CN211253019U - A vertical take-off and landing unmanned transport aircraft - Google Patents

Abstract

A vertical take-off and landing unmanned transport plane belongs to the field of aviation and comprises a plane body, wings, an empennage, landing gears, an engine cabin and a cargo hold; the utility model discloses unmanned transport plane adopts the lift fan to provide lift and auxiliary balance when VTOL, simultaneously through the design to aircraft structure and pneumatic layout, reduces the control degree of difficulty of aircraft, increases the cargo space of aircraft, effectively solves current VTOL unmanned vehicles's the control difficulty and the little problem of loading capacity to realize perpendicular and short distance take off and land, have advantages such as the flexibility of flight is steady, application scope is wide, the loading capacity is big.

Description

A vertical take-off and landing unmanned transport aircraft

technical field

The utility model belongs to the field of aviation, in particular to a vertical take-off and landing unmanned transport aircraft.

Background technique

In recent years, with the rapid development of UAV technology, UAVs have great application value in aerial photography, transportation, inspection, plant protection and other fields. UAVs have now been widely used in various fields of military and civilian use. Among them, vertical take-off and landing As a special kind of UAV, UAV can take off and land at zero speed without opening a special take-off and landing runway. Compared with conventional UAVs, VTOL UAVs have the advantages of flexible take-off and landing methods, convenient launch and recovery, and good maneuverability, and also have the general functions of conventional UAVs. The development of new vertical take-off and landing UAVs has high practical value for winning the initiative in the future battlefield.

At present, there are mainly three kinds of vertical take-off and landing technologies. The first is tilt-rotor, which realizes the conversion of vertical take-off and landing and flight through tilting engine and rotor. However, the hovering and low-speed capabilities and economy of tilt-rotor aircraft are far from The high-grade helicopter has far less ability to fly forward than the high-grade fixed-wing aircraft, but its existence fills the gap between the two and brings new ideas to the aviation industry; the second is a composite layout, which has both rotor and The man-machine can take off and land vertically, hover in the air, and has the excellent cruise function of conventional UAVs. The two are integrated into one UAV, which is convenient and flexible in use. Moreover, technical indicators such as level flight speed, endurance, ceiling, cruise performance, and range are better than those of rotary-wing UAVs, but their carrying capacity is very limited, which is only suitable for small and medium-sized UAVs; the third is tilting. The engine nozzle or with a lift fan to achieve vertical take-off and landing. By tilting the engine nozzle, its thrust is directed from the parallel direction to other directions. In addition to providing vertical take-off and landing or short-range take-off and landing capability, thrust vectoring technology can also be used in air combat. It provides extra maneuvering power for the aircraft, but it has high requirements on the control system, not only the control hardware is numerous, but the control software is also very complex. Therefore, a new vertical take-off and landing aircraft is currently required to effectively solve the above problems.

SUMMARY OF THE INVENTION

In order to solve the above problems, the present utility model provides a vertical take-off and landing unmanned transport aircraft, which adopts a lift fan to provide lift and assist balance during vertical take-off and landing. The cargo space of the large aircraft can effectively solve the problems of control difficulties and small carrying capacity of the existing vertical take-off and landing unmanned aerial vehicles, so as to realize vertical and short-distance take-off and landing. It has the advantages of flexible and stable flight, wide application range and large carrying capacity. , and its specific technical solutions are as follows:

A vertical take-off and landing unmanned transport aircraft, comprising a fuselage 1, a wing 2, a tail 6, a landing gear 8, an engine compartment 10, and a cargo compartment 20, characterized in that the fuselage 1 is provided with wings 2 on both sides, and the fuselage 1 and the wing 2 are a wing body fusion body; the fuselage 1 and the wing 2 are provided with three landing gears 8 below; the rear end of the wing 2 is provided with an aileron 3 and two flaps 4, The tip of the wing 2 is provided with a winglet 5; the tail of the fuselage 1 is provided with a tail 6, the tail 6 is a single vertical tail, and the tail 6 is provided with a rudder 7; the wing 2 is close to the inner side of the fuselage 1 An engine compartment 10 is provided, the front end of the engine compartment 10 is provided with an engine compartment air inlet 9, and the rear end of the engine compartment 10 is provided with an engine compartment air outlet 11; the head of the fuselage 1 is provided with a nose lift fan air duct 13 The nose lift fan air passage 13 is provided with a nose lift fan 12, and the nose lift fan air passage 13 is respectively provided with an upper hatch 14 of the nose lift fan air passage and a lower hatch door 15 of the nose lift fan air passage. The wing 2 is provided with a wing lift fan air duct 17, a wing lift fan 16 is provided in the wing lift fan air duct 17, and the wing lift fan air duct 17 is provided with a wing lift fan air duct up and down respectively. The hatch 18 and the lower hatch 19 of the wing lift fan airway; as shown in Figure 1-4;

The trailing edge of the wing 2 is perpendicular to the longitudinal center axis of the fuselage 1, and the ratio of the wingspan of the wing 2 to the total length of the fuselage 1 is (1.6-1.8):1;

The winglet 5 is a single upper winglet, the height of the winglet 5 is 10% to 15% of the half span, and the inclination angle is 15 to 20 degrees;

The distance from the geometric center of the nose lift fan 12 to the vertex of the nose is 25% to 27% of the total length of the fuselage; the distance from the geometric center of the wing lift fan 16 to the central axis of the fuselage 1 is half the wingspan. 42% to 43%, the distance from the geometric center of the wing lift fan 16 to the trailing edge of the wing 2 is 20% to 22% of the total length of the fuselage 1;

The interior of the fuselage 1 is provided with a cargo hold 20, the top-view contour area of the cargo hold 20 is 15% to 20% of the overall top-down contour area of the aircraft, and the maximum raised height on the upper surface of the cargo hold 20 is 10% to 15% of the total length of the aircraft, and Not less than the maximum raised height on the upper surface of the engine compartment 10;

The vertical take-off and landing unmanned transport aircraft is installed with a total of five engines, three of which are respectively connected with the nose lift fan 12 and the wing lift fan 16 as a whole to provide vertical take-off and landing power; two engines are respectively installed on the wings 2 In the cabin 10, horizontal thrust is provided;

The nose lift fan 12 and the wing lift fan 16 are distributed in an isosceles triangle;

The three landing gears 8 are distributed in an isosceles triangle; the landing gear 8 at the fuselage 1 is arranged in the area between the nose lift fan 12 and the nose vertex; the landing gear 8 at the wing 2 is arranged in the area between the wing lift fan 16, the nacelle 10, the nacelle outlet 11 and the flaps 4;

The above-mentioned control method for a vertical take-off and landing unmanned transport aircraft includes the following stages:

Stage 1, vertical take-off - hovering in the air, or short roll takeoff:

Open the upper and lower doors of the three lift fans at the same time, and the three lift fans are activated at the same time. At this time, the three lift fans simultaneously generate vertical downward thrust. When the total thrust of the lift fans is greater than the total gravity of the aircraft , the aircraft leaves the ground vertically, and gradually decelerates after reaching a certain height, until the thrust of the lift fan is equal to the aircraft's own gravity, achieving vertical take-off - hovering in the air;

When the carrying capacity is large and the total weight of the aircraft is greater than the maximum thrust of the three lift fans, a short-distance roll-off is performed, and the three lift fans and two horizontal thrust engines are started at the same time. After reaching a certain speed, the wing-body fusion aircraft When the aerodynamic lift generated by the body is equal to the aircraft's own gravity, turn off the three lift fans, and at the same time close the upper and lower doors of the three lift fan airways to achieve short-distance roll-off takeoff;

Stage 2, hovering in the air - level flight:

Start the horizontal thrust engine, after reaching a certain speed, when the aerodynamic lift generated by the fuselage of the wing-body fusion body is equal to the aircraft's own gravity, turn off the three lift fans, and close the upper and lower doors of the air passages of the three lift fans at the same time. complete the process from hovering in the air to level flight;

Stage three, level flight:

By controlling the ailerons 3 and flaps 4 on both sides to deflect upwards or downwards at the same time, the pitching or pitching moment of the aircraft is obtained, and the pitching or pitching motion during the plane's level flight is realized; by controlling the ailerons 3 on the left side up or down Downward deflection, while the right aileron 3 is deflected downwards or upwards, the left or right rolling moment of the aircraft is obtained, and the rolling motion of the aircraft during level flight is realized; by controlling the rudder 7 on the tail 6 to the left or right Yaw, get the left or right yaw moment of the aircraft, and realize the yaw motion during the plane flight;

Stage 4, level flight - hovering in the air:

The horizontal thrust engine is gradually turned off, the aircraft is gradually decelerated, the ailerons 3 and flaps 4 on both sides are deflected downward by 90° at the same time, and the upper door 14 of the nose lift fan airway and the lower door 15 of the nose lift fan airway are opened at the same time , start the nose lift fan 12, and control the thrust of the nose lift fan 12 to decelerate the aircraft while keeping the fuselage horizontally stable. The upper door 18 and the lower airway door 19 of the wing lift fan are opened at the same time, the wing lift fan 16 is activated, the ailerons 3 and flaps 4 on both sides are reset at the same time, and the three lift fans are controlled to generate thrust to maintain the fuselage. The level is stable until the speed of the aircraft is zero, and the hovering in the air is realized;

Stage 5, hovering in the air - vertical landing:

By controlling the thrust of the three lift fans to gradually weaken, while maintaining the horizontal stability of the fuselage, the aircraft is gradually lowered to the ground, the upper and lower doors of the three lift fans airway are closed at the same time, and the three lift fans are closed at the same time. achieve vertical landing.

Compared with the prior art, the vertical take-off and landing unmanned transport aircraft of the utility model has the following beneficial effects:

1. Vertical take-off and landing capability: The unmanned transport aircraft of the present utility model can realize stable vertical take-off and landing, reducing the area of the flight site; the present utility model uses three lift fans as the vertical take-off and landing power, compared with the tilt rotor and Tilting the engine nozzle, the control difficulty is relatively low; compared with the composite layout, the carrying capacity of the aircraft is greatly improved; the vertical take-off and landing function of the unmanned transport aircraft of the utility model can allow the aircraft to complete the operation of the aircraft on the deck of warships or complicated ground conditions. Taking off and landing in the environment increases the application range of the aircraft.

2. Advantages of aerodynamic shape: The unmanned transport aircraft of the present utility model is a wing-body fusion aircraft, and the wings and the front part of the fuselage are fused together, which can reduce the self-weight, increase the lift and reduce the drag, and greatly improve the aerodynamic efficiency and structure. In addition, because the fuselage and the wings are connected by a smooth curved surface, there is no obvious bending angle, which eliminates the dihedral reflection effect, effectively reduces the radar wave reflection area, and improves the stealth performance of the aircraft.

3. Although the unmanned transport aircraft of the present utility model carries 5 engines, its cost and weight are relatively large, but it is beneficial to the stability of its vertical take-off and landing gear, and its carrying capacity is large, which can well ensure flight safety during the carrying flight process. .

To sum up, compared with the existing large transport aircraft, the vertical take-off and landing unmanned transport aircraft of the present utility model increases the vertical take-off and landing function, which can allow the aircraft to complete the take-off on the deck of a warship or in an environment with complex ground conditions Compared with tilt-rotor aircraft and tilt-engine nozzle aircraft, the control difficulty is relatively low; compared with composite layout transport aircraft, the carrying capacity of the aircraft is greatly improved .

