A long-flight aircraft

Abstract

Conventional aircraft usually have only a single wing, and in order to have long flight capabilities, slender wings are usually used, but this increases the risk of wing breakage and reduces safety. At the same time, the width of the entire aircraft is too large, and a wider runway is required for takeoff and landing, which is inconvenient to use. The present invention takes increasing the aircraft's flight time as the main goal, taking into account ease of use, and provides a long-flight aircraft design with a new overall layout. The design adopts a two-wing design with a moderate wing length and a high wing projection area, which can reduce flight power consumption and increase flight time. At the same time, it also avoids the problems of reduced flight safety and inconvenience in use caused by excessively long wings. The long-flight aircraft according to the present invention has a long flight time, is easy to use, and has high structural safety.

Description

Technical Field

[0001] The invention relates to a long-flight aircraft and belongs to the field of aviation design. Background Art

[0002] The flight time of long-flight aircraft is generally more than 24 hours. A single flight can perform missions for more than a day without interruption. It has low maintenance costs and can efficiently meet application needs in wide-area surveillance, search and tracking, territorial waters patrol, border inspection, long-distance UHV transmission line inspection, forest fire monitoring, persistent communication relay in disaster areas, meteorological research, etc. It occupies an irreplaceable position in both military and civil aircraft.

[0003] For long-flight aircraft, the larger the wing projected area, the lower the speed at which it can fly, the less power it consumes in flight, and this helps to increase the aircraft's flight time. However, conventional long-flight aircraft only have a single wing. If the wing area is increased, the length of the wing will increase significantly, increasing the risk of wing breakage and affecting flight safety. In addition, longer wings will cause the entire aircraft to be too wide, making it impossible to take off or land on roads or small airport runways, which places certain restrictions on the use of the aircraft. The above-mentioned defects of reduced flight safety and inconvenience in use limit the increase in the wing projected area and flight time of conventionally arranged aircraft. Summary of the invention

[0004] According to one aspect of the present invention, there is provided a long-flight aircraft, characterized in that it comprises:

[0005] Propeller, fuselage, landing end plate, front wing, rear wing, tail strut, vertical tail and horizontal tail,

[0006] in:

[0007] The propeller is located at the head of the fuselage.

[0008] The front wing and the rear wing are both mounted on the fuselage, and the landing end plate is installed in the middle of the front wing.

[0009] The vertical tail and horizontal tail are located behind the fuselage and are mounted on the fuselage through the tail support.

[0010] The front and rear wings are both slender wings.

[0011] The outer ends of the front and rear wings are equipped with crescent-shaped winglets to improve the airflow conditions at the front and rear wing tips and increase aerodynamic efficiency.

[0012] The front wing is located at the bottom of the fuselage, and the rear wing is located at the top of the fuselage. The front wing and the rear wing are separated by a certain distance in the height direction and a certain distance in the front and rear directions.

[0013] A pair of ailerons are installed on the outside of the rear wing to control the aircraft's roll attitude.

[0014] The overall fuselage is slender and streamlined.

[0015] The parts where the fuselage is connected to the front wing and the rear wing are all equipped with fairings to ensure a smooth connection between the fuselage, the front wing and the rear wing.

[0016] The vertical tail is installed on the tail strut, and the horizontal tail is installed at the lower part of the vertical tail.

[0017] The rear half of the vertical tail is the rudder, which is used to adjust the aircraft's heading by its deflection. The two landing end plates are installed in the middle of the front wing and are the first to touch the ground when the aircraft lands, thus protecting the propeller. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 1 is a schematic isometric view of a long-flight aircraft according to an embodiment of the present invention.

[0019] Figure 2 yes Figure 1 A schematic side view of a long-flight aircraft according to the illustrated embodiment.

[0020] Figure 3 yes Figure 1 A schematic top view of a long-flight aircraft according to the illustrated embodiment.

[0021] Figure 4 yes Figure 1 A schematic front view of a long-flight aircraft of the illustrated embodiment. DETAILED DESCRIPTION

[0022] In order to achieve higher aerodynamic efficiency, long-flight aircraft need to use longer wings to increase the wing projection area. However, the requirements of flight safety and ease of use require limiting the overall length of the wing. Therefore, in order to achieve better endurance performance and overcome the above-mentioned problems of the prior art, it is necessary to adopt an innovative layout. To this end, the present invention provides a long-flight aircraft with a new overall layout.

[0023] like Figures 1 to 4 As shown, a long-flight aircraft according to an embodiment of the present invention comprises a propeller (1), a fuselage (2), a landing end plate (3), a front wing (4), a rear wing (5), a tail strut (6), a vertical tail (7) and a horizontal tail (8). The propeller (1) is located at the head of the fuselage (2). The front wing (4) and the rear wing (5) are both mounted on the fuselage (2), and the landing end plate (3) is mounted in the middle of the front wing (4). The vertical tail (7) and the horizontal tail (8) are located behind the fuselage (2) and are mounted on the fuselage (2) through the tail strut (6).

