Three-hull segmented wing double-engine propulsion heavy-load water transportation unmanned aerial vehicle

Abstract

The utility model discloses a three-hull segmented wing double-engine propulsion heavy-load water transportation unmanned aerial vehicle. The novel three-hull segmented wing double-engine propulsion heavy-load water transportation unmanned aerial vehicle consists of three parallel hulls, a combined wing surface, a control surface system and a double-engine propulsion system. The three parallel ship bodies are composed of the central main ship body and the two side ship bodies, serve as an aircraft main body structure and provide water net buoyancy and material load loading space, the combined wing face is composed of the inner wing section, the outer wing section, the connecting type horizontal tail and the vertical tail, and the water surface sliding stability, the aircraft structural strength and the low-altitude flight ground effect lift force are improved. According to the heavy-load water unmanned aerial vehicle, ground-effect flight is adopted, higher transportation capacity and ground-effect flight lift force are achieved, the lift force can be increased by 40%, the loading space and capacity can be increased by 30%, the voyage can be increased by 30%, the heavy-load water unmanned aerial vehicle has higher structural strength and longer endurance, and the heavy-load water unmanned aerial vehicle can be used for transportation, search and rescue and island material transportation in water areas such as lake surfaces on the sea.

Description

Technical Field

[0001] This utility model relates to unmanned aerial vehicles for water transport, and in particular to a three-hull segmented wing twin-engine propulsion heavy-load unmanned aerial vehicle for water transport. Background Technology

[0002] my country has a vast sea area of ​​over 4.7 million square kilometers, with numerous islands totaling nearly 10,000, and a coastline exceeding 14,000 kilometers. The delivery of vital supplies along the coast, between islands, along large rivers, and on lakes, as well as rescue operations for major maritime accidents, have become crucial needs for maritime material transport. While maritime vessels can transport supplies quickly and with large loads, their timeliness, convenience, and cost are significantly lacking. Existing aircraft, especially heavy-load transport aircraft or unmanned transport aircraft, rely on land-based airports or makeshift airfields, which cannot meet the needs of delivering or transferring supplies across large sea areas, long coastlines, and numerous islands in terms of range, takeoff and landing sites, and ease of use. Considering the current application status and existing problems, transport aircraft are an important solution. As mentioned earlier, manned aircraft designed for heavy-load transport generally require dedicated airports or makeshift airfields, with specific requirements for takeoff and landing conditions and flight routes. For many islands, these requirements are difficult to meet. Transport-oriented drones fall into two categories: conventional fixed-wing drones and multi-rotor drones. While these drones have relatively high range and loiter time, they are similar to manned transport aircraft, requiring stringent takeoff and landing conditions and maintenance requirements. They are unsuitable for the frequent transport of supplies between islands or across large sea areas in my country, and are also unsuitable for maritime search and rescue missions. Multi-rotor drones, on the other hand, have a better vertical takeoff and landing advantage and require no special airport conditions, making them suitable for the takeoff and landing environments of most islands. However, due to their design characteristics and lift generation methods, multi-rotor drones have shorter ranges, lower cruising speeds, and smaller payloads, failing to meet the practical needs of inter-island material transport and emergency rescue.

[0003] To address the aforementioned critical issues, and taking into account take-off and landing conditions, carrying capacity, flight speed, and mission requirements, the design of the ship and the aircraft were integrated. The aircraft's airframe structure, overall aerodynamic layout, power system, and control system were redesigned to achieve water surface take-off and landing (facilitating island material delivery, maritime emergency rescue, and other stationing needs), effectiveness (higher flight speed), and high lift (ground effect flight can significantly increase lift). It adapts to the requirements of sea and water surface take-off and landing, and has the combined advantages of the large payload of ships and the speed of aircraft.

[0004] The technical problems of the utility model are to realize the following key problems: (1) how to realize the heavy load transportation capacity of the aircraft under limited geometric size; (2) how to comprehensively improve the lift characteristics and time characteristics of the aircraft; (3) how to realize the comprehensive design of the structural strength, take-off and landing stability and power arrangement of the aircraft caused by heavy load. The effective solution to the above three key problems will realize the efficient transportation of heavy and important materials between islands and realize the disaster emergency rescue in water area such as sea and lake and the forest fire rescue. SUMMARY

[0005] The utility model wants to solve the problem, aiming at the above prior art's shortcoming, provide a kind of water take-off and landing unmanned aircraft that can realize water take-off and landing and heavy load transportation.

[0006] To solve the above problems, the utility model adopts the scheme as follows: a kind of three ship bodies segmented wing double launch heavy load water transportation unmanned aircraft, it is characterized in that, aircraft is composed of parallel three ship bodies, combined airfoil, control rudder surface system, double launch system.

[0007] The parallel three ship bodies include central main body ship body and two side ship bodies, load space is arranged in the central main body ship body and two side ship bodies.

