification aircraft and large-scale models, the present inventor proposes a frame-type medium fuselage design scheme. In order to make efficient and reasonable use of the internal space of the fuselage, the design scheme divides the internal space of the middle fuselage into upper, middle and lower floors by installing ceilings and floors. Conformal fuel tanks are arranged on the upper and lower floors. The front lower layer of the middle fuselage is equipped with a front landing gear installation foundation and a front landing gear compartment. The middle upper layer of the middle fuselage and the central wing box form an integral closed structure. The lower layer of the middle fuselage is connected to the main landing gear through the adapter lug. The rear part of the middle fuselage is connected with the rear fuselage by means of end-to-face connection.

Unmanned aerial vehicles (UAVs) and large-scale model aircraft, such as scaled-down verification aircraft for large transport aircraft and passenger aircraft, have high requirements for the internal space and structural quality of the fuselage, as well as the carrying capacity. Which technical solution to adopt is a key issue in the design of this type of aircraft fuselage. The present invention realizes the design of a medium fuselage with high load-bearing efficiency and large internal space through rational design of the form, structure, space and function distribution of the framed fuselage.

The following describes the technical solutions for the specific implementation of the present invention.

1) The form and structure of the fuselage in the frame type.

According to the overall shape structure of an aircraft according to an implementation example of the present invention, as shown in Figure 1, the middle fuselage is located at the middle and front of the aircraft fuselage, and the wings, rear fuselage, nose and landing gear are connected as a whole. The position (10) shown in Fig. 1 is a schematic diagram of the position of the middle fuselage in the aircraft.

The structural composition of the middle fuselage is shown in Figure 2. There are mainly several bulkheads (1) forming the outline, and a number of (such as 4) carbon fiber beams (3) are arranged longitudinally along the fuselage, and several stringers (8) The individual bulkheads are connected together to form the main structure of the framed fuselage. The front landing gear installation part (5) is reserved in the front part of the fuselage, and a reinforced partition frame (7) is provided in the middle part to install parts such as landing gear.

A reinforcing frame (7) is arranged at the connecting part between the middle part of the fuselage and the wing, and is connected with the wing through the lugs. Through the ingenious design of the lugs, it not only meets the load transmission requirements, but also accurately guarantees the design requirements such as wing installation angle and sweep angle. As in the embodiment of the present invention shown in Fig. 5, aluminum alloy tab (52) is fixed on the middle fuselage reinforcement frame (51) by bolt (53), and is connected by the connecting pin passing hole (54) The corresponding lugs on the wing are plugged together to realize the assembly of the wing and the fuselage, so as to realize simple installation and precise positioning.

The middle fuselage of the present invention is connected with the retractable main landing gear and the retractable and steerable front landing gear through the reinforcing frame. In the embodiment of the invention shown in Figure 6, the mounting lugs (63) are fixed on the reinforcement bulkhead (7) with bolts passing through the holes (62), and the main landing gear ( 65) Install on the fuselage to realize installation and positioning. A total of multiple lugs are used to transfer the load of a pair of main landing gear to the fuselage. A rectifying bulge cabin is designed at the installation position of the main landing gear to accommodate the main landing gear and reduce fuselage resistance, and an inspection cover is arranged on the rectifying bulge of the main landing gear to facilitate maintenance and overhaul.

According to an embodiment of the present invention, the front fuselage and the middle fuselage are connected by hinges, and can be opened to facilitate maintenance and loading and unloading of goods. As in the embodiment shown in Figure 7, in the front nose (73) inner wall, a curved rocking arm (72) is installed, and the base (74) is embedded in the middle fuselage inner wall, and the rocking arm (72) is connected by a hinge. ) is connected with the base (74), the front nose can be opened forward/upwards easily.

According to the present invention, the middle fuselage is connected with the rear fuselage in an end-to-face butt joint manner. The connection method according to one embodiment of the present invention is shown in Figure 8, wherein a polished rod (81) is installed in the middle fuselage, and a clamping device (82) is embedded inside the end face bulkhead (84) of the rear fuselage (80). , reserve screw fastening hole (83) at rear fuselage side wall, utilize the screw that passes fastening hole (83) to make clasping device (82) deformation and polish rod (81) lock, realize positioning.

2) Division and utilization of each space.

Figures 3 and 4 show the division and utilization of the interior space of the fuselage according to an embodiment of the present invention; the ceiling (4) and the floor (6) divide the cabin into three parts, and the upper and lower parts are used to install the fuel tank, thereby effectively The irregular corner area is used, the fuel loading capacity is increased, and the voyage time and range are extended. At the same time, considering the connection relationship between the wings, the landing gear, the airborne equipment and the fuselage, fuel tanks (2) of different specifications are installed on the top and bottom of the fuselage according to different position spaces. Several fuel tanks (2) can be installed on the ceiling (4), and fuel tanks (2) can also be installed below the floor (6). At the same time, the ceiling (4) and the floor (6) are designed as detachable structures, which is convenient for maintenance, loading and unloading of fuel tanks, and convenient arrangement of various system pipelines. The fuel tank adopts a split type and is embedded between the bulkheads, which is also convenient to control the influence of fuel consumption on the position of the center of gravity of the aircraft.

Advantages/beneficial effects

Advantages and/or beneficial effects of the present invention include:

1) The structure adopts the frame type. Ordinary bulkheads are alternated with reinforced frames, the former is dimensionally shaped, and the latter is also used to connect wings, landing gear, rear fuselage, front fuselage, etc., both of which support the skin, girders and stringers. While maintaining the rigidity and strength of the fuselage, it also ensures the space requirements inside the fuselage.

