Flying wing layout miniature unmanned aerial vehicle with tilting duct for vertical take-off and landing

Abstract

The utility model discloses a flying wing layout miniature unmanned aerial vehicle capable of realizing vertical take-off and landing by tilting ducted fans, which can realize vertical take-off and landing and hovering as well as high-speed cruise, and comprises an integrated fuselage and wings, flaps positioned at the inner sections of the wings are used for providing lift force and resistance for runway take-off and landing, and the flaps are used for providing lift force and resistance for runway take-off and landing. The ailerons located on the inner sections of the wings are used for providing rolling torque during flight, the ducts located at the two ends of the wings are used for controlling transverse stability in the vertical take-off and landing and cruising process, the two main ducted fans are longitudinally distributed, and the main ducted fan on the front portion of the fuselage is vertically fixed to provide lift force. The main ducted fan at the rear part of the fuselage tilts by 90 degrees through the tilting mechanism to realize power required by vertical take-off and landing and cruising, and the wing body fusion technology of the flying wing layout has good aerodynamic characteristics and reasonable mass distribution.

Description

Technical Field

[0001] The utility model belongs to the field of fixed-wing aircraft design, and is a tilt-ducted vertical take-off and landing flying-wing layout micro-UAV, specifically relates to a tilt-ducted vertical take-off and landing, micro-fixed-wing, flying-wing layout UAV. Background Art

[0002] Drones are miniaturized, intelligent, and low-cost. They have become the core combat weapon platform in the current modern, information-based, and intelligent warfare. The types of missions they perform have also evolved from aerial reconnaissance and battlefield surveillance to suppressing enemy air defense systems, implementing rapid ground strikes, and missile defense, gradually transforming from auxiliary combat means to main combat means.

[0003] Micro UAVs have always been an important research direction. They are light in weight, easy to transport and have certain maneuverability. They are mainly used for close-range reconnaissance, electromagnetic interference, battlefield detection, target attack, etc. In view of the above background, a tilt-rotating vertical take-off and landing micro fixed-wing UAV is needed.

[0004] Due to the limited area of ​​the aircraft carrier deck, vertical take-off and landing technology came into being. Compared with the instability of the tilt-rotor aircraft, the tilt-duct makes the transmission mechanism simpler and has better stability.

[0005] In civilian use, it can solve the problem of short range and small payload of general aviation helicopters and high requirements for take-off and landing sites of fixed-wing aircraft. In military use, when there is no available landing runway and insufficient area of ​​aircraft carrier deck, resources can be quickly mobilized to solve the above dilemma. Utility Model Content

[0006] In view of the above problems, the utility model designs a micro UAV with a tilting duct vertical take-off and landing flying wing layout. The UAV can get rid of the dependence of traditional aircraft on the runway for take-off and landing. It can switch between short take-off and vertical take-off and landing modes, and has good maneuverability, so that the aircraft has higher survivability.

[0007] The plane layout of the utility model is a wing-body fusion tailless flying wing layout, a small aspect ratio large swept wing, a lifting body fuselage and a segmented wing, which make the aircraft have good aerodynamic characteristics, and the wing is provided with four control surfaces to make the aircraft have better maneuverability.

[0008] In order to have the ability of vertical take-off and landing, main duct fans are installed at the front and rear of the fuselage. The main duct fan at the rear of the fuselage is fixed on the tilt mechanism. The main duct fans at the front and rear of the fuselage are far away from the center of gravity to provide better controllability. An auxiliary duct is installed inside each outer wing on both sides. The duct speed is controlled by the flight controller and the tilt mechanism tilts the main duct to cooperate with the other three ducts to achieve vertical take-off and landing.

[0009] The aircraft has three flight modes, namely vertical take-off and landing and hovering mode, short take-off mode and high-speed flight mode. Three channels are set for these three modes. The three channels respectively control the tilt angle of the tilt mechanism. The aircraft obtains or weakens the forward thrust vector, so that the aircraft can switch between vertical take-off and landing, short take-off and high-speed flight. The aircraft is powered by lithium batteries, and the batteries are installed in the wings.

[0010] During vertical takeoff and landing, the main ducted fans at the front and rear of the fuselage provide vertical upward lift, and the auxiliary ducted fans on the outer wings actively jet to provide symmetrical rolling torque on both sides of the aircraft to maintain the aircraft's attitude.

