Vertical take-off and landing unmanned aerial vehicle having z-shaped folding wing

Abstract

A vertical take-off and landing unmanned aerial vehicle having a Z-shaped folding wing, comprising: a tubular fuselage (1), a main wing, lift motor support arms (3), lift motors (4), a horizontal thrust motor (7), and all-moving tailplanes (9). The main wing is mounted above the tubular fuselage (1), and can be folded in segments towards the middle to reduce a projection area; the lift motor support arms (3) are symmetrically mounted on a non-foldable section of the main wing with respect to the tubular fuselage (1) as the center; two ends, i.e. front and rear ends, of each lift motor support arm (3) are each provided with one lift motor; the horizontal thrust motor (7) is mounted at the head of the fuselage (1) to generate horizontal thrust; there are two all-moving tailplanes (9) in total, which are mounted at the tail of the fuselage (1) in an inverted V-shaped layout.

Description

A vertical take-off and landing unmanned aerial vehicle with Z-shaped folding wings TECHNICAL FIELD

[0001] The present application belongs to the field of unmanned aerial vehicles, and relates to a vertical take-off and landing unmanned aerial vehicle with Z-shaped folding wings. BACKGROUND

[0002] Composite wing vertical take-off and landing aircraft has become a major development direction of vertical take-off and landing aircraft because it has the flight speed and endurance time of fixed-wing aircraft and the vertical take-off and hovering ability of multi-rotor aircraft. During hovering and vertical take-off, the wings of conventional composite wing aircraft do not generate lift because there is no horizontal speed, and the aircraft becomes unstable due to factors such as wind and airflow, so it cannot perform hovering tasks in bad weather such as strong wind, and has to reduce the wing span to reduce airflow interference, but this also reduces the flight time. SUMMARY

[0003] The present application adopts a folding wing mode to reduce the length of the wings in the hovering state, thereby avoiding the influence of airflow on the hovering aircraft. The main wing is divided into three sections and folded in a Z shape, and the inverted V-shaped movable tail wing is folded forward along the rotation shaft. The combination of the aircraft body shape and the pod design allows the aircraft to have the smallest wind area in the folded state, which is conducive to long-term stable hovering. At the same time, the wings have a larger span than conventional aircraft after being unfolded, which allows the aircraft to have a longer endurance time and flight distance than other models of the same level.

[0004] TECHNICAL SCHEME

[0005] The present application provides a vertical take-off and landing unmanned aerial vehicle with Z-shaped folding wings, which comprises a tubular fuselage, a main wing, a lift motor support arm, a lift motor, a horizontal propulsion motor and a movable tail wing.

[0006] The main wing is installed above the tubular fuselage, and the segmented main wing can be folded towards the center to reduce the projected area. The lift motor support arms are symmetrically installed on the non-foldable section of the main wing with the tubular fuselage as the center. One lift motor is installed at the front and rear ends of the lift motor support arm. The horizontal propulsion motor is installed at the head of the fuselage to generate horizontal propulsion force. The movable tail wing has two pieces and is installed in an inverted V shape at the tail of the fuselage.

[0007] Further, the main wing comprises an inner fixed wing, a middle folding wing and an outer folding wing.

[0008] The inner fixed wing is installed above the tubular fuselage and is the non-foldable section of the main wing. The middle folding wing is fixed on both sides of the inner fixed wing through a rotation shaft and can be folded inward above the inner fixed wing. The outer folding wing is fixed outside the middle folding wing through a rotation shaft and can be folded inward above the middle folding wing.

[0009] The wing span of the inner section fixed main wing is 1 to 1.2 times the sum of the half span of the middle section folding main wing and the outer section folding main wing.

[0010] Further, the aircraft further comprises a tail folding mechanism;

[0011] The tail folding mechanism is installed at the rear of the fuselage, providing installation and folding functions for the movable tail, and is used to fold the movable tail forward to be parallel to the tubular fuselage.

[0012] Further, the aircraft further comprises a pod;

[0013] The pod is installed below the fuselage, providing installation space for loads and energy sources.

[0014] Further, the movable tail is rotated along the control axis to adjust the tail angle when unfolded, achieving pitch and heading control.

[0015] Further, the outer section folding main wing is provided with ailerons to achieve roll operation when the main wing is unfolded.

[0016] Further, the main wing and the movable tail are unfolded or folded synchronously to achieve switching between the fixed wing mode and the vertical take-off and landing mode of the aircraft.

[0017] Further, the pod is installed with a flight controller for receiving external instructions to achieve manual control of the unfolding or folding of the main wing and the movable tail, or collecting current environmental information to achieve automatic control of the unfolding or folding of the main wing and the movable tail. Beneficial effects:

[0018] The present application designs a multi-mode aircraft with vertical take-off and landing function, operating at a flight speed of 0-60km / h. The present application is used to achieve the following technical effects, that is, to provide an aircraft with evenly distributed four rotors as the power for vertical take-off and hovering, and to use the speed difference of the four rotors to achieve the control force during hovering and low-speed flight; having a three-section folding main wing, which is folded in Z shape when the aircraft is vertically taking off and hovering, reducing the wind area and ensuring the stability of the aircraft; unfolding during horizontal flight to obtain the longest flight time in the large wing span state; having a foldable inverted V-shaped tail, which is folded forward in the heading direction when the aircraft is vertically taking off and hovering, reducing the wind area; and achieving pitch and heading control during horizontal flight by manipulating the tail angle when unfolded. BRIEF DESCRIPTION OF DRAWINGS

[0019] Fig. 1 is a schematic view of the components of a Z-shaped folding wing vertical take-off unmanned aerial vehicle.

[0020] Fig. 2a is a top view of the aircraft in an unfolded state.

