Single-propeller deformable unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicle design, and discloses a single-propeller deformable unmanned aerial vehicle, which adopts a tail boom type fuselage and n-shaped empennage layout design, and comprises a wing hanging beam; the wings are symmetrically connected to the two sides of the wing hanging beam; the tail booms are connected to the wings, vertical empennages are arranged on the tail booms, and the two vertical empennages are connected through a horizontal empennage; the cover body is installed on the wing hanging beam and comprises a front cover body and a rear cover body which are installed at the two ends of the wing hanging beam respectively, and the rear cover body can move on the wing hanging beam and can be locked with the front cover body in a butt joint mode; the power device is arranged on the wing hanging beam; and a landing gear. The problems of efficiency and safety of existing air-drop are solved, the wing hanging beam serves as a main force bearing beam, and the front cover body and the rear cover body only play a role in rectification and do not participate in bearing. The structural weight of the aircraft is reduced to the maximum extent, and meanwhile the loading capacity of the aircraft is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aircraft design, and in particular relates to a single-propeller deformable unmanned airdrop aircraft. Background Art

[0002] The design and use of aircraft airdrop systems need to consider many factors, including the aircraft's flight performance, the weight and size of the cargo, the accuracy requirements for delivery, and the airdrop environment. With the development of technology, airdrop systems are becoming more automated and intelligent to improve the efficiency and safety of airdrops.

[0003] At present, the airdrop mission of the aircraft platform requires a lot of preparation work, which is time-consuming and labor-intensive. The airdrop system is highly complex and takes a long time to maintain, and its overall cost is also high. It is difficult to quickly meet the needs of tasks such as cargo transportation and rescue material delivery. How to improve the efficiency of replenishment and realize the airdrop of standard containers is an issue that we urgently need to solve. Summary of the invention

[0004] In view of the problems of the background technology, the present invention proposes a single-propeller deformable unmanned airdrop aircraft. By using air / land / water intermodal standard containers, the freight efficiency can be improved by replacing the containers; after the container is airdropped, the rear cover and the front cover of the aircraft can be docked together, and the aircraft can ensure that it can fly with the maximum flight performance; at the same time, standardized, universal and modular accessories are used to improve the economy of the aircraft.

[0005] The technical solution of the present invention is achieved in this way:

[0006] A single-propeller deformable unmanned airdrop aircraft adopts a tail-supported fuselage and a P-shaped tail layout design, comprising:

[0007] The wing beam is the main load-bearing beam that runs through the entire fuselage;

[0008] Wings symmetrically connected to both sides of the wing suspension beam;

[0009] A tail strut connected to the wing, wherein a vertical tail is provided on the tail strut, and two vertical tails are connected via a horizontal tail;

[0010] A cover body installed on the wing suspension beam, the cover body includes a front cover body and a rear cover body, which are respectively installed at two ends of the wing suspension beam, and the rear cover body can move on the wing suspension beam and can be docked and locked with the front cover body;

[0011] A power device disposed on the wing suspension beam; and

[0012] landing gear.

[0013] As a further solution of the present invention: the landing gear includes a front landing gear and a main landing gear, the front landing gear is installed on the wing suspension beam, and the main landing gear is installed on the wing.

[0014] As a further solution of the present invention: the front cover adopts a split structural design, is hingedly mounted on the wing suspension beam, and can be opened laterally.

[0015] As a further solution of the present invention: a slide rail device is provided on the wing suspension beam, and the rear cover is hinged on the slide rail device and can be flipped upwards.

[0016] As a further solution of the present invention: the wing is provided with a wing tip, which is a fairing part at the outer end of the wing and is installed on the wing end rib.

[0017] As a further solution of the present invention: the power device includes an engine and a propeller.

[0018] As a further solution of the present invention: the wing suspension beam is provided with a standard joint, which can be connected to a separate standard container.

[0019] As a further solution of the present invention: the separated standard container adopts an international standard container, is installed on the wing hanging beam using four joints, and uses an electric drive device to autonomously unlock and lock, meeting the needs of efficient intermodal transport.

[0020] The beneficial effects of this application are:

[0021] 1. Standard containers use detachable standard containers to meet the needs of fast air / land / water transport.

[0022] 2. The wing suspension beam is used as the main load-bearing beam, and the front and rear covers only play a rectifying role and do not participate in the load-bearing, thereby minimizing the structural weight of the aircraft and improving the aircraft's loading capacity.

[0023] 3. The rear cover opens upwards, and the ground airport equipment can achieve the docking and rapid separation of standard containers. The aircraft transit time can be shortened to less than 10 minutes, and the efficiency is more than 3 times higher than that of conventional aircraft.