Description of drawings

Fig. 1 is the structural representation of a kind of vertical take-off and landing unmanned transport aircraft of the present invention;

2 is a top view of a vertical take-off and landing unmanned transport aircraft of the present invention;

3 is a schematic structural diagram of the nose lift fan and the air passage of the nose lift fan of the present invention;

4 is a schematic structural diagram of a wing lift fan of the present utility model and an air passage of the wing lift fan;

In the picture: 1-fuselage, 2-wing, 3-aileron, 4-flaps, 5-winglet, 6-tail, 7-rudder, 8-landing gear, 9-engine compartment air intake , 10-engine compartment, 11-engine compartment air outlet, 12- nose lift fan, 13- nose lift fan air passage, 14- nose lift fan air passage upper hatch, 15- nose lift fan air passage lower cabin Door, 16-wing lift fan, 17-wing lift fan airway, 18-wing lift fan airway upper hatch, 19-wing lift fan airway lower hatch, 20-cargo compartment.

Detailed ways

The present utility model will be further described below in conjunction with specific implementation cases, but the present utility model is not limited to these embodiments.

A vertical take-off and landing unmanned transport aircraft, comprising a fuselage 1, a wing 2, a tail 6, a landing gear 8, an engine compartment 10, and a cargo compartment 20, characterized in that the fuselage 1 is provided with wings 2 on both sides, and the fuselage 1 and the wing 2 are a wing body fusion body; the fuselage 1 and the wing 2 are provided with three landing gears 8 below; the rear end of the wing 2 is provided with an aileron 3 and two flaps 4, The tip of the wing 2 is provided with a winglet 5; the tail of the fuselage 1 is provided with a tail 6, the tail 6 is a single vertical tail, and the tail 6 is provided with a rudder 7; the wing 2 is close to the inner side of the fuselage 1 An engine compartment 10 is provided, the front end of the engine compartment 10 is provided with an engine compartment air inlet 9, and the rear end of the engine compartment 10 is provided with an engine compartment air outlet 11; the head of the fuselage 1 is provided with a nose lift fan air duct 13 The nose lift fan air passage 13 is provided with a nose lift fan 12, and the nose lift fan air passage 13 is respectively provided with an upper hatch 14 of the nose lift fan air passage and a lower hatch door 15 of the nose lift fan air passage. The wing 2 is provided with a wing lift fan air duct 17, a wing lift fan 16 is provided in the wing lift fan air duct 17, and the wing lift fan air duct 17 is provided with a wing lift fan air duct up and down respectively. The hatch 18 and the lower hatch 19 of the wing lift fan airway; as shown in Figure 1-4;

The trailing edge of the wing 2 is perpendicular to the longitudinal center axis of the fuselage 1, and the ratio of the wingspan of the wing 2 to the total length of the fuselage 1 is (1.6-1.8):1;

The winglet 5 is a single upper winglet, the height of the winglet 5 is 10% to 15% of the half span, and the inclination angle is 15 to 20 degrees;

The distance from the geometric center of the nose lift fan 12 to the vertex of the nose is 25% to 27% of the total length of the fuselage; the distance from the geometric center of the wing lift fan 16 to the central axis of the fuselage 1 is half the wingspan. 42% to 43%, the distance from the geometric center of the wing lift fan 16 to the trailing edge of the wing 2 is 20% to 22% of the total length of the fuselage 1;

The interior of the fuselage 1 is provided with a cargo hold 20, the top-view contour area of the cargo hold 20 is 15% to 20% of the overall top-down contour area of the aircraft, and the maximum raised height on the upper surface of the cargo hold 20 is 10% to 15% of the total length of the aircraft, and Not less than the maximum raised height on the upper surface of the engine compartment 10;

The vertical take-off and landing unmanned transport aircraft is installed with a total of five engines, three of which are respectively connected with the nose lift fan 12 and the wing lift fan 16 as a whole to provide vertical take-off and landing power; two engines are respectively installed on the wings 2 In the cabin 10, horizontal thrust is provided;