[0008] The combined airfoil includes inner section main wing, outer section main wing, connecting flat tail and vertical tail.

[0009] The control rudder surface system includes inner section flap, outer section aileron, elevator and rudder.

[0010] The double launch system includes propeller, propulsion motor and power support frame.

[0011] The inner side of two side ship bodies is fixedly arranged at the two sides of central main body ship body by inner section main wing, and the outer side of two side ship bodies is fixedly connected with outer section main wing;Vertical tail is arranged at the tail of central main body ship body;Connecting flat tail connects two side ship bodies and vertical tail;Inner section flap is arranged at the trailing edge of inner section main wing, outer section aileron is arranged at the trailing edge of outer section main wing, elevator is arranged at the trailing edge of connecting flat tail, and rudder is arranged at the trailing edge of vertical tail;Propeller is connected with propulsion motor, and is fixedly arranged at the front end of two side ship bodies by power support frame.

[0012] Further, the three ship bodies segmented wing double launch heavy load water transportation unmanned aircraft is characterized in that, power support frame is inclinedly arranged to the inside of aircraft.

[0013] For aircraft, engine thrust line is generally closer to the axis of fuselage, but water aircraft power system is too low, and splash phenomenon occurs when taking off, which causes take-off accident, therefore, the double launch is inclinedly arranged inward, and the take-off safety and thrust line problem are considered.

[0014] Further, the three-hull segmented wing twin-engine propulsion heavy-load water transport unmanned aerial vehicle is characterized in that the length of the two side hulls is 30-85% of the length of the central main hull, and the transverse spacing is 20-70% of the length of the central main hull; the bottom of the central main hull and the two side hulls is provided with a ship bottom break, which is located at 40-60% of the distance from the head of the hull, and the central main hull and the two side hulls adopt a raised stern, and the angle of the raised stern is 5-30 degrees.

[0015] When the seaplane takes off and lands at high speed, a large amount of wave-making resistance is generated in the fuselage, especially in the rear section of the fuselage. The break and the raised stern design can effectively suppress such wave-making resistance, and at the same time, reduce the probability of the rear section of the fuselage touching the water during takeoff and landing, thereby improving safety.

[0016] Further, the three-hull segmented wing twin-engine propulsion heavy-load water transport unmanned aerial vehicle is characterized in that the inner section main wing root is located outside the central main hull, and the wing tip is connected to the two side hulls, adopting a central monoplane or an upper monoplane design, the wing root is 20-45% of the length of the central main hull from the head of the central main hull, the forward sweep angle is 0-30 degrees, the downward angle is 0-10 degrees, and the airfoil is a low-speed airfoil, a laminar airfoil or a supercritical airfoil; the outer section main wing is located outside the two side hulls, the wing root position is consistent with the wing tip position of the inner section main wing, the upward angle is 0-10 degrees, the aspect ratio is 3-10, and the airfoil is a low-speed airfoil, a laminar airfoil or a supercritical airfoil; the vertical tail is located at the tail of the central main hull, and is 0-10% of the length of the central main hull from the stern of the central main hull, and the airfoil is a symmetrical airfoil; the connected horizontal tail is located at the tail of the central main hull and the two side hulls, and is connected to the vertical tail.

[0017] Further, the three-hull segmented wing twin-engine propulsion heavy-load water transport unmanned aerial vehicle is characterized in that the length of the inner section flap is 35-65% of the span of the inner section main wing, the length of the outer section aileron is 35-65% of the span of the outer section main wing, the length of the elevator is 30-65% of the span of the connected horizontal tail, and the area of the rudder is 20-75% of the area of the vertical tail.

[0018] Further, the three-hull segmented wing twin-engine propulsion heavy-load water transport unmanned aerial vehicle is characterized in that the propulsion propeller is a 2-, 3-, 4- or 5-blade propeller; the propulsion motor is located at the top end of the power support frame; the power support frame is located on the upper side of the front end of the two side hulls, and is 5-25% of the length of the two side hulls from the head of the two side hulls, and the cross section is a symmetrical airfoil NACA0006, NACA0008 or NACA0012.

[0019] The technical effects of the utility model are as follows: the parallel three-hull is composed of a central main hull and two side hulls, is the main structure of the aircraft, provides the net buoyancy on water and the loading space of the material load, the combined airfoil is composed of two inner and outer wings, a connected horizontal tail and a vertical tail, improves the water surface sliding stability, the aircraft structure strength and the ground effect lift in low altitude flight, the control surface system is composed of an inner flap, an outer aileron, an elevator and a rudder, controls the flight attitude, the double-engine propulsion system is composed of a propulsion paddle, a propulsion motor and a power support frame, and the aircraft material, the propulsion system and the like are all waterproof materials.