[0024] 4. The front and rear covers of the aircraft are replaceable, the left and right nacelles, the structural parts and system parts of the left and right main lifts are interchangeable, the left and right wings are interchangeable, the left and right vertical tails are interchangeable, and the horizontal vertical tail adopts the same airfoil and integrated actuator design, which simplifies the tooling to the greatest extent and improves the economy of the entire life cycle from research and development, manufacturing to use.

[0025] 5. All parts of the UAV body adopt an integral structure, which greatly reduces on-site assembly; the body structural parts and equipment adopt standardized design, reducing the types of accessories and materials.

[0026] 6. The front cover of the aircraft is centrally arranged with an integrated and modular flight control system, navigation system, power system and information transmission system, etc., which can be repaired and replaced by one person using handheld maintenance equipment, making the UAV highly safe, reliable, testable, usable and maintainable.

[0027] The present application is further described in detail below in conjunction with the accompanying drawings of the embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a structural schematic diagram of a single-propeller deformable unmanned airdrop aircraft of the present invention;

[0029] Figure 2 It is a front view schematic diagram of a single-propeller deformable unmanned airdrop aircraft of the present invention;

[0030] Figure 3 It is a side view schematic diagram of a single-propeller deformable unmanned airdrop aircraft of the present invention;

[0031] Figure 4 It is a side view schematic diagram of the airdropping of a standard container with the rear cover moving forward according to the present invention;

[0032] Figure 5 It is a top view schematic diagram of a single-propeller deformable unmanned airdrop aircraft of the present invention;

[0033] Figure 6 It is a side view schematic diagram of the rear cover body of the present invention opened upward;

[0034] Figure 7 It is a side view schematic diagram of the rear cover body of the present invention moving forward;

[0035] Figure 8 It is a schematic side view of the front cover body of the present invention with both sides opened.

[0036] The accompanying drawings are marked as follows: 1-wing suspension beam, 2-separate standard container, 3-front cover, 4-rear cover, 5-wing, 6-tail support, 7-vertical tail, 8-horizontal tail, 9-power unit, 10-landing gear, 51-left wing, 52-right wing, 53 / 54-wing tips, 61-left tail support, 62-right tail support, 71-right vertical tail, 72-left vertical tail, 91-engine, 92-propeller, 101-front landing gear, 102 / 103-main landing gear. DETAILED DESCRIPTION

[0037] The technical solution of the present application will be described clearly and completely below in conjunction with the accompanying drawings of the embodiments.

[0038] Figures 1 to 8 It is a schematic diagram for illustrating an embodiment of the single-propeller deformable unmanned airdrop aircraft of the present invention.

[0039] A single-propeller deformable unmanned airdrop aircraft comprises a wing beam 1, a detachable standard container 2, a front cover 3, a rear cover 4, a wing including a wing tip 5, a tail support 6, a vertical tail 7, a horizontal tail 8, a power unit engine and a propeller 9, and a front landing gear and a main landing gear 10. Standardized, universal and modular accessories are used, and each major component is interchangeable to improve the economy of the aircraft.

[0040] The wing suspension beam 1 is the main load-bearing beam that runs through the entire fuselage.

[0041] The detachable standard container 2 can choose containers of different specifications according to different mission scenarios to meet the airdrop requirements of different goods. The detachable standard container 2 adopts international standard containers, which are installed on the wing beam using four joints and are automatically unlocked and locked using an electric drive device to meet the needs of efficient intermodal transport. It adopts the form of standard containers, including general-purpose containers of standard sizes, insulated standard containers, livestock air transport standard containers, airdrop standard containers, etc.

[0042] The front cover 3 is designed to be replaceable and can be opened to both sides, which is convenient for the inspection and maintenance of the aircraft management system. The front cover 3 is installed with a quick release lock and can be opened laterally. The hinge joints are set on both sides of the front cover frame to facilitate the inspection and maintenance of the entire aircraft equipment.

[0043] The rear cover 4 is designed to be replaceable. It can be moved forward through the slide rail device installed at the bottom of the wing hanging beam, and docked and locked with the front cover to form a complete aircraft aerodynamic shape to improve the flight performance of the aircraft after the container is airdropped. The hinge joint and drive device of the rear cover 4 are installed at the rear of the wing hanging beam. The entire rear cover can be flipped up using the gas strut to ensure the channel for autonomous docking and rapid disassembly of standard containers.

[0044] The front cover 3 and the rear cover 4 are aerodynamically optimized in design with comprehensive consideration of innovation, aesthetics, and craftsmanship. After the airdrop is completed, the rear cover can move forward to dock and lock with the front cover, allowing the aircraft to fly with maximum performance.

[0045] The wing 5 comprises a left wing 51 and a right wing 52; the wing tips 53 / 54 are the fairing parts at the outer ends of the wings and are installed on the wing end ribs.

[0046] Also includes: tail support 6;

[0047] There are two tail supports 6, a left tail support 61 and a right tail support 62.