[0024] 1) Wing

[0025] like Figure 3 As shown, the lengths of the front wing (4) and the rear wing (5) are both moderate, and the sum of the projected areas is relatively large. The front wing (4) and the rear wing (5) are both slender wings, which have relatively small drag while generating relatively large lift, and have high aerodynamic efficiency. The outer ends of the front wing (4) and the rear wing (5) are both provided with crescent-shaped winglets (9), which can improve the airflow conditions at the tips of the front wing (4) and the rear wing (5), and further improve the aerodynamic efficiency.

[0026] like Figure 2 As shown, the front wing (4) is located at the bottom of the fuselage (2), and the rear wing (5) is located at the top of the fuselage (2). The front wing (4) and the rear wing (5) are spaced a certain distance apart in the height direction and also have a certain distance in the front-rear direction. Figure 1 and Figure 3 As shown, a pair of ailerons (10) are provided at the outer position of the rear wing (5) to control the rolling attitude of the aircraft.

[0027] 2) Body

[0028] like Figure 1 and Figure 4 As shown, the fuselage (2) is in a relatively slender streamlined shape as a whole, and the parts where the fuselage (2) is connected to the front wing (4) and the rear wing (5) are all provided with fairings (11), so that the fuselage (2) and the front wing (4) and the rear wing (5) are smoothly connected, which can reduce the aerodynamic interference between the fuselage (2) and the front wing (4) and the rear wing (5), thereby reducing the resistance of the aircraft.

[0029] 3) Tail

[0030] like Figure 1 , Figure 2 As shown, the vertical tail (7) is installed on the tail support (6), and the horizontal tail (8) is installed at the lower part of the vertical tail (7). The rear half of the vertical tail (7) is a rudder (12), and the rudder (12) can adjust the heading of the aircraft when it is deflected. The vertical tail (7) and the horizontal tail (8) are located behind the fuselage (2) to ensure the stability of the aircraft flight.

[0031] 4) Landing end plate

[0032] like Figure 1 As shown, two landing end plates (3) are installed in the middle of the front wing (4) and are the first to touch the ground when the aircraft lands, so as to protect the propeller (1). Figure 4 As shown, the distance between the two landing end plates (3) is relatively large, which can provide a higher sliding stability when the aircraft lands, thereby improving the safety of the aircraft during landing. The landing end plates (3) are light in weight and have low resistance, which is conducive to long-duration flight.

[0033] The advantages and beneficial effects of the present invention include:

[0034] 1) The two-wing design increases the wing projection area while limiting the wing length, thus reducing power consumption and increasing flight time while avoiding problems such as reduced flight safety and inconvenience caused by excessively long wings.

[0035] 2) Different from the traditional biplane, the front wing of the solution of the present invention is below the rear wing, and the two wings are separated by a large distance, so the aerodynamic interference between them is small.

[0036] 3) Both the front wing and the rear wing are slender wings, and there is no additional connection or support between the two, so they have low resistance, high lift and high aerodynamic efficiency.

[0037] 4) The fuselage is streamlined and is connected to the wings through a fairing, so the flight resistance is small.

[0038] 5) The vertical tail and horizontal tail are located at the tail of the aircraft, farther away from the fuselage, which can provide better stability and maneuverability.

[0039] 6) The landing end plate can protect the propeller during the aircraft landing process, improve landing safety, and is light in weight and has low resistance, which is conducive to long-duration flight.

Claims

1. A long-flight aircraft, characterized in that include: Propeller (1), fuselage (2), landing end plate (3), front wing (4), rear wing (5), tail strut (6), vertical tail (7) and horizontal tail (8), in: The propeller (1) is located at the head of the fuselage (2). The front wing (4) and the rear wing (5) are both mounted on the fuselage (2), and the landing end plate (3) is mounted in the middle of the front wing (4). The vertical tail (7) and the horizontal tail (8) are located behind the fuselage (2) and are mounted on the fuselage (2) via a tail support (6). The front wing (4) and the rear wing (5) are both slender wings. The outer ends of the front wing (4) and the rear wing (5) are both provided with crescent-shaped winglets (9) to improve the airflow conditions at the tips of the front wing (4) and the rear wing (5) and to enhance the aerodynamic efficiency. The front wing (4) is located at the bottom of the fuselage (2), and the rear wing (5) is located at the top of the fuselage (2). The front wing (4) and the rear wing (5) are spaced a certain distance apart in the height direction and a certain distance apart in the front-rear direction. A pair of ailerons (10) are provided at the outer side of the rear wing (5) to control the rolling attitude of the aircraft. The fuselage (2) is in an overall slender streamlined shape. The parts where the fuselage (2) is connected with the front wing (4) and the rear wing (5) are all provided with fairings, so that the fuselage (2) is smoothly connected with the front wing (4) and the rear wing (5). The vertical tail wing (7) is installed on the tail support (6), and the horizontal tail wing (8) is installed at the lower part of the vertical tail wing (7). The rear half of the vertical tail (7) is a rudder (12), which is used to adjust the heading of the aircraft by its deflection. Two landing end plates (3) are installed in the middle of the front wing (4) and are the first to touch the ground when the aircraft lands, so as to protect the propeller (1).

2. The long-flight aircraft according to claim 1, characterized in that: The distance between the two landing end plates (3) provides sliding stability when the aircraft lands.

3. The long-flight aircraft according to claim 1, characterized in that: The landing end plate (3) is made of a light material with low resistance, so as to facilitate long-duration flight.

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