The nose lift fan 12 and the wing lift fan 16 are distributed in an isosceles triangle;

The three landing gears 8 are distributed in an isosceles triangle; the landing gear 8 at the fuselage 1 is arranged in the area between the nose lift fan 12 and the nose vertex; the landing gear 8 at the wing 2 is arranged in the area between the wing lift fan 16, the nacelle 10, the nacelle outlet 11 and the flaps 4;

In this example, a model machine is produced. The basic parameters are: the length of the fuselage 1 is 4 meters, the height of the fuselage 1 is 1.2 meters, the wingspan of the wing 2 is 7 meters, the area of the wing 2 is 12.4 square meters, and the empty weight of the aircraft is 410 kg. The maximum take-off weight is 1450 kg. The engine adopts the F112 turbofan engine, with a horizontal thrust of 2×3.26 kN and a vertical thrust of 3×3.26 kN.

A control method for a vertical take-off and landing unmanned transport aircraft in this embodiment includes the following stages:

Stage 1, vertical take-off - hovering in the air, or short roll takeoff:

Open the upper and lower doors of the three lift fans at the same time, and the three lift fans are activated at the same time. At this time, the three lift fans simultaneously generate vertical downward thrust. When the total thrust of the lift fans is greater than the total gravity of the aircraft , the aircraft leaves the ground vertically, and gradually decelerates after reaching a certain height, until the thrust of the lift fan is equal to the aircraft's own gravity, achieving vertical take-off - hovering in the air;

When the carrying capacity is large and the total weight of the aircraft is greater than the maximum thrust of the three lift fans, a short-distance roll-off is performed, and the three lift fans and two horizontal thrust engines are started at the same time. After reaching a certain speed, the wing-body fusion aircraft When the aerodynamic lift generated by the body is equal to the aircraft's own gravity, turn off the three lift fans, and at the same time close the upper and lower doors of the three lift fan airways to achieve short-distance roll-off takeoff;

Stage 2, hovering in the air - level flight:

Start the horizontal thrust engine, after reaching a certain speed, when the aerodynamic lift generated by the fuselage of the wing-body fusion body is equal to the aircraft's own gravity, turn off the three lift fans, and close the upper and lower doors of the air passages of the three lift fans at the same time. complete the process from hovering in the air to level flight;

Stage three, level flight:

By controlling the ailerons 3 and flaps 4 on both sides to deflect upwards or downwards at the same time, the pitching or pitching moment of the aircraft is obtained, and the pitching or pitching motion during the plane's level flight is realized; by controlling the ailerons 3 on the left side up or down Downward deflection, while the right aileron 3 is deflected downwards or upwards, the left or right rolling moment of the aircraft is obtained, and the rolling motion of the aircraft during level flight is realized; by controlling the rudder 7 on the tail 6 to the left or right Yaw, get the left or right yaw moment of the aircraft, and realize the yaw motion during the plane flight;

Stage 4, level flight - hovering in the air:

The horizontal thrust engine is gradually turned off, the aircraft is gradually decelerated, the ailerons 3 and flaps 4 on both sides are deflected downward by 90° at the same time, and the upper door 14 of the nose lift fan airway and the lower door 15 of the nose lift fan airway are opened at the same time , start the nose lift fan 12, and control the thrust of the nose lift fan 12 to decelerate the aircraft while keeping the fuselage horizontally stable. The upper door 18 and the lower airway door 19 of the wing lift fan are opened at the same time, the wing lift fan 16 is activated, the ailerons 3 and flaps 4 on both sides are reset at the same time, and the three lift fans are controlled to generate thrust to maintain the fuselage. The level is stable until the speed of the aircraft is zero, and the hovering in the air is realized;

Stage 5, hovering in the air - vertical landing:

By controlling the thrust of the three lift fans to gradually weaken, while maintaining the horizontal stability of the fuselage, the aircraft is gradually lowered to the ground, the upper and lower doors of the three lift fans airway are closed at the same time, and the three lift fans are closed at the same time. achieve vertical landing.