[0011] During level flight, roll control is achieved through the active jet of the auxiliary duct fan and the ailerons. The main duct fans at the front and rear of the fuselage provide pitch control. An air intake duct is set in the fuselage to increase the air intake volume of the main duct fan at the rear of the fuselage.

[0012] During a short takeoff, the main ducted fan at the front of the fuselage provides vertical upward thrust, and the main ducted fan at the rear of the fuselage is angled with the axis of the aircraft, providing vertical upward and horizontal forward thrust. The aircraft glides forward, providing a certain speed to generate lift. When the sum of the lift provided by the four ducted fans and the lift generated by the aircraft is greater than the gravity of the aircraft, it takes off.

[0013] When the tilt mechanism is working, the servo drives the gear set to drive the fixed frame to tilt the rear main duct fan, thereby realizing vector thrust tilt.

[0014] The flight controller senses the aircraft's attitude through a gyroscope and adjusts the speed of each ducted fan, so that the ducted fans and ailerons can be jointly controlled in the air to achieve stability of the aircraft's attitude, and can also be used for roll control during level flight.

[0015] The three-point landing gear is used to provide the support required for the aircraft to take off and land. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the overall appearance of an aircraft according to an embodiment of the utility model.

[0017] Figure 2 It is a schematic diagram of the aircraft plan layout according to an embodiment of the utility model.

[0018] Figure 3 It is a schematic diagram of an aircraft tilting mechanism according to an embodiment of the utility model.

[0019] Figure 4 It is a schematic diagram of the structure of an aircraft from a belly perspective according to an embodiment of the utility model.

[0020] In the figure: 1-fuselage; 2-main wing; 3-outer wing; 4-tilt mechanism; 5-flaps; 6-ailerons; 7-main ducted fan; 8-flight controller; 9-auxiliary ducted fan; 10-ducted fan fixing frame; 11-large gear; 12-small gear; 13-frame; 14-servo; 15-rear landing gear; 16-front landing gear; DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model. In the absence of conflict, the embodiments in the utility model and the features in the embodiments can be combined with each other.

[0022] Figure 1 The tilt-ducted vertical take-off and landing flying wing micro-UAV shown in an embodiment of the utility model includes an integrated fuselage 1 and a main wing 2, and has good aerodynamic characteristics. The aileron 6 and the auxiliary ducted fan 9 are both located on the outer wing 3 for roll control during flight. The flap 5 is located behind the main wing 2. The main ducted fan 7 is located at the front and rear of the fuselage 1, respectively. The tilt mechanism is fixed at the connection between the fuselage 1 and the main wing 2, and the main ducted fan 7 at the rear of the fuselage is fixed to the tilt mechanism 4. During high-speed flight, the tilt mechanism 4 makes the main ducted fan 7 at the rear of the fuselage 180 degrees with the axis of the aircraft to provide forward thrust, and the main ducted fan 7 at the front of the fuselage generates a pitch moment to provide pitch control. During vertical takeoff and landing, the tilt mechanism 4 makes the main ducted fan 7 at the rear of the fuselage form a 90-degree angle with the aircraft axis to provide vertical upward thrust, and the flight controller 8 adjusts the rotation speed of the main ducted fan 7 at the rear of the fuselage and the secondary ducts 9 on both sides of the aircraft so that the pitch moment and the rolling moment of the aircraft are in a balanced state, and the total thrust generated is greater than the aircraft gravity, thereby achieving vertical takeoff and landing. During short-distance takeoff, the tilt mechanism 4 makes the main ducted fan 7 at the rear of the fuselage form an acute angle with the aircraft axis, generating thrust in the horizontal direction and thrust in the vertical direction, so that the aircraft obtains a certain acceleration and rapid taxiing, generates a horizontal speed, and the wing-body fusion generates lift. When the taxiing speed reaches a certain value, the sum of the lift generated by the wing-body fusion, the thrust generated by the main ducted fan 7 and the secondary ducted fan 9 is greater than the weight of the aircraft, and the aircraft leaves the ground.

[0023] Figure 2The aircraft tilt mechanism according to an embodiment of the utility model shown in the figure is composed of a frame 13, a steering gear 14, a large gear 11, a small gear 12 and a ducted fan fixing frame 10. The gear set adopts an asymptotic gear, the ratio of the number of teeth of the large gear 11 and the small gear 12 is 2:1, the steering gear 14 is fixed on the frame 13, the large gear 11 is arranged on the frame, the small gear 12 is connected to the steering gear 14, and the ducted fan fixing frame 10 is fixed on the large gear 11. The small gear 12 is rotated by the steering gear 14, so that the large gear 11 rotates and drives the ducted fan fixing frame 10 to tilt, thereby realizing the change of the direction of the thrust vector.