[0021] Figure 2b is a front view of the aircraft in its deployed state.

[0022] Figure 2c is a side view of the aircraft in its deployed state.

[0023] Figure 3a is a top view of the aircraft in its folded state.

[0024] Figure 3b is a front view of the aircraft in its folded state.

[0025] Figure 3c is a side view of the aircraft in its folded state.

[0026] Figure 4 shows a comparison of the aircraft in its unfolded and folded states.

[0027] Figure 5 shows a comparison of the fully movable tail fin in the deployed and folded states.

[0028] Figure 6 is a schematic diagram of the all-moving tail fin control. Detailed Implementation

[0029] This invention provides a Z-shaped folding wing vertical takeoff and landing unmanned aerial vehicle (UAV), as shown in Figure 1, comprising: a low-drag, lightweight tubular fuselage 1; an inner fixed main wing 2 mounted on top of the fuselage 1; two lift motor arms 3 symmetrically arranged on both sides of the fuselage 1, mounted on the inner fixed main wing 2; four lift motors 4 mounted at both ends of the lift motor arms 3; a mid-section folding main wing 5 fixed to both sides of the inner fixed main wing 2 via a pivot, which can be folded inward to above the inner fixed main wing 2; an outer folding main wing 6 fixed to the outside of the mid-section folding main wing 5 via a pivot, which can be folded inward to above the mid-section folding main wing 5; a horizontal propulsion motor 7 mounted at the front end of the fuselage 1 to generate horizontal propulsion; as shown in Figures 5-6, a tail wing folding mechanism 8 mounted at the rear of the fuselage 1 to provide installation and folding functions for an all-moving tail wing 9; the all-moving tail wing 9 consists of two pieces, installed in an inverted V-shape, which can be folded forward to be parallel to the fuselage 1; and a pod 10 mounted below the fuselage 1 to provide space for the installation of payload and energy.

[0030] As shown in Figures 2a, 2b, 2c, 3a, 3b, 3c, and 4, the main wing consists of five sections: an inner fixed main wing, a middle folding main wing, and an outer folding main wing, connected by a pivot. The middle and outer folding main wings can be folded in a Z-shape above the inner fixed main wing, reducing the frontal area during hovering. The all-moving tail can be folded forward to be parallel to the fuselage via a tail folding mechanism, further reducing the frontal area during hovering. The all-moving tail can rotate along the control axis in its deployed state to adjust the tail angle, enabling pitch and yaw control.

[0031] 1) During takeoff, the aircraft is in a folded state and takes off vertically using the power of the quadcopter; at this time, the aircraft's wind-receiving area is minimal, and the flight is stable;

[0032] 2) When reaching a certain height, the aircraft unfolds the wings and tail, and starts the horizontal propulsion motor, and the aircraft gradually accelerates to a horizontal cruising speed;

[0033] 3) Horizontal flight state, the aircraft can control the attitude of the aircraft through the control of the rudder and wing surfaces.

Claims

1. A vertical take-off and landing unmanned aerial vehicle of Z-folded wings, characterized by, Comprise: Tubular fuselage (1), main wing, lift motor arm (3), lift motor (4), horizontal propulsion motor (7), full-moving tail (9); The main wing is installed above the tubular fuselage (1), and the main wing is segmented and can be folded towards the center to reduce the projected area; The lift motor arm (3) is symmetrically installed on the non-foldable section of the main wing with the tubular fuselage (1) as the center; One lift motor (4) is installed at the front and rear ends of the lift motor arm (3); The horizontal propulsion motor (7) is installed at the head of the fuselage (1) to generate horizontal propulsion force; The full-moving tail (9) has two pieces and is installed in inverted V-shaped layout at the tail of the fuselage (1).

2. The aircraft of claim 1, wherein, The main wing comprises an inner fixed main wing (2), a middle folded main wing (5), and an outer folded main wing (6); The inner fixed main wing (2) is installed above the tubular fuselage (1) and is the non-foldable section of the main wing; The middle folded main wing (5) is fixed on both sides of the inner fixed main wing (2) through a rotating shaft and can be folded inward above the inner fixed main wing (2); The outer folded main wing (6) is fixed outside the middle folded main wing (5) through a rotating shaft and can be folded inward above the middle folded main wing (5); The wing span of the inner fixed main wing (2) is 1 to 1.2 times the sum of the half spans of the middle folded main wing (5) and the outer folded main wing (6).

3. The aircraft of claim 2, wherein, The aircraft further comprises a tail folding mechanism (8); The tail folding mechanism (8) is installed at the rear of the fuselage (1) and provides installation and folding functions for the full-moving tail (9), which is used to fold the full-moving tail (9) forward to be parallel to the tubular fuselage (1).

4. The aircraft of claim 1, wherein, The aircraft further comprises a nacelle (10); The nacelle (10) is installed below the fuselage (1) to provide installation space for loads and energy sources.

5. The aircraft of claim 3, wherein, When the full-moving tail is in the unfolded state, it rotates along the control axis to adjust the tail angle and realize pitch and heading control.

6. The aircraft of claim 2, wherein, The aileron is arranged at the trailing edge of the outer folded main wing (6) to realize roll operation in the unfolded state of the main wing.

7. The aircraft of claim 3, wherein, The main wing and the full-moving tail (9) are unfolded or folded synchronously to realize the switching between the fixed-wing mode and the vertical take-off and landing mode of the aircraft.

8. The aircraft of claim 7, wherein, The flight controller is installed in the nacelle to receive external instructions to realize manual control unfolding or folding of the main wing and the full-moving tail (9), or to collect current environmental information to realize automatic control unfolding or folding of the main wing and the full-moving tail (9).

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