CN106586001A - Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration - Google Patents

Abstract

The present invention relates to the technical field of unmanned aerial vehicles, in particular to a drone with multiple working modes such as vertical take-off and landing/short take-off and landing/conventional take-off and landing/low-speed forward flight/high-speed forward flight, which can realize shore-based/ship-based multiple The unmanned aerial vehicle with a tailed flying wing layout based on deployment includes a lift body with an airfoil shape in longitudinal section, a main wing, an upper wing, and an end wing arranged on both sides of the fuselage that are smoothly integrated with the fuselage. Ducted propeller propulsion device and vertical tail at the tail. The lower end of the vertical tail is fixedly connected with the duct structure of the ducted propeller propulsion device arranged at the tail of the fuselage. The present invention adopts the tailed flying wing aerodynamic layout integrated with the connecting wing. While the unmanned aerial vehicle has many advantages such as excellent aerodynamic characteristics and high effective loading coefficient of the conventional flying wing layout, it effectively overcomes the stability of the conventional flying wing layout. and inherent flaws in maneuverability.

Description

Multi-mode multi-base unmanned aerial vehicle with tail flying wing layout

technical field

The invention relates to the technical field of unmanned aerial vehicles, belongs to the technical field of design of fixed-wing aircraft in aviation aircraft, and specifically relates to a multi-function aircraft with vertical take-off and landing/short-distance take-off and landing/conventional take-off and landing/low-speed forward flight/high-speed forward flight, etc. Modal, it can realize shore-based/ship-based multi-base deployment, and integrates a flying-wing unmanned aerial vehicle in the form of aerodynamic layout of joint wings.

Background technique

At present, the aircraft with VTOL/STOL functions and capable of shore-based/ship-based multi-base deployment can be mainly divided into helicopters, VTOL aircraft using jet engine thrust steering, tilt-rotor/propeller powered VTOL aircraft, etc. Several types of landing aircraft.

Among them, helicopters have been widely used in military and civilian fields due to their excellent flight qualities such as vertical take-off and landing, hovering, and sideways flight without the need for a ground runway. However, when the helicopter flies forward at high speed, there are problems such as the shock loss of the forward blade and the stall of the backward blade, so it is difficult to increase the flight speed. In addition, the helicopter's rotor lift needs to balance gravity during flight, which also makes the helicopter always work at high power throughout the flight, resulting in the disadvantages of limited range and short battery life of the helicopter.

The aircraft using jet engine thrust steering to achieve vertical take-off and landing involves the key technology of thrust vectoring technology, which requires the engine exhaust nozzle to have a larger vector deflection angle than the conventional vectoring nozzle, and the nozzle deflection The angle can be continuously adjusted and simultaneously meet various combat technical indicators such as short take-off and landing, vertical take-off and landing, pitch and yaw control during cruise, and superior cruise performance. It is difficult to develop and expensive to manufacture.

Tilting rotor/propeller powered vertical take-off and landing aircraft realizes the adjustment of the flight state through the tilting of propellers such as rotors/propellers. This type of aircraft not only has various technical difficulties of fixed-wing aircraft and helicopters, but also has unique technical problems of tilt-rotor aircraft. Its structure, aerodynamic force and control technology are much more complicated than ordinary fixed-wing aircraft or helicopters. Its research and development involves the research of many key technologies, which is difficult and risky.

As mentioned above, there are only two types of aircraft with vertical take-off and landing functions and high-speed cruising capabilities that have been put into practical use at present: vertical take-off and landing aircraft that use jet engine thrust steering and tilt-rotor/propeller powered vertical take-off and landing aircraft, but Its research and development costs are relatively high, and research and development is extremely difficult.

Contents of the invention

The purpose of the present invention is to provide an unmanned aerial vehicle which has not only the vertical take-off and landing capability similar to that of a helicopter, but also the high-speed cruising capability of a fixed-wing aircraft. Steering is erratic and difficult to steer.

To achieve the above object, the present invention provides the following technical solutions:

A multi-mode multi-base unmanned aerial vehicle with a tail flying wing layout, comprising:

The longitudinal section is an airfoil (the airfoil refers to the longitudinal cross-sectional shape of a classic fixed-wing aircraft wing), a lift body, and the main wing, upper wing, and end wing arranged on both sides of the fuselage are smoothly integrated with the fuselage. , a ducted propeller propulsion device and a vertical tail arranged at the tail of the fuselage. The main wings arranged on both sides of the fuselage are provided with end wings at the wing points, and the upper ends of the two end wings are respectively connected with the vertical tail arranged at the tail of the fuselage through the upper wing arranged above the fuselage. The lower end of the tail is fixedly connected with the duct structure of the ducted propeller propulsion device arranged at the tail of the fuselage.

