CN101804865A - Small multi-purpose unmanned aerial vehicle - Google Patents

Abstract

A small multi-purpose UAV that can be used to perform missions such as scientific research experiments, remote sensing detection, and aerial photography. The UAV has the following characteristics: 1) It has a long battery life, which is convenient for flying missions that require high flight time; 2) It is easy to use and easy to operate; 3) It has good stability and is suitable for carrying autopilots and aerial cameras , cameras and other equipment; 4) lower requirements for take-off and landing conditions. A small unmanned aerial vehicle according to one aspect of the present invention includes: a fuselage; a wing connected to the fuselage; an empennage; a tail support for realizing the connection between the empennage and the fuselage; (1) The engine (10) at the front end; The propeller (11) driven by the engine (10) is used to provide the pulling force required for flight for the aircraft. The UAV according to another aspect of the present invention further includes a modular loading design including a floor support plate (32) located in the middle of the fuselage (1) for mounting onboard equipment.

Description

A small multipurpose drone

technical field

The invention relates to the design of a small multi-purpose unmanned aerial vehicle, which belongs to the field of structural design of aviation aircraft, in particular to the structural design of a small unmanned aerial vehicle that requires a relatively long endurance time.

Background technique

The cost of UAV is relatively low, it can avoid the casualties of drivers, and it can perform many tasks that man-machines cannot perform. It has broad application prospects.

Existing UAVs mainly use a simple box-shaped fuselage and a conventional hexahedron-shaped fuel tank, which has high flight resistance, low utilization rate of internal space, small amount of fuel carried, and short voyage time. And most of them are tailor-made according to specific task loads, and the versatility of task load loading is not strong; it is not very convenient to carry out loading tests on loads that have not been formally finalized, and sometimes even requires modification of the body structure.

Contents of the invention

In view of the above-mentioned problems in the prior art, the inventor has developed a UAV with a V-tail layout in which the fuel tank is embedded in the wing-body fusion body.

The unmanned aerial vehicle of the present invention is mainly used for carrying out flight missions such as scientific research experiments, remote sensing detection and aerial photography. The UAV has the following characteristics: 1) It has a long battery life, which is convenient for flying missions that require high flight time; 2) It is easy to use and easy to operate; 3) It has good stability and is suitable for carrying autopilots and aerial cameras , cameras and other equipment; 4) lower requirements for take-off and landing conditions.

According to one aspect of the present invention, there is provided a small unmanned aerial vehicle, which is characterized in that it includes: a fuselage; a wing connected to the fuselage; an empennage; Connection.

According to a further aspect of the present invention, the above-mentioned small UAV further includes: an engine installed at the front end of the fuselage; and a propeller driven by the engine, which is used to provide the aircraft with the pulling force required for flight.

According to a further aspect of the present invention, the above-mentioned small unmanned aerial vehicle further includes: a cabin cover arranged on the upper part of the fuselage, which defines a cabin with the fuselage; wherein the fuselage is a The flat lifting body of an airfoil.

According to a further aspect of the present invention, the above-mentioned empennage is a V-shaped empennage, and the trailing edge of the empennage is provided with a control surface, so that the functions of the elevator and rudder can be realized through the V-tail mixed control mode. The UAV according to another aspect of the present invention further includes a modular loading design, including a floor support plate (32) located in the middle of the fuselage (1) for mounting on-board equipment.

Description of drawings

Fig. 1 shows the overall appearance of a small UAV according to an embodiment of the present invention.

Fig. 2 shows a schematic diagram of an oil tank arrangement according to an embodiment of the present invention.

Fig. 3 shows a schematic diagram of the connection of the fuel tank according to an embodiment of the present invention.

Fig. 4 shows a schematic diagram of a base plate according to an embodiment of the present invention.

Fig. 5 shows a schematic diagram of installation of equipment and a base plate according to an embodiment of the present invention.

Fig. 6 shows the device installation and effect diagram according to an embodiment of the present invention.

Detailed ways

In order to solve the problems of the existing small unmanned aerial vehicle, such as the small range and flight time, and the "disassembly-installation" mode of the airborne equipment takes a long time and the process is cumbersome; a basic aspect of the present invention is to provide a small resistance , A small unmanned aerial vehicle with a reasonable structural design, which can quickly load and unload airborne equipment.

A further aspect of the present invention is to provide a small unmanned aerial vehicle solution with small resistance, large fuel capacity, long flight time, and the ability to perform long-distance flight missions. Quick loading and unloading of airborne equipment.

According to an embodiment of the present invention, it is mainly realized through the rational design and assembly debugging of the overall layout of the V-tail layout UAV of the wing-body fusion.

