CN110667837A - A new type of vector thrust dislocation biplane tailstock vertical take-off and landing UAV - Google Patents

Abstract

The invention discloses a novel vector thrust dislocation double-wing tailstock vertical take-off and landing unmanned aerial vehicle. This UAV has two wings that are dislocated up and down. The upper and lower wing support plates support the wings, and the tail rudder surface is arranged at the tail of the support plates. The middle fuselage is connected by two carbon fiber tubes with the upper and lower wing struts on its left and right. The twin-engine vectored powertrain is anchored to the front carbon fiber tubes. Under the condition of effectively controlling the floor space and windward area of the tailstock type unmanned aerial vehicle, the invention improves the effective lift area, improves the load-carrying performance, and the design of the short-tail full-moving rudder surface improves the handling performance. This UAV is especially suitable for short-range and high-flexibility investigations, such as the use of public security departments to track fugitives on highways.

Description

A new type of vector thrust dislocation biplane tailstock vertical take-off and landing UAV

technical field

The invention relates to the field of aviation technology, in particular to a tailstock type vertical take-off and landing unmanned aerial vehicle.

Background technique

At present, the mainstream vertical take-off and landing UAVs in the world include two categories: one is a conventional fixed-wing plus rotor component to form a composite-wing UAV, as described in the patent number CN110116802A, and the other is a flying-wing tailless layout. As described in the patent number CN207580149U. These two types of UAVs have their own advantages and disadvantages. The first type of compound-wing UAV uses multi-rotor components to provide lift and steering torque during take-off and landing. The disadvantage is that the four additional rotors and power systems only play a role in the take-off and landing process, and do not provide power during level flight, but act as redundant components to increase the extra load in level flight, and also cause a certain amount of air resistance. less efficient.

In addition, it is a tail-mounted UAV with a flying wing and tailless layout. During the vertical take-off and landing process, the fuselage is upright. When taking off and hovering, the rotor plane is perpendicular to the direction of gravity of the aircraft. When flying horizontally, the rotor plane and the ground level Vertical, this type of UAV needs to tilt the entire fuselage 90 degrees during the flight attitude switching process, which is more complicated when designing the control law. In addition, due to the limitation of the layout of this kind of UAV, the use of anti-camber airfoil has the disadvantage that the overall lift is low, the carrying capacity is limited, and the level flight speed is fast. The advantage is that no extra power is used in the process of vertical take-off and landing, and the conversion between horizontal flight and vertical take-off and landing is realized by tilting the fuselage, and the aerodynamic efficiency and structural use efficiency are higher.

SUMMARY OF THE INVENTION

The invention aims to solve the problems of small lift coefficient, small load capacity, high level flight speed lower limit and poor wind resistance capability of the existing tailstock UAV, and to improve mission load diversity, environmental adaptability, and tilting flexibility , to expand the scope of application of the task.

In order to achieve the above purpose, the present invention adopts a tail-mounted unmanned aerial vehicle with a staggered upper and lower wings and a short tail layout. noodle. Further, in the process of vertical take-off and landing and hovering, the UAV uses the left and right twin-engine propellers to provide static thrust, and the position is high. Attitude control and anti-wind operation are performed by using the vector power mechanism and the deflection of the tail rudder surface to provide torque. The vector power mechanism is composed of a vector motor base, a motor, a propeller, a vector tilt steering gear, and an ESC. Vector motor mounts mounted on support carbon fiber tubes

The fuselage assembly is made of aviation laminates, and is fixed to the aircraft through two carbon fiber tubes running through the fuselage at the front and rear. Due to the modular design of the UAV, the fuselage can be easily and conveniently replaced by pulling out two carbon fiber tubes according to different mission loads.

Through the above-mentioned design and organization method, when the UAV takes off and lands, the nose is vertically upward, and the tripod extending from the upper and lower wing braces provides support. When taking off, the UAV is powered by a two-engine vector power system. When converting to level flight, the vector motor mechanism is deflected, and the full-motion elevator on the short tail is deflected, providing enough torque to drive the UAV to tilt and enter level flight. In the process of level flight, the upper and lower wings provide most of the lift. Compared with the conventional flying wing without tail layout design, the dislocation design of the upper and lower flat wings of this UAV can also make the wing moments balance each other, depending on the Reduced torque on the stern provides improved maneuverability while reducing trim lift losses. This design improves the lift coefficient of the whole aircraft, effectively reduces the lower limit of the level flight speed, increases the payload, and improves the maneuverability.

Further, due to the staggered double-wing design, the UAV increases the effective wing area by about twice, while the projected area of the wing is about 1.3 times that of the single wing, and the projected area of the wing is not significantly improved. The wind resistance performance is effectively improved in the lowered state. The vector thrust system can change the direction of the pulling force line, which effectively improves the maneuverability and the wind resistance stability in the vertical take-off and landing state.

Further, the UAV has a compact design, and the fuselage and wings are modularly designed to be easily replaced. Among them, the upper and lower wing support plates play a structural reuse design, can support the upper and lower wings, and serve as a landing support frame, which is connected to the full-motion lift. aileron.

