Foldable double-engine front-pulling delta wing aircraft

Abstract

The foldable double-engine front-pulling delta wing aircraft comprises a fuselage, a left wing and a right wing, and the fuselage is provided with an upper wing platform and a lower equipment cabin; the left wing and the right wing are hinged to the lower edge of the wing platform through a folding mechanism, and the left wing and the right wing can be folded downwards to be parallel to the fuselage and can be automatically unfolded to coincide with the plane of the wing platform in an unfolded flight state; double-engine power systems are arranged at the front edges of the left wing and the right wing; vertical fins are mounted at wingtips of the left wing and the right wing. The invention has the following beneficial effects: in a folded storage state, the occupied space is small, and the portability is good; unfolding is easy, and using convenience is good; power is strong, no reverse torsional moment exists, and flight is stable; the system is suitable for various takeoff modes; and the safety of the unmanned aerial vehicle in the landing process is effectively protected. The unfolding mechanism is simple, reliable and light in weight, the machine body space is huge, and various loads can be conveniently installed to complete different tasks.

Description

Technical Field

[0001] The invention relates to the field of aerodynamic layout of unmanned aerial vehicles, and in particular to a foldable twin-engine front-pull delta-wing aircraft. Background Art

[0002] Generally, patrol drones adopt conventional layout, which has disadvantages such as complex structure, cumbersome installation, inconvenient to carry, and complex control. Generally, catapult drones and cruise missiles adopt tandem wing layout, which has complex structure, poor low-speed performance, unstable aerodynamic surface, complex deployment mechanism, complex locking mechanism, low space utilization, high recovery risk and many other disadvantages. Summary of the invention

[0003] In order to solve the above problems, the present invention provides a foldable twin-engine front-pull delta-wing aircraft.

[0004] The technical solution of the present invention is: a foldable twin-engine front-pull delta-wing aircraft, comprising a fuselage and left and right wings. The fuselage has an upper wing platform and a lower equipment compartment; The left wing and the right wing are hinged to the lower edge of the wing platform through a folding mechanism. The left wing and the right wing can be folded down to be parallel to the fuselage, and can be automatically unfolded to coincide with the plane of the wing platform when in the unfolded flight state; The leading edges of the left wing and the right wing are provided with a twin-engine power system; The wing tips of the left wing and the right wing are provided with vertical tails.

[0005] The folding mechanism is a hinge spring hinge.

[0006] The vertical tail is installed in an inverted manner.

[0007] The wing platform and the equipment cabin are both hollow cavities.

[0008] The twin-engine power system includes a left power system and a right power system; the left power system is centrally installed on the left wing, and the right power system is installed on the right wing.

[0009] Compared with the prior art, the present invention has the following beneficial effects: 1. It takes up little space when folded and has good portability, making it easy to carry and store.

[0010] 2. The unfolding process is simple and easy to use, without complicated operation steps.

[0011] 3. It adopts a twin-engine front-pull power mode, which has strong power, no reverse torque and stable flight.

[0012] 4. The double delta wing layout enables the aircraft to have excellent performance when flying at low speed and high angle of attack, and is suitable for a variety of take-off methods.

[0013] 5. The bottom of the fuselage is higher, and the main wing and propeller are farther away from the bottom, which effectively protects the safety of the drone during landing.

[0014] 6. It has a simple structure, low production cost, stable flight, easy to unfold and fold, strong portability, excellent low-speed performance, simple and reliable wing folding and unfolding mechanism, light weight, huge body space, easy to install various loads to complete different tasks, and a huge bottom area of ​​the body that can effectively protect the load to complete landing. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 Schematic diagram of the structure of the present invention.

[0016] Figure 2 The present invention is an unfolded front view schematic diagram.

[0017] Figure 3 The present invention is a schematic diagram of the front view of the unfolding process.

[0018] Figure 4 Schematic diagram of the folded front view of the present invention.

[0019] Figure 5 The present invention is a schematic diagram of the right side.

[0020] Figure 6 The present invention is a bottom view schematic diagram. DETAILED DESCRIPTION

[0021] like Figure 1-6 As shown, a foldable twin-engine front-pull delta-wing aircraft comprises a fuselage 1 and a left wing 2 and a right wing 3. The fuselage 1 has an upper wing platform 5 and a lower equipment compartment 6. The left wing 2 and the right wing 3 are hinged to the lower edge of the wing platform 5 through a folding mechanism 4. The left wing 2 and the right wing 3 can be folded downward to be parallel to the fuselage 1, and can be automatically unfolded to coincide with the plane of the wing platform 5 when in the unfolded flight state; The leading edges of the left wing 2 and the right wing 3 are provided with a twin-engine power system 7; The wing tips of the left wing 2 and the right wing 3 are provided with vertical tails 8 to improve flight stability and controllability.

