Vertical take-off landing craft with wind guiding plate

Abstract

To solve the problem of crash accidents due to a vortex ring state that is one of problems of vertical take-off landing crafts including helicopters and drones.SOLUTION: In a vertical take-off landing craft of the present invention, an arm is mounted on a main wing, and two-vane elevating propellers are mounted on the front and back of the arm. A front wing is located above in front of the front elevating propeller, and the front wing is mounted on the arm. Since the front wing, upon vertical lowering, works to obstruct an air stream flowing upward from below, the same can obstruct the occurrence of a vortex ring state. An advancing propeller is located below the back of the front elevating propeller, and air of the bottom of the front elevating propeller is sucked by the rotation of the propeller. Consequently, the front elevating propeller can obstruct the situation of turning into a vortex ring state.SELECTED DRAWING: Figure 4

Description

[Technical Field]

[0001] The present invention relates to a vertical take-off and landing aircraft. [Background technology]

[0002] Vertical take-off and landing aircraft include helicopters and drones. One of the problems with these aircraft is the risk of crashes caused by vortex ring states.

[0003] The vortex ring state, also known as settling with power, occurs when a helicopter, vertical take-off and landing aircraft, or drone descends rapidly, causing the downwash to be sucked back into the propeller, resulting in air circulating vertically around the propeller.

[0004] Downwash is the downward wind caused by the rotation of a propeller, and a vortex ring state is essentially a helicopter, VTOL aircraft, or drone falling into its own downwash.

[0005] A vortex ring state can cause a loss of lift, potentially leading to a crash. The occurrence of a vortex ring state is the number one or second leading cause of helicopter crashes. When rapidly descending helicopters, vertical take-off and landing aircraft, and drones, they are affected by downwash, so caution is required to prevent the occurrence of a vortex ring state.

[0006] As a specific means of preventing the occurrence of a vortex ring state, the vertical take-off and landing aircraft of the present invention has an arm attached to the main wing, two-bladed lift propellers attached to the front and rear of the arm, and also has a front wing.

[0007] There is a canard attached to the arm above and in front of the two-bladed lift propeller at the front. During vertical descent, this canard interferes with the airflow flowing from below to above, preventing the occurrence of a vortex ring state. Elevators and ailerons can also be attached to this canard.

[0008] There is a forward propeller behind and below the two-bladed front lift propeller, and as this propeller rotates, it sucks in air from under the two-bladed front lift propeller, preventing the two-bladed front lift propeller from entering a vortex ring state.

[0009] The vertical take-off and landing aircraft of the present invention also has a two-bladed ascent propeller at the rear of the arm attached to the main wing. In front of this rear two-bladed ascent propeller is the main wing, which obstructs the airflow flowing from below to above during vertical descent, thereby preventing the occurrence of a vortex ring state.

[0010] Furthermore, a forward propeller is attached to the main wing, and behind the forward propeller there is a flap and a propeller wake deflector. These deflect the propeller wake generated by the rotation of the forward propeller, bending it downward to form downwash, which flows downward. This generates vertical lift. This downwash makes it difficult for airflow to flow from below to above when the aircraft descends, preventing the two-bladed lift propeller at the rear from entering a vortex ring state.

[0011] The vertical take-off and landing aircraft of the present invention has wingtip plates near the tips of the main wings, which extend rearward and prevent the rear two-bladed lift propeller from entering a vortex ring state. [Prior art documents] [Patent documents]

[0012] [Patent Document 1] Special Publication No. 2014-528382 Summary of the Invention [Problem to be solved by the invention]

[0013] The present invention aims to reduce crashes caused by vortex ring states. [Means for solving the problem]

[0014] The advantage of this invention is that the baffle plate bends the propeller wake flowing backward downward, generating a vertical upward force. This allows the propeller thrust to be used more effectively and reduces crashes caused by vortex ring states. Furthermore, the propeller thrust can be used both during vertical takeoff and landing and during horizontal flight. Furthermore, this baffle plate can also generate lift during horizontal flight. Furthermore, ailerons can be attached to this baffle plate.

[0015] The wingtip plates also function as vertical stabilizers, and by attaching a rudder to the rear of the wingtip plates, the direction of the aircraft can be controlled during horizontal flight. The wingtip plates are positioned far below the main wing, so wheels can be attached to the bottom of the wingtip plates to support the aircraft. These wheels can increase the tread, i.e., the distance between the centers of the left and right tire contact surfaces, thereby maintaining the stability of the aircraft when on the ground.