Further, the rear ends of the two upper wings are provided with elevators for pitch control in level flight;

Further, the rear end of the vertical tail is provided with a rudder for heading control in level flight.

Further, ducted fans are arranged on both sides of the fuselage and in front of the center of gravity, and the directions of rotation of the ducted fans on both sides are opposite; the two ducted fans are arranged along a transverse axis (referring to a horizontal axis perpendicular to the front and rear direction of the fuselage) swing setting.

Further, the two ducted fans are respectively fixedly connected to both ends of the horizontal shaft installed in the fuselage; the servo motor installed in the fuselage drives the worm device, and the worm device meshes with the worm gear device on the horizontal shaft, and through the servo motor The actuation and the transmission of the worm gear device realize the 360° omnidirectional rotation of the ducted fan system in the horizontal axis plane.

Furthermore, the ducted fans on both sides of the fuselage are respectively driven by two DC motors that turn in opposite directions, and the voltage applied to the busbar of the DC motor is controlled by the ESC to adjust the fan speed and pulling force; the servo motor and the DC motor All are powered by onboard energy storage devices.

Further, the tail of the fuselage is provided with a small turbojet engine installed vertically.

Furthermore, the main shaft of the turbojet engine drives the rotor input shaft of the high-speed permanent magnet generator through the transmission of the clutch, the driving bevel gear and the driven bevel gear. Onboard energy storage device charging.

Further, the heavy oil piston power plant installed horizontally inside the fuselage is used to drive the ducted propeller device at the rear of the fuselage; the small turbojet engine and the heavy oil piston power plant use the same fuel.

Technical effect of the present invention is:

a. The aerodynamic layout with a tailed flying wing integrated with a connecting wing is adopted. While the unmanned aerial vehicle has many advantages such as excellent aerodynamic characteristics and high effective loading coefficient of the conventional flying wing layout, it effectively overcomes the stability of the conventional flying wing layout. and inherent flaws in maneuverability.

b. The unmanned aerial vehicle adopts an aerodynamic shape design based on the composite lift mechanism of a tailed flying wing embedded in a ducted fan, and assists in using the jet thrust of a small turbojet engine to achieve longitudinal attitude control in a vertical take-off and landing state. In the state of level flight, the output shaft power of the turbojet engine drives the high-speed power generation device, and the generated electric energy is stored in the onboard energy storage device, and can be used for onboard equipment, ducted fans and task loads, realizing the energy power of the aircraft platform High-efficiency integrated layout of the system.

c. Unmanned aerial vehicles can not only use the longitudinal force provided by ducted fans and turbojet engines to achieve vertical take-off and vertical landing, but also use the differential pressure lift provided by wings and fuselages to obtain higher flight speeds and The power propulsion efficiency makes the unmanned aerial vehicle integrate the performance of vertical take-off and landing and high-speed cruise.

d. The ducted fans on both sides of the fuselage can realize 360° omnidirectional rotation in the horizontal axis plane, and the pulling force generated by it can be used as the lifting force in the vertical take-off and landing stage, the pull-in force in the level flight stage, or in other flight states The auxiliary control force greatly improves the maneuverability and maneuverability of the unmanned aerial vehicle.

e. The ducted propeller driven by the heavy oil piston power unit is used as the main propeller in the low-speed forward flight state, and can be combined with the ducted fan rotating to the horizontal position to realize the high-speed forward flight of the UAV. The combination of two-stage propellers enables the unmanned aerial vehicle to have conventional take-off and landing capabilities, and can also change the forward flight speed according to the needs of the flight mission, realizing the multi-modal use of unmanned aerial vehicles and the multi-modality of shore-based/ship-based base deployment.