According to a further embodiment of the present invention, the overall layout of the V-tail layout UAV with the fuel tank embedded in the wing-body fusion body, the design of the embedded fuel tank, the alternative fuel supply method and the rationalization of the installation form of the modular airborne equipment are mainly adopted. Design and assembly debugging to achieve.

The technical scheme of the present invention is illustrated below in conjunction with specific examples:

1) The overall layout of the small UAV

The small UAV adopts a conventional aerodynamic layout (as shown in Figure 1), a wing-body fusion design, a pull-in power plant, a V-shaped tail and a tricycle landing gear.

Wherein the fuselage (1) is a flat lifting body with a certain airfoil, the upper part is provided with a cabin cover (9), and the inside is a large-capacity cabin for the installation of airborne equipment. Both sides of the fuselage are integrated with the wing (3) through reasonable curves to ensure better aerodynamic characteristics. An engine (10) is installed at the front end of the fuselage, and the engine (10) drives the propeller (11) to provide the pulling force required for flight for the aircraft.

According to one embodiment, the plane shape of the wing (3) is trapezoidal, with its leading edge swept back and its trailing edge swept forward. An aileron (4) is arranged on the outer trailing edge of each wing, and a flap (5) is arranged on the inner trailing edge.

According to one embodiment, the empennage adopts a V-shaped empennage (7). According to a specific embodiment, the left and right empennages of the empennage (7) are mutually about 120°. A control surface (6) is provided on the trailing edge of the empennage, and the functions of the elevator and rudder can be realized through the V-tail mixed control mode.

The connection between the V-shaped tail (7) and the fuselage (1) is realized through the tail brace (8). Tail brace (8) adopts such as the carbon fiber composite material circular tube with taper; According to a specific embodiment, the smaller end of this circular tube diameter is used for installing V-shaped empennage (7), and the larger end of diameter is connected with fuselage (1 ) tail connection.

The front landing gear (12) is located at the front lower part of the fuselage (1), and the main landing gear system (2) is located at the middle and lower part of the fuselage (1).

2) Embedded fuel tank design

According to one embodiment of the present invention, as shown in Figure 2, left front fuel tank (16), left rear fuel tank (15), right front fuel tank (13) and The right rear fuel tank (14) is designed like this without additional resistance, and reserves as much space as possible for the load compartment (17) in the middle of the fuselage, which improves the loading capacity of the aircraft. The profile of the fuel tank is different from the conventional hexahedron shape, but is determined according to the profile of the wing-body fusion body, that is, the left and right front fuel tanks (13), (16) sides are in the shape of an airfoil leading edge, and the left and right rear fuel tanks (14) , (15) the rear portion is in the shape of an airfoil trailing edge, and the inside is hollow to load oil.

3) Alternate oil supply mode

According to one embodiment of the present invention, as shown in Figure 3, the intake pipe (22) is inserted into the left rear fuel tank (15), and the left rear fuel tank (15) is connected with the right front fuel tank (13) through the oil pipe (21), and the right front fuel tank (13) ) is connected to the right rear fuel tank (14) through the fuel pipe (20), the right rear fuel tank (14) is connected to the left front fuel tank (16) through the fuel pipe (19), and the left front fuel tank (16) is connected to the anti-bubble fuel tank (18) through the fuel pipe (23) ), the anti-bubble fuel tank (18) is connected to the engine by the oil pipe (24).

After the fuel tanks are connected as above, the order of engine fuel consumption in flight is to use the fuel in the left rear fuel tank (15) first, then use the fuel in the right front fuel tank (13), and then use the fuel in the right rear fuel tank (14) Fuel, and finally use the fuel in the left front fuel tank (16). In this way, the order of fuel consumption in the whole machine is left rear-right front-right rear-left front, so that every time the fuel of one rear fuel tank is consumed, the fuel of one front fuel tank will be consumed accordingly, so as to avoid the simultaneous consumption of two rear fuel tanks or The two front fuel tanks are consumed at the same time, so as to ensure that the influence of fuel consumption on the center of gravity of the whole machine is within the allowable range.

The main feature of the anti-bubble fuel tank (18) is that the volume of the main fuel tank is relatively small, which can ensure that no matter how the oil level in the main fuel tank (13), (14), (15), (16) changes during the whole flight, The anti-bubble oil tank (18) is full of oil, thereby stably supplying oil to the engine.

4) Modular loading

In order to facilitate the installation and replacement of airborne equipment and reduce the impact on the aircraft structure, a modular loading structure is designed in the middle of the fuselage (as shown in Figure 4).

Bottom plate support plate (32) is designed in fuselage (1) middle part, is designed with screw hole (31) above, and the back side of screw hole is inlaid with anti-catch nut, is used for installing screw to fix bottom plate (42). The front portion of base plate support plate (32) is designed with square hole (33), becomes " mouth " shape, reserves space for installing the airborne equipment such as detection cloud platform.