Description of drawings

The present invention will be described below with reference to the accompanying drawings

Figure 1. The overall schematic diagram of the new type of vector thrust dislocation bi-wing tailstock vertical take-off and landing UAV

Figure 2 Schematic diagram of the upper and lower wing braces and rudder surface components of the new type of vector thrust dislocation double-wing tailstock vertical take-off and landing UAV

Figure 3 Schematic diagram of the fuselage components of the new type of vector thrust dislocation bi-wing tailstock vertical take-off and landing UAV

Figure 4 Schematic diagram of the dual-engine vector power components of the new type of vector thrust dislocation bi-wing tailstock vertical take-off and landing UAV

Figure 5 Schematic diagram of the hovering attitude of the new type of vector thrust dislocation bi-wing tailstock vertical take-off and landing UAV

Detailed ways

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

As shown in FIG. 1 , the novel vector thrust dislocation double-wing tailstock VTOL UAV of the present invention includes an upper wing surface 102, a lower wing surface 101, a right aileron elevator surface 103, a left aileron elevator surface 104, and upper and lower wings. Strap 105 , right vector power system 107 , left vector power system 108 , fuselage assembly 109 . The upper and lower wings are installed up and down, and the front and rear are dislocated. The leading edge of the upper wing is forward of the leading edge of the lower wing. This arrangement can maximize the aerodynamic advantage of the double-wing layout. While the upper and lower wing braces connect the upper and lower fuselage, the fuselage is also fixed by two carbon fiber tubes, which has high structural efficiency. The left and right dual-engine vector power system is installed at the front, and the vertical position is in the middle of the upper and lower wings, providing the power and control ability of vertical take-off and landing.

As shown in FIG. 2, the upper and lower wing support plate assemblies have mounting holes 202 for connecting the upper wing surface and the lower wing surface mounting holes 201, mounting holes 203 and 204 for fixing the carbon fiber tubes of the fuselage, and the elevons 206 of the drone. It is fixed at the tail of the upper and lower wing support plates, and the steering gear 207 that controls the aileron is in the installation hole of the upper and lower support plate components. Deflection of the rudder surface. The upper and lower wing struts extend rearward to form upright landing gear 205 .

As shown in FIG. 3 , the fuselage assembly is composed of a front cover plate 303 , a side plate 301 , a central plate 302 , and an upper cover plate 307 . A full-motion rudder 304 is mounted on the fuselage. The fuselage is equipped with all avionics such as flight control, battery, camera and image transmission system.

As shown in FIG. 4 , the vector power system is composed of a propeller 401, a motor 402, a vector motor base 403, a support rod 404 and an adapter mount 405. The propeller is directly connected to the motor with double blades, and the motor is installed on the vector motor base through the screw hole at the bottom. The vector motor base is fixedly connected with the support rod and the adapter mounting. The vector motor base can deflect the direction of the motor pulling force, improving the flexibility and wind resistance of the UAV.

Finally, it should be noted that the above embodiments of the invention are only used to illustrate the technical solutions of the present invention, but not to limit them. Any modification, equivalent replacement and improvement made within the spirit and principle of the solution of the present invention shall be included in the protection scope of the solution of the present invention.

Claims (5)

1. a novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle, is characterized in that, comprises middle fuselage assembly, upper and lower wing braces, upper wing assembly, lower wing assembly, full-motion elevon, Vector power component; the UAV is directly tilted by tilting vector power and elevator deflection to drive the fuselage to tilt from the hovering state to the horizontal flight state, and relies on the static thrust output by the power propeller to maintain the attitude during the hovering and vertical take-off and landing stages. In the stable, level flight stage, the manoeuvres such as roll and yaw are realized by means of the elevons. 2. A novel vector thrust dislocation double-wing tailstock vertical take-off and landing unmanned aerial vehicle according to claim 1, characterized in that the upper and lower wing assemblies are fixed on the upper and lower wing support plates, and are fixed on the rear of the upper and lower wing support plates The middle fuselage and the upper and lower wing braces are connected by a circular tube beam, and the power unit is fixed on the circular tube beam. 3. a novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle according to claim 2, is characterized in that, its wing uses high camber high lift airfoil, straight wing shape, and does not have on the wing. The rudder surface is arranged, the upper and lower wings are installed in a front and rear dislocation, and the leading edge of the lower wing is at 60% of the chord length behind the upper wing. 4. a kind of novel vector thrust dislocation biplane tailstock type vertical take-off and landing drone according to claim 1, is characterized in that, wherein on the fuselage are installed pitot tubes, task loads such as cameras, batteries, flight controllers etc. Avionics. 5. a novel vector thrust dislocation double-wing tailstock type vertical take-off and landing unmanned aerial vehicle according to claim 1, is characterized in that the upper wing is located at the front above the relative position of the lower wing, and the leading edge of the upper wing is located at the leading edge of the lower wing 60 percent of the chord length to maximize the aerodynamic efficiency of the wings.

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