Description of drawings

Fig. 1 is a perspective view of an unmanned aerial vehicle provided by an embodiment of the present invention;

Fig. 2 is a schematic side view of the overall layout of the unmanned aerial vehicle provided by the embodiment of the present invention;

Fig. 3 is a schematic top view of the overall layout of the unmanned aerial vehicle provided by the embodiment of the present invention;

Fig. 4 is a schematic diagram of the arrangement of part of the energy power system of the ducted fan of the unmanned aerial vehicle provided by the embodiment of the present invention;

Fig. 5 is a definition diagram of the rotation position of the ducted fan provided by the embodiment of the present invention;

Fig. 6 is a schematic diagram of the energy power system layout of the unmanned aerial vehicle turbojet engine and the piston power plant part provided by the embodiment of the present invention, and this figure is a longitudinal sectional view of the fuselage;

7 is a three-view diagram of the vertical take-off and landing working mode of the unmanned aerial vehicle provided by the embodiment of the present invention;

Fig. 8 is a three-view view of the short take-off and landing working mode of the unmanned aerial vehicle provided by the embodiment of the present invention;

Fig. 9 is a three-view diagram of the conventional take-off and landing working mode of the unmanned aerial vehicle provided by the embodiment of the present invention;

Fig. 10 is a three-view view of the low-speed forward flight working mode of the unmanned aerial vehicle provided by the embodiment of the present invention;

Fig. 11 is a three-view diagram of the high-speed forward flight working mode of the unmanned aerial vehicle provided by the embodiment of the present invention.

detailed description

The present invention will be described in detail below in conjunction with the accompanying drawings.

Example 1

As shown in Figures 1, 2, and 3, a multi-mode, multi-base unmanned aerial vehicle with a tail flying wing layout includes: a lift body 1 with a longitudinal section in the shape of an airfoil plane, arranged on both sides of the fuselage 1 The wing-body fusion type main wing 2, upper wing 3, end wing 4, the ducted propeller propulsion device 5, the vertical tail 6 that are arranged on fuselage 1 afterbody. The main wing 2 arranged on both sides of the fuselage 1 is provided with an end wing 4 at the tip of the wing, and the upper parts of the two end wings 4 pass through the upper wing 3 arranged above the fuselage 1 and the rear wing arranged at the tail of the fuselage 1 respectively. The vertical tail 6 is connected, and the lower end of the vertical tail 6 is fixedly connected with the duct structure of the ducted propeller propulsion device 5 arranged at the fuselage 1 tail.

The unmanned aerial vehicle provided by the present invention adopts the aerodynamic layout with a tailed flying wing integrated with the connecting wing, and the design scheme of the lifting body 1, while greatly reducing the aerodynamic resistance, it can also generate a certain pressure when flying forward. The differential lift effectively improves the lift-drag characteristics of the whole machine. Through the aerodynamic design scheme of the connecting wing formed by the combination of the main wing 2, upper wing 3, end wing 4 and vertical tail 6, the aircraft effectively solves this problem while inheriting the inherent good cruise characteristics of the conventional flying wing aerodynamic layout. This type of aircraft is unstable in horizontal direction and difficult to control, and has good maneuverability and stability.

Example 2

According to an embodiment of the present invention, the multi-mode, multi-base and tailed flying-wing unmanned aerial vehicle provides a high-efficiency integrated energy power system design solution, as shown in FIG. 3 . Its features include:

The unmanned aerial vehicle adopts a layout form in which ducted fans 9 are arranged on both sides of the front of the fuselage 1 and before the center of gravity, so as to generate direct lifting force during the vertical take-off and landing phase. As shown in FIG. 4 , the ducted fans 9 on both sides of the fuselage 1 rotate in opposite directions, and are fixedly connected to both ends of the horizontal shaft 13 installed in the fuselage 1 . The ducted fan 9 is driven by two DC motors 15 turning in opposite directions and generates pulling force. The servo motor 12 installed in the fuselage 1 drives the worm gear 11 and meshes with the worm gear 14 on the horizontal shaft 13 . Both the servo motor 12 and the DC motor 15 driving the ducted fan 9 are supplied with electrical energy by an on-board energy storage device 17 built into the fuselage 1 . Through the actuation of the servo motor 12 and the transmission of the worm gear device, the 360° omnidirectional rotation of the ducted fan 9 in the horizontal axis plane can be realized and the locking at any position can be realized. The rotational position of the ducted fan is defined as shown in the figure 5.

As shown in Figure 6, after the center of gravity of the unmanned aerial vehicle, a small-sized turbojet engine 10 is vertically arranged on the axis of the fuselage 1, and when the clutch 20 is released, the turbojet engine 10 is mainly used to generate jet thrust, The high-temperature and high-pressure gas expands in the exhaust nozzle 18 and produces a vertical upward thrust, that is, a lift force. In addition to completing the lift of the aircraft with the fan pull, the jet thrust can also be used to provide vertical pitch attitude control during the vertical take-off and landing phase. Required operating torque: Under the state of clutch 20 tightening, the main shaft 19 of turbojet engine drives the rotor input shaft of high-speed permanent magnet generator 23 through the transmission of driving bevel gear 21 and driven bevel gear 22. At this time, most of the remaining power of the turbojet engine 10 is used to drive the high-speed generator 23 and generate high-frequency alternating current, which is charged to the onboard energy storage device 17 after being converted by the electric energy conversion device 24; Road propeller propulsion device 5, and propeller is driven by the heavy oil piston type power unit 25 that is built in fuselage 1, horizontal installation. Small turbojet engine 10 and heavy oil piston type power unit 25 adopt same kind of fuel.