[0016] The vertical take-off and landing aircraft of the present invention does not need to rotate its four two-bladed ascent propellers during horizontal flight. This is because the aircraft's gravity can be supported by the lift of the main wings alone. Therefore, during horizontal flight except during vertical take-off and landing, the four two-bladed ascent propellers are stopped in a state where air resistance is minimal. This allows the aircraft to save fuel during horizontal flight. Note that the main wings can be fitted with ailerons or spoilers in addition to flaps. [Effects of the Invention]

[0017] This invention can reduce crashes caused by vortex ring states. [Brief explanation of the drawings]

[0018] [Figure 1] FIG. 1 is a plan view of a vertical take-off and landing aircraft of the present invention. [Figure 2] FIG. 2 is a cross-sectional view taken along the line AA of the vertical take-off and landing aircraft of the present invention. [Figure 3] FIG. 3 is a partial detailed view of the AA cross section of the vertical take-off and landing aircraft of the present invention. [Figure 4] FIG. 4 is a cross-sectional view of the vertical take-off and landing aircraft of the present invention taken along line AA with the flaps lowered. [Figure 5] FIG. 5 is a partial detailed view of a cross section taken along line AA of the vertical take-off and landing aircraft of the present invention with the flaps lowered. [Figure 6] FIG. 6 is a B-B cross-sectional view of the vertical take-off and landing aircraft of the present invention. [Figure 7] FIG. 7 is a partial detailed plan view of a vertical take-off and landing aircraft of the present invention. DETAILED DESCRIPTION OF THE INVENTION [Example]

[0019] Figure 1 shows an embodiment of a vertical take-off and landing aircraft of the present invention, with a fuselage 5 attached below main wings 4 and arms 2 attached to the top of the main wings 4. Wing end plates 3 are attached near the tips of the main wings 4. These wing end plates 3 also function as vertical stabilizers, with rudders attached to the rear of the wing end plates.

[0020] Attached to the arms 2 are the canards 1. Four two-bladed lift propeller rotating discs 6 indicate the mounting locations of the lift propellers.

[0021] 2 is an AA cross-sectional view of the vertical take-off and landing aircraft of the present invention in horizontal flight. Two two-bladed ascent propellers 20 are attached below and above the arm 2. An engine 12 is attached below the main wing 4 via a pylon 10, and a forward propeller 11 is attached to the engine 12.

[0022] A boom 13 extends from the rear of the engine 12, and a wind guide plate 15 is attached to the end of the boom 13 via a hinge 14.

[0023] 3 is a partial detailed view of the AA cross section of the vertical take-off and landing aircraft of the present invention, with the flaps 16 of the main wing 4 in the raised position.

[0024] Figure 4 is an AA cross-sectional view of the vertical take-off and landing aircraft of the present invention, showing the aircraft in a vertical take-off and landing state. The flap 16 is lowered, and the baffle plate 15 rotates around the hinge 14 to stand upright. As a result, the propeller wake generated by the forward propeller 11 is bent downward by the flap 16 and the baffle plate 15, becoming downwash. This generates vertical lift.

[0025] 5 is a partial detailed view of the AA cross section of the vertical take-off and landing aircraft of the present invention, with the flaps 16 of the main wing 4 in the lowered position.

[0026] 6 is a B-B cross-sectional view of the vertical take-off and landing aircraft of the present invention. The forward propeller rotating disk 30 indicates the mounting position of the forward propeller.

[0027] The wingtip plates 3 hang downward from the main wings 4, so if wheels are attached to the bottom of these wingtip plates, the tread can be made larger, making the aircraft more stable on the ground.

[0028] 7 is a partial detailed plan view of the vertical take-off and landing aircraft of the present invention. This figure shows the aircraft in horizontal flight, with the four two-bladed ascent propellers 20 stopped in a state where air resistance is minimal. [Industrial Applicability]

[0029] The present invention can be used in place of a vertical take-off and landing aircraft, a drone, or a helicopter. [Explanation of symbols]

[0030] 1.Forewing 2. Arm 3. Wingtip 4. Main wing 5. Torso 6. Two-bladed lift propeller rotating disk 10. Pylon 11. Forward propeller 12. Engine 13. Boom 14. Hinge 15.Air guide plate 20. Two-bladed climb propeller 30. Forward propeller rotating disk

Claims

1. A vertical take-off and landing aircraft characterized by having a propeller wake deflector.

2. 2. The vertical take-off and landing aircraft of claim 1, further comprising wingtip plates.

3. 2. The vertical take-off and landing aircraft of claim 1, wherein an arm is attached to the main wing, and the arm has an ascent propeller.

4. 4. The vertical take-off and landing aircraft according to claim 3, wherein the arm has a front wing.

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