The model aircraft of this embodiment has been flight tested: the maximum speed is Mach 0.65, the vertical take-off and landing payload is 480 kg, the short-distance rolling payload is 940 kg, the practical ceiling is 3500 meters, the maximum range is 1580 km, and the thrust-to-weight ratio is 4.56: 1.

Compared with the X-48B UAV model machine, the model machine of this embodiment has a maximum speed of 264.95% and a maximum range of 624.77%.

Claims (3)

1. a vertical take-off and landing unmanned transport aircraft, comprising a fuselage (1), a wing (2), a tail (6), a landing gear (8), an engine compartment (10), a cargo compartment (20), characterized in that, Wings (2) are provided on both sides of the fuselage (1), and the fuselage (1) and the wings (2) are a wing-body fusion body; A landing gear (8) is provided; a piece of aileron (3) and two flaps (4) are arranged at the rear end of the wing (2), and a winglet (5) is arranged at the tip of the wing (2); The tail part of the fuselage (1) is provided with a tail (6), the tail (6) is a single vertical tail, and the tail (6) is provided with a rudder (7); the wing (2) is close to the fuselage (1) The inner side of the engine compartment (10) is provided with an engine compartment (10), the front end of the engine compartment (10) is provided with an engine compartment air inlet (9), and the rear end of the engine compartment (10) is provided with an engine compartment air outlet (11); The head of (1) is provided with a head lift fan air passage (13), a head lift fan (12) is arranged in the head lift fan air passage (13), and the head lift fan air passage (13) is up and down The upper hatch (14) of the air passage of the nose lift fan and the lower hatch (15) of the air passage of the nose lift fan are respectively provided; A wing lift fan (16) is arranged in the fan air duct (17), and the wing lift fan air duct (17) is respectively provided with an upper hatch (18) of the wing lift fan air duct and a lower cabin of the wing lift fan air duct. door(19); The trailing edge of the wing (2) is perpendicular to the longitudinal center axis of the fuselage (1), and the ratio of the wingspan of the wing (2) to the total length of the fuselage (1) is (1.6-1.8):1; The winglet (5) is a single upper winglet, the height of the winglet (5) is 10% to 15% of the half span, and the inclination angle is 15 to 20 degrees; The distance from the geometric center of the nose lift fan (12) to the nose vertex is 25% to 27% of the total length of the fuselage; the distance from the geometric center of the wing lift fan (16) to the central axis of the fuselage (1) The distance is 42% to 43% of the half span, and the distance from the geometric center of the wing lift fan (16) to the trailing edge of the wing (2) is 20% to 22% of the total length of the fuselage (1); The interior of the fuselage (1) is provided with a cargo compartment (20), the top-view contour area of the cargo compartment (20) is 15% to 20% of the overall top-view contour area of the aircraft, and the maximum raised height on the upper surface of the cargo compartment (20) is the total length of the aircraft 10% to 15% of the upper surface of the engine compartment (10), and not less than the maximum raised height on the upper surface of the engine compartment (10); The vertical take-off and landing unmanned transport aircraft is installed with a total of five engines, three of which are respectively connected with the nose lift fan (12) and the wing lift fan (16) to provide vertical take-off and landing power; two wings are respectively installed In the engine compartment (10) at (2), horizontal thrust is provided. 2 . The vertical take-off and landing unmanned transport aircraft according to claim 1 , wherein the nose lift fans ( 12 ) and the wing lift fans ( 16 ) are distributed in an isosceles triangle. 3 . 3. A kind of vertical take-off and landing unmanned transport aircraft according to claim 1, is characterized in that, described three landing gears (8) are distributed in isosceles triangle; ) is arranged in the area between the nose lift fan (12) and the apex of the nose; the landing gear (8) at the wing (2) is arranged on the wing lift fan (16), the engine compartment (10), the engine The area between the cabin air outlet (11) and the flaps (4).

Images