Example 3

According to an embodiment of the present invention, the system state of the multi-mode multi-base unmanned aerial vehicle with tailed flying wing layout in the vertical take-off and landing mode is shown in FIG. 7 . Under the vertical take-off and landing working mode, the heavy oil piston type power unit 25 at the rear of the fuselage 1 remains in a "quiet" state. The ducted fan 9 on both sides of the fuselage 1 rotates to a vertical position as shown in Figure 4, rotates at a high speed and produces an upward lifting force; the clutch 20 at the output end of the turbojet main shaft 19 is released, and the high-temperature and high-pressure gas is exhausted. The nozzle 18 expands and produces a vertical upward thrust, that is, a lifting force, and together with the ducted fan 9, a sufficient lifting force is generated to realize vertical take-off and landing under direct force control in the vertical direction. In addition, the jet thrust produced by the turbojet engine 10 can also be used to provide the maneuvering moment required for vertical pitch attitude control during the vertical take-off and landing phase.

According to an embodiment of the present invention, a multi-mode multi-base unmanned aerial vehicle with a tail flying wing layout, the system state in the short take-off and landing working mode is shown in FIG. 8 . Under STOL working mode, the clutch 20 of turbojet engine main shaft 19 output ends is loosened, and turbojet engine 10 sprays air downwards to produce vertically upward lifting force; The ducted fan 9 on fuselage 1 both sides rotates to In the middle position shown in Figure 5, the vertical component of the fan pulling force is used to provide the lifting force required for short take-off and landing, and the horizontal component is used to provide the pulling force along the axis of the fuselage 1; the fuselage 1. The heavy oil piston power unit 25 at the rear drives the ducted propeller propulsion unit 5 to rotate at a high speed to generate propulsion along the axial direction of the fuselage 1. After possessing a certain forward speed, the vertical jet thrust produced by the turbojet engine 10, the lift component provided by the ducted fan 9 and the pressure differential lift produced by the fuselage 1, the wing 2 and the upper wing 3 Under the action, the short take-off and landing process of the unmanned aerial vehicle is completed.

According to an embodiment of the present invention, the system status of the multi-mode multi-base unmanned aerial vehicle with tailed flying wing layout under the normal take-off working mode is shown in FIG. 9 . Under normal take-off working mode, the ducted fan 9 on both sides of the fuselage 1 rotates to the vertical position as shown in Figure 5, and maintains a "quiet" state together with the turbojet engine 10, and the heavy fuel oil at the rear of the fuselage 1 The piston type power unit 25 drives the ducted propeller unit 5 to rotate at a high speed to generate propulsion along the axis of the fuselage 1 . After having a certain forward speed, the unmanned aerial vehicle completes the take-off process under the action of the differential pressure lift generated by the wing 2 , the upper wing 3 and the fuselage 1 . The system state under the conventional landing mode is the same as the conventional take-off mode, and the turbojet engine 10 and the ducted fan 9 can be started as required during the landing process to assist the landing.

According to an embodiment of the present invention, the multi-mode multi-base unmanned aerial vehicle with tail flying wing layout, after completing vertical take-off/short-distance take-off and having a certain height above the ground, first passes through the heavy oil piston type power at the rear of the fuselage 1. Device 25 provides propulsion, makes aircraft possess certain flying speed; Then ducted fan 9 is rotated to the vertical position as shown in Figure 5 and closed in good time; Then clutch 20 is tightened up, most of turbojet engine 10 The remaining power is used to drive the high-speed generator 23 and generate high-frequency alternating current, which is converted by the electric energy conversion device 24 to charge the onboard energy storage device 17 . The above-mentioned system mode conversion will bring a large loss of lift, which will directly cause the flying height of the unmanned aerial vehicle to drop and enter the dive state; with the increase of airspeed, the elevator 7 at the rear end of the upper wing 3 will be used to move the unmanned aerial vehicle. After recovering from the dive attitude, the UAV turns into level flight and enters the low-speed forward flight working mode. The state of the system in the low-speed forward flight working mode is shown in FIG.