2) The layered design of the internal space can meet the needs of loading and delivery. The upper and lower floors are used to arrange fuel tanks and pipelines, etc., and the middle is used to place goods to be delivered and airborne equipment, with high space utilization.

3) In the middle of the fuselage, the cloth reinforcement frame is reasonably arranged, and the installation of the wings and landing gear is realized by connecting the lugs. Through the ingenious design of the lugs, it not only meets the load transmission requirements, but also accurately guarantees the design requirements such as wing installation angle and sweep angle. The retractable main landing gear and the retractable and steerable nose landing gear are directly connected to the reinforced bulkhead through the lugs. A rectifying bulge cabin is designed at the installation position of the main landing gear to accommodate the main landing gear, reduce the fuselage resistance, and An inspection cover is arranged on the fairing drum of the main landing gear to facilitate maintenance and inspection.

4) The front fuselage and the middle fuselage are connected by hinges and can be opened to facilitate maintenance and loading and unloading. It is connected to the rear fuselage by end-to-face connection, and a quick-release joint is installed on the docking frame, which is convenient for disassembly and transportation.

Applied the example of the embodiment of the present invention: large aircraft scaling verification machine design

The free flight test of the scaled model has low cost, little interference, realistic condition simulation, and no pilot safety issues, and plays an important role in aircraft development.

According to the embodiment of the present invention, the large aircraft scaling verification machine adopts the upper single-wing layout, which has good stability. Four turbojet engines are hung under the wings, and the frame-type middle fuselage is adopted to reasonably and effectively bear the aerodynamic and loading loads. The space requirements for loading and aerial simulation delivery are met. By dividing the cabin space, the fuel load is increased without occupying the loading space, and the voyage time/range is increased. The beams, stringers and skin of the framed fuselage jointly participate in the transfer and balance of loads, which improves the weight efficiency and effectively reduces the structural weight. The mid-fuselage also realizes detachable and stable connections with the wings, landing gear, nose and rear fuselage through the reinforcement frame.

It should be understood that the description of the present invention in the foregoing description and description is only illustrative and not limiting, and that the above-described embodiments may be modified without departing from the present invention as defined in the appended claims. Various changes, deformations, and/or corrections.

Claims (9)

1. A framed front-middle fuselage suitable for unmanned aerial vehicles and large-scale scale model aircraft, characterized in that it includes: a plurality of bulkheads (1), which maintain and constitute the outline of the front middle fuselage, A plurality of carbon fiber beams (3) longitudinally arranged along the outline of the front center fuselage are used to connect each of the bulkheads (1) to form the main structure of the front center fuselage. 2. The framed front center fuselage according to claim 1, further comprising: The front landing gear installation part (5) reserved at the front part of the front center fuselage is used for installing the landing gear; A reinforcing frame (7, 51) arranged at the middle part of the front middle fuselage. (7) is used for installing main landing gear, and (51) is used for installing wing. 3. The framed front center fuselage according to claim 2, characterized in that At least one of said reinforcing bulkheads (51) is adapted to be fixedly connected to wing connecting lugs (52) by bolts (53), and said wing connecting lugs (52) have holes (54), thereby being suitable for The connecting pin passing through the hole (54) is plugged together with the corresponding lugs on the wing, so as to realize the connection between the wing and the front middle fuselage. 4. The framed front center fuselage according to claim 2, characterized in that at least one of said reinforcing frames (7); adapted to be fixedly connected to said undercarriage attachment lugs (63) by means of bolts passing through holes (62) on said undercarriage attachment lugs (63), Wherein said landing gear connecting lug (63) is suitable for main landing gear (65) is installed on the said landing gear connecting lug (63) by landing gear connecting pin (64), thereby said main landing gear Falling frame (65) is installed on the said front middle fuselage of the road. 5. The framed front center fuselage according to claim 4, characterized in that The main landing gear (65) is connected to a plurality of bulkheads (1) and/or reinforcing bulkheads (7) through a plurality of landing gear connecting lugs (63), thereby transferring the load of the main landing gear to the fuselage; A rectifying bulge cabin is designed at the installation position of the main landing gear to accommodate the main landing gear and reduce fuselage resistance, and an inspection cover is arranged on the rectifying bulge of the main landing gear to facilitate maintenance and overhaul. 6. according to any one frame type front center fuselage in claim 1-4, it is characterized in that A pedestal (74) is pre-embedded in the inner wall of the front middle fuselage, and is used to connect the curved rocker arm (72) installed on the inner wall of a front nose (73) with the pedestal (74) through a hinge , so that the front nose can be opened forward/upward conveniently. 7. according to any one frame type front center fuselage in the claim 1-4, it is characterized in that A polished rod (81) is installed on the front middle fuselage, and the polished rod (81) is suitable for being embedded in a clasping device (82) inside the end face bulkhead frame (84) of a rear fuselage (80). ) locked, Wherein, a screw fastening hole (83) is reserved on the side wall of the rear fuselage, and the tightening device (82) is deformed by the screw passing through the fastening hole (83) to lock the polished rod (81). 8. According to any one of the frame type front middle fuselage in claim 1-4, it is characterized in that The inside of the front center fuselage is divided into three parts by a ceiling (4) and a floor (6). 9. The framed front center fuselage according to claim 8, characterized in that The upper and lower parts of the three parts are used to install the fuel tank; The ceiling (4) and the floor (6) are detachable structures, so as to facilitate maintenance, loading and unloading of oil tanks and/or arrangement of various system pipelines, The fuel tank adopts a split type and is embedded between the bulkhead (1) and/or the reinforcement frame (7), so as to facilitate the control of the influence of fuel consumption on the position of the center of gravity of the aircraft.

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