[0024] Figure 3 The schematic diagram of the structure of the aircraft from the belly perspective according to an embodiment of the utility model is shown. The front three-point landing gear is composed of a front landing gear 16 and two rear landing gears 15. The stability of the aircraft on the ground is good, and it is not easy to deflect and invert during taxiing. When landing on the runway, only the two rear landing gears 15 are used to touch the ground, which is relatively easy to operate.

[0025] The advantages and beneficial effects of the utility model include:

[0026] The flying wing layout combined with the wing-body fusion design has good aerodynamic characteristics. Thanks to the wing-body fusion design, the aircraft can increase its internal space and the weight distribution is more evenly and reasonably. The tailless characteristics of the flying wing layout greatly reduce the resistance during flight, which is conducive to carrying more loads and increasing the range.

[0027] The power system is embedded inside the aircraft, which greatly reduces the external drag and interference to the aerodynamic shape during flight, and has a certain stealth effect.

[0028] The tilt-ducted vertical take-off and landing solution enables the aircraft to face more complex working environments, and the large swept wing and small aspect ratio design of the utility model makes the aircraft extremely maneuverable.

[0029] The simple tilting mechanism greatly reduces the manufacturing cost and improves the reliability to a certain extent.

Claims

1. A tilt-ducted vertical take-off and landing flying-wing micro-UAV. Features include: The fuselage, main wing and outer wing of the wing-body fusion, the flaps at the rear of the main wing are used for pitch control in level flight, the ailerons at the rear of the outer wing are used for roll control in level flight, the main ducted fans at the front and rear of the fuselage are used for pitch control during vertical take-off and landing, the auxiliary ducts on both sides of the outer wing are used for roll balancing during vertical take-off and landing, the landing gear at the belly of the fuselage is used to keep the aircraft stable when preparing for take-off and landing, the flight controller inside the fuselage is used to control the speed of the ducted fan, and the tilt mechanism is located at the connection between the fuselage and the main wing, wherein the main ducted fan at the rear of the fuselage Thrust vector tilt is achieved through a tilt mechanism. During level flight, the main ducted fan at the rear of the fuselage is horizontal, providing forward thrust. During vertical takeoff and landing, the main ducted fan at the front of the fuselage and the main ducted fan at the rear generate vertical upward thrust perpendicular to the ground and control the pitch. The auxiliary ducted fans on both sides balance the roll. When the total thrust of the four ducted fans is greater than gravity, vertical takeoff and landing is achieved. During short-distance takeoff, the main ducted fan at the rear of the fuselage forms an acute angle with the axis of the aircraft, generating horizontal forward and vertical upward thrust vectors. The flight controller controls the thrust size, and the aircraft accelerates to glide and generate lift. When the total force is greater than gravity, the aircraft takes off.

2. The tilt-ducted vertical take-off and landing flying-wing micro-UAV according to claim 1, Features Further: The aircraft has no vertical tail and only relies on the active jets of the auxiliary ducts on both sides to achieve heading stability.

3. The tilt-ducted vertical take-off and landing flying-wing micro-UAV according to claim 1, Features Further: the main duct fan at the front of the fuselage is vertically arranged in the fuselage, the main duct fan at the rear of the fuselage is fixed on the tilting mechanism, and the two main ducts are located on the axis of the fuselage. The tilting mechanism drives the small gear to transmit the large gear through the servo to tilt the main duct fan at the rear of the fuselage.

4. The tilt-ducted vertical take-off and landing flying-wing micro-UAV according to claim 1, Features Further: the aircraft is powered by lithium batteries, which are arranged inside the wings.

5. The tilt-ducted vertical take-off and landing flying-wing micro-UAV according to claim 1, It is further characterized by: The aircraft achieves steering through the combined control of ailerons and auxiliary ducts on both sides of the wings.

6. The tilt-ducted vertical take-off and landing flying-wing micro-UAV according to claim 1, Features Further: an air intake passage is provided in the fuselage to increase the air intake volume of the main duct fan at the rear of the fuselage.

7. The tilt-ducted vertical take-off and landing flying-wing micro-UAV according to claim 1, Features Further: The aircraft uses a front three-point landing gear to provide the support required for takeoff and landing.

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