According to an embodiment of the present invention, a multi-mode multi-base unmanned aerial vehicle with a tail flying wing layout, the system state in the high-speed forward flight working mode is shown in FIG. 11 . In the high-speed forward flight mode, the ducted fans 9 on both sides of the fuselage 1 rotate to the horizontal position as shown in Figure 5 and are turned on in due course. Provides power for forward flight.

In the low-speed forward flight/high-speed forward flight working mode of the unmanned aerial vehicle, the elevator 7 at the rear end of the upper wing 3 and the rudder 8 at the rear end of the vertical tail 6 complete the pitch and yaw attitude control respectively.

When completing the cruising task and about to turn over to vertical landing/short-distance landing, the unmanned aerial vehicle should first enter the low-speed forward flight mode, and then reduce the forward flight mode by adjusting the throttle of the heavy oil piston type power unit 25 at the rear of the fuselage 1. Speed, and timely start the ducted fan 9 on both sides of the fuselage 1 and the turbojet engine 10 at the rear of the fuselage 1, then further reduce the output power of the heavy oil piston power unit 25 until it stops, and complete the gravity of the unmanned aircraft system by the pressure difference. The lift balance is transferred to the load where the gravity of the system is balanced by the fan pull and the jet thrust, and then the vertical landing/short-distance landing of the UAV is realized.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present invention should be included in the protection of the present invention. within range.

Claims (9)

1. A kind of multi-mode multi-base has tail flying wing layout unmanned aerial vehicle, it is characterized in that comprising: The longitudinal section is an airfoil-shaped lifting body (1), and the main wing (2), upper wing (3) and end wing (4) arranged on both sides of the fuselage (1) are smoothly integrated with the fuselage. The ducted propeller propulsion device (5) and the vertical tail (6) at the fuselage (1) tail; the main wing (2) that is arranged on both sides of the fuselage (1) is provided with an end wing (4) at the wing point, so The upper ends of the two end wings (4) are respectively connected with the vertical tail (6) arranged on the tail of the fuselage (1) through the upper wing (3) arranged on the fuselage (1), and the vertical tail (6) The lower end of the lower end is fixedly connected with the duct structure of the ducted propeller propulsion device (5) arranged at the tail of the fuselage (1). 2. multimode multibase according to claim 1 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: the rear end of described two upper wings (3) is all provided with elevator (7), is used for level flight time pitch control. 3. multi-mode multi-base according to claim 1 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: described vertical tail (6) rear end is provided with rudder (8), is used for the direction control when level flight . 4. multi-mode multi-base according to claim 1 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: both sides of described fuselage (1), all are provided with ducted fan (9) before center of gravity, two The rotation directions of the side ducted fans are opposite; the two ducted fans (9) are arranged to swing along a transverse axis. 5. multi-mode multi-base according to claim 4 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: two ducted fans (9) are respectively fixedly connected in the horizontal axis (13 that is built in fuselage (1) installation ) both ends; the servo motor (12) installed in the fuselage (1) drives the worm gear (11), and the worm gear (11) meshes with the worm gear (14) on the horizontal shaft (13), and the servo motor ( 12) and the transmission of the worm and gear device realize the 360° omnidirectional rotation of the ducted fan (9) system in the transverse axis plane. 6. multi-mode multi-base according to claim 4 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: the ducted fan (9) of fuselage (1) both sides is by turning to opposite two DC motors (15 ) are driven respectively, and the voltage applied to the busbar of the DC motor (15) is controlled by the electric regulator (16) to realize the adjustment of the fan speed and pulling force; the servo motor (12) and the DC motor (15) are powered by the onboard energy storage The device (17) supplies electrical energy. 7. multimode multibase according to claim 1 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: fuselage (1) afterbody is provided with the small turbojet engine (10) that vertical direction is installed. 8. multimode multibase according to claim 7 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: turbojet engine main shaft (19) passes through clutch (20), driving bevel gear (21) and driven bevel gear The transmission of (22) drives the rotor input shaft of the high-speed permanent magnet generator (23), and the generated high-frequency alternating current is transformed into the direct current of the corresponding system by the electric energy conversion device (24), and charged to the onboard energy storage device (17) . 9. multimode multibase according to claim 1 has tail flying wing layout unmanned aerial vehicle, it is characterized in that: the heavy oil piston type power unit (25) that is horizontally installed in fuselage (1) inside, is used to drive fuselage (1) ducted propeller device (5) at tail; small turbojet engine (10) and heavy oil piston type power plant (25) adopt same kind of fuel.