[0022] The folding mechanism 4 is a hinge spring hinge, so that in the folded storage state, the left and right wings can be compactly folded, and in the unfolded flight state, the left and right wings can be automatically unfolded without the need for an additional locking mechanism.

[0023] The vertical tail 8 is installed in an inverted manner, so that the bottom of the fuselage is higher, and the main wing and the propeller are farther away from the bottom surface, so as to effectively protect the aircraft during gliding or parachuting.

[0024] The wing platform 5 and the equipment compartment 6 are both hollow, so that the purpose of flexibly arranging the effective load can be achieved. The folded storage state occupies a small space, is easy to carry and store, and the unfolding process is simple, and the convenience of use is good.

[0025] The twin-engine power system 7 includes a left power system 71 and a right power system 72; the left power system 71 is centrally mounted on the left wing 2, and the right power system 72 is mounted on the right wing 3. It provides forward pulling power without reverse torque. The twin-engine power system provides strong power, so that when the aircraft is in the unfolded flight state, the wings and the control surfaces can be immersed in the propeller slipstream, and the aircraft can complete the conversion flight by itself without the need for the vehicle to give the initial speed.

[0026] In this practical technical solution, the fuselage 1 is made of lightweight and high-strength materials, and the upper wing platform 5 and the lower equipment compartment 6 are both hollow structures, which can flexibly arrange batteries, flight control systems, payloads and other payloads as needed. The left wing 2 and the right wing 3 are hinged to the lower edge of the wing platform 5 through hinge spring hinges 4, and can be folded down to be parallel to the fuselage 1. The twin-engine power system 7 includes a left power system 71 and a right power system 72, which are respectively centrally installed on the left wing 2 and the right wing 3 to provide strong forward pulling power. An inverted vertical tail 8 is installed at the wing tip to improve flight stability and controllability.

[0027] In the folded storage state, the aircraft takes up little space and is easy to carry and store. When unfolded for flight, the wings automatically unfold to coincide with the plane of the wing platform 5 under the action of the hinge spring hinge 4, without the need for an additional locking mechanism. The aircraft adopts a twin-engine front-pull power method, which is powerful and stable in flight. The design of the inverted vertical tail 8 enables the aircraft to have excellent performance when flying at low speed and high angle of attack, and is suitable for various take-off methods such as hand-throwing take-off and catapult take-off.

[0028] The technical solution of this embodiment is that the fuselage is made of lightweight and high-strength materials, and the wing platform and equipment compartment are both cavity structures, which can flexibly arrange batteries, flight control, and load equipment as needed. The left and right wings are hinged to the lower edge of the wing platform of the fuselage through spring hinges and can be folded down to be parallel to the fuselage. The twin-engine power system is located at the leading edge of the wing, installed in the center, providing strong forward pulling power. The wingtips are equipped with inverted vertical tails to improve flight stability and controllability.

[0029] In the folded storage state, the left and right wings are folded down, and the whole machine is small in size, which can be easily placed in the launch tube or storage box. When unfolding for flight, the left and right wings automatically unfold to coincide with the wing platform plane under the action of the hinge spring, without the need for an additional locking mechanism. The aircraft is suitable for a variety of take-off methods such as hand-throwing take-off and catapult take-off, and can maintain excellent performance when flying at low speed and high angle of attack.

[0030] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A foldable twin-engine delta-wing aircraft, comprising a fuselage (1) and a left wing (2) and a right wing (3), characterized in that: The fuselage (1) has an upper wing platform (5) and a lower equipment compartment (6); The left wing (2) and the right wing (3) are hinged to the lower edge of the wing platform (5) through a folding mechanism (4); the left wing (2) and the right wing (3) can be folded downward to be parallel to the fuselage (1), and can automatically unfold to coincide with the plane of the wing platform (5) when in an unfolded flight state; The leading edges of the left wing (2) and the right wing (3) are provided with a twin-engine power system (7); The wing tips of the left wing (2) and the right wing (3) are provided with vertical tails (8).

2. A foldable twin-engine front-pull delta-wing aircraft according to claim 1, characterized in that: The folding mechanism (4) is a hinge spring hinge.

3. A foldable twin-engine front-pull delta-wing aircraft according to claim 1, characterized in that: The vertical tail (8) is installed in an inverted manner.

4. A foldable twin-engine front-pull delta-wing aircraft according to claim 1, characterized in that: The wing platform (5) and the equipment cabin (6) are both hollow cavities.

5. A foldable twin-engine delta-wing aircraft according to claim 1, characterized in that: The twin-engine power system (7) comprises a left power system (71) and a right power system (72); the left power system (71) is centrally mounted on the left wing (2), and the right power system (72) is mounted on the right wing (3).

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