[0048] Also includes: vertical tail 7;

[0049] There are two vertical tails 7, a right vertical tail 71 and a left vertical tail 72, one on each tail strut 6. The front and rear beams of the vertical tail 7 are directly inserted into the tail strut 6 and are integrated with the tail strut 6.

[0050] Also includes: horizontal tail 8;

[0051] The horizontal tail 8 is installed on the top of the two vertical tails 7.

[0052] It also includes: a power device 9 arranged on the wing suspension beam;

[0053] The power unit 9 includes an engine 91 and a propeller 92 .

[0054] Also includes: a landing gear 10;

[0055] A front landing gear 101 is arranged under the front cover, and a main landing gear 102 / 103 is arranged on the left and right wings respectively. The main landing gear is retracted at the side of the tail support, which can reduce the cross-sectional size of the tail support and thus reduce the weight of the tail support compared with being retracted inside the tail support.

[0056] Example:

[0057] The aircraft adopts a high-wing, tail-brace fuselage, P-type tail, two wing-mounted piston engines, and a front three-point wing landing gear layout.

[0058] 1) The aircraft has a main load-bearing wing beam, and the mission container, wing, front and rear covers, and front landing gear are connected by longitudinal beams.

[0059] 2) The front cover of the aircraft opens sideways to facilitate the inspection and maintenance of the aircraft management system; the rear cover flips up to enable standard containers or cargo to enter and exit.

[0060] 3) The aircraft has a detachable standard container connected to the wing beam through a connecting joint;

[0061] 4) The aircraft is equipped with one engine, which is installed through the wing hanging beam;

[0062] 5) The aircraft is equipped with two tail struts, which are butted with the nacelle at the rear beam plane of the wing;

[0063] 6) The aircraft is equipped with two vertical tails, one vertical tail is installed on one tail support, the tail support and the vertical tail are designed to be integrated, and the front and rear beams of the tail support are inserted into the tail support for docking;

[0064] 7) The aircraft uses a horizontal tail, which is installed on top of two vertical tails;

[0065] 8) The aircraft is equipped with three landing gears, one front landing gear and two main landing gears. The front landing gear is installed on the wing longitudinal beam and the main landing gear is installed under the wing.

[0066] 9) The retracted position of the aircraft's main landing gear is located inside the tail strut.

[0067] 10) The structural parts and system parts of the left and right nacelles and the left and right landing gears of the aircraft are designed to be consistent, which reduces the types of spare parts and facilitates use and maintenance.

[0068] 11) The aircraft can directly replace standard containers to improve operational efficiency, reduce aircraft stopover time, and improve aircraft economy;

[0069] 12) The aircraft standard container can select different types and specifications of standard containers for autonomous docking according to different missions, and can be used for air, land and sea transport.

[0070] So far, the purpose of the present invention has been achieved.

[0071] The above are only preferred embodiments of the present invention and are 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 single-propeller deformable unmanned airdrop aircraft, characterized in that: It adopts tail-brace fuselage and П-type tail layout design, including: The wing beam is the main load-bearing beam that runs through the entire fuselage; Wings symmetrically connected to both sides of the wing suspension beam; A tail strut connected to the wing, wherein a vertical tail is provided on the tail strut, and two vertical tails are connected via a horizontal tail; A cover body installed on the wing suspension beam, the cover body includes a front cover body and a rear cover body, which are respectively installed at two ends of the wing suspension beam, and the rear cover body can move on the wing suspension beam and can be docked and locked with the front cover body; A power device disposed on the wing suspension beam; and landing gear.

2. The single-propeller deformable unmanned airdrop aircraft according to claim 1, characterized in that: The landing gear comprises a front landing gear and a main landing gear, wherein the front landing gear is mounted on the wing suspension beam, and the main landing gear is mounted on the wing.

3. The single-propeller deformable unmanned airdrop aircraft according to claim 2, characterized in that: The front cover adopts a split structure design, is hingedly mounted on the wing suspension beam, and can be opened laterally.

4. The single-propeller deformable unmanned airdrop aircraft according to claim 3, characterized in that: A slide rail device is provided on the wing suspension beam, and the rear cover body is hinged on the slide rail device and can be flipped upwards.

5. The single-propeller deformable unmanned airdrop aircraft according to claim 4, characterized in that: The wing is provided with a wing tip, which is a fairing part at the outer end of the wing and is installed on the wing end rib.

6. The single-propeller deformable unmanned airdrop aircraft according to claim 5, characterized in that: The power unit comprises an engine and a propeller.

7. The single-propeller deformable unmanned airdrop aircraft according to claim 6, characterized in that: The wing hanging beam is provided with a standard joint, which can be connected to a separate standard container.

8. The single-propeller deformable unmanned airdrop aircraft according to claim 7, characterized in that: The separated standard container adopts an international standard container, is installed on the wing hanging beam using four joints, and uses an electric drive device to autonomously unlock and lock, meeting the needs of efficient intermodal transport.

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