The airborne equipment (41) is installed on the upper surface of the base plate (42) (as shown in Figure 5), and the four corners of the base plate are designed with screw holes (43).

When installing the airborne equipment, at first the airborne equipment (41) is fixed on the upper surface of the base plate (42), and then the base plate (42) is fixed on the base plate support plate (32) with screws (as shown in Figure 6).

The embodiment of the present invention is described more specifically below by two examples:

Example 1, long-endurance mission flight

The whole machine adopts wing-body fusion and "V"-shaped tail design and pull-in power plant, which has small resistance and high lift. Due to the installation of the embedded fuel tank in the form of alternate fuel supply, after the UAV takes off, the sequence of left rear fuel tank-right front fuel tank-right rear fuel tank-left front fuel tank is used to supply fuel to the engine in turn. During the process of fuel consumption, the whole machine The longitudinal change of the center of gravity is small, and due to the large volume of the fuel tank, a longer flight can be achieved.

Example 2, rapid replacement of airborne equipment in routine tasks

Due to the low cost of the modular design of the airborne equipment base plate, multiple base plates can be manufactured, and various required airborne equipment can be installed on the base plate before the field test. During the field flight test, the bottom plate screws can be removed, and the “airborne equipment-bottom plate” module can be replaced to quickly change the configuration of the drone’s airborne equipment.

Beneficial effect

The advantages of the present invention are:

1) The small UAV adopts the layout type of wing-body fusion, single tail brace, V-shaped tail and pull-in power, which has excellent aerodynamic characteristics, especially the wing-body fusion design increases the lift of the whole aircraft, Reduce wing-body interference resistance;

2) Embedded fuel tank design is adopted to make full use of the internal space of the fuselage to load fuel without adding additional resistance, which not only saves the space in the load compartment, but also increases the fuel load and improves the battery life of the whole machine;

3) Alternate fuel supply is adopted to prevent the two front fuel tanks or the two rear fuel tanks or the two fuel tanks on the same side from being exhausted at the same time during the flight, so as to ensure that the influence of fuel consumption on the longitudinal center of gravity of the whole machine is within the allowable range;

4) Modular loading design facilitates the installation and replacement of airborne equipment and reduces the impact on the body structure.

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 (10)

1. A small unmanned aerial vehicle, characterized in that it comprises: fuselage (1); Wings (3) connected to the fuselage (1); empennage (7); and The tail support (8) is used to realize the connection between the empennage (7) and the fuselage (1). 2. The small unmanned aerial vehicle according to claim 1, further comprising: An engine (10) mounted on the front end of the fuselage (1); The propeller (11) driven by the engine (10) is used to provide the pulling force required for flight for the aircraft. 3. The small UAV according to claim 2, further comprising: a nacelle cover (9) arranged on the upper part of the fuselage (1), which defines a nacelle with the fuselage (1); Wherein the fuselage (1) is a flat lifting body with a certain airfoil. 4. The small unmanned aerial vehicle according to claim 3, characterized in that The wings (3) are fused with both sides of the fuselage through reasonable curves, thereby ensuring better aerodynamic characteristics. The plane shape of the wing (3) is trapezoidal, with its leading edge swept back and its trailing edge swept forward. An aileron (4) is arranged on the outer trailing edge of each wing, and a flap (5) is arranged on the inner trailing edge. 5. The small unmanned aerial vehicle according to claim 1, characterized in that The empennage is a V-shaped empennage (7), the left and right empennages of the V-shaped empennage (7) form about 120° each other, and the rear edge is provided with a control surface (6), so that the functions of the elevator and rudder can be realized through the V-tail mixed control mode . 6. The small unmanned aerial vehicle according to claim 1, characterized in that Described tail support (8) is a round tube, and round tube adopts carbon fiber composite material, and one end with its smaller diameter is used for installing V-shaped empennage (7), and one end with larger diameter is connected with the afterbody of fuselage (1). 7. The small unmanned aerial vehicle according to claim 1, further comprising: the nose landing gear (12) positioned at the front lower part of the fuselage (1), and The main landing gear system (2) located at the lower middle part of the fuselage (1). 8. The small unmanned aerial vehicle according to claim 7, further comprising: The bottom plate supporting plate (32) located in the middle part of the fuselage (1) is used for installing airborne equipment. 9. The small unmanned aerial vehicle according to claim 8, further comprising: The screw holes (31) provided on the base support plate (32), The anti-catch nut embedded in the back side of the screw hole (31) is used to install the screw for fixing the base plate (42). 10. The small unmanned aerial vehicle according to claim 9, further comprising: The hole (33) that is arranged on the front portion of said floor support plate (32) is used for installing airborne equipment, Wherein the four corners of the base plate (42) are provided with screw holes (43), and the upper surface of the base plate (42) can be used for installing airborne equipment (41).

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