[0020] (1) the parallel aircraft design method that the central main hull is main and the two side hulls are auxiliary is adopted, both of which adopt the hull type design, the fuselage structure is large, the effective load space can be improved by more than 110%, combined with the wing and the connected horizontal tail design, the structure strength is greatly improved by more than 25%.

[0021] (2) the main wing is combined with the three-hull design, the bionic structure design is adopted, the inner main wing is reversed downward and the outer main wing is reversed upward, the ground effect flight lift is effectively improved, and meanwhile, the wing area increasing design (the main wing and the connected horizontal tail wing area) is supplemented, compared with the air cruising, the lift can be improved by more than 45%.

[0022] (3) the three-hull type design not only guarantees the water surface take-off and landing stability, but also provides greater net buoyancy on water, is beneficial to improving the load performance, the power system is front-mounted on the two side hulls, can effectively improve the take-off and landing characteristics and actively control the wing upper surface flow, improves the lift characteristics. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 It is the oblique view of the unmanned aerial vehicle of the utility model.

[0024] Figure 2 It is the plan view of the unmanned aerial vehicle of the utility model.

[0025] Figure 3 It is the side view of the unmanned aerial vehicle of the utility model.

[0026] Figure 4 It is the front view of the unmanned aerial vehicle of the utility model.

[0027] In the drawing, 11 is the central main hull, 12 is the two side hulls, 13 is the ship bottom break step, 14 is the rear upturned type stern, 21 is the inner main wing, 22 is the outer main wing, 23 is the connected horizontal tail, 24 is the vertical tail, 31 is the inner flap, 32 is the outer aileron, 33 is the elevator, 34 is the rudder, 41 is the propulsion paddle, 42 is the propulsion motor, and 43 is the power support frame. DETAILED DESCRIPTION

[0028] The utility model will be further explained in detail in combination with the drawings. Example 1

[0029] The utility model provides a novel three ship body segmented wing double -jet propulsion heavy load water transport unmanned aerial vehicle, its characterized in be: novel three ship body segmented wing double -jet propulsion heavy load water transport unmanned aerial vehicle is by parallel three ship body, combined wing surface, control rudder surface system, double -jet propulsion system is composed, its wingspan is 6.6m, fuselage length is 4.9m, height is 1.08m, wing root place wing maximum chord length is 1.07m. Parallel three ship body is by central main body ship body, both sides ship body is composed, is the aerial vehicle main structure, provides water net buoyancy and material load loading space, combined wing surface is by inside and outside two section wings, connecting flat tail, vertical tail is composed, improves water surface sliding stability, aerial vehicle structure strength and low altitude flight ground effect lift, control rudder surface system is by inside section flap, outside section aileron, elevator, rudder is composed, controls flight attitude, double -jet propulsion system is by propulsion paddle, propulsion motor, power support frame.

[0030] Parallel three ship body is by central main body ship body (11), both sides ship body (12), ship bottom break stage (13), rear warping type stern (14) is composed. Central main body ship body (11) is located in the middle part of unmanned aerial vehicle, both sides ship body (12) and central main body ship body (11) design mode are similar, both sides ship body (12) are located in central main body ship body (11) both sides, both sides ship body (12) length is 30% of central main body ship body (11) length, horizontal distance is 20% of central main body ship body (11) length, ship bottom break stage (13) is located in central main body ship body (11) and both sides ship body (12) ship bottom distance ship body head 40% position, rear warping type stern (14) rear warping angle is 5 degrees.

[0031] Combined wing surface is by inside section main wing (21), outside section main wing (22), connecting flat tail (23), vertical tail (24) is composed. Inside section main wing (21) wing root is located in central main body ship body (11) outside, wing tip is connected in both sides ship body (12), adopts central single wing design, distance central main body ship body (11) head 20% central main body ship body (11) ship length, forward sweep angle is 0 degree, down angle of reflection 0 degree, airfoil is low speed airfoil;Outside section main wing (22) is located in both sides ship body (12) outside, wing root position is consistent with inside section main wing (21) wing tip position, upper angle of reflection is 0 degree, aspect ratio is 3, airfoil is low speed airfoil;Connecting flat tail (23) is located in central main body ship body (11) and both sides ship body (12) tail, and is connected with vertical tail (24), vertical tail (24) is located in central main body ship body (11) tail, distance central main body ship body (11) stern 2% central main body ship body (11) length, airfoil is symmetrical airfoil NACA0006.

[0032] The control surface system is composed of an inner segment flap (31), an outer segment aileron (32), an elevator (33), and a rudder (34). The inner segment flap (31) is located at the trailing edge of the inner segment main wing (21) and has a length of 35% of the wing span of the inner segment main wing (21). The outer segment aileron (32) is located at the trailing edge of the outer segment main wing (22) and has a length of 35% of the wing span of the outer segment main wing (22). The elevator (33) is located at the trailing edge of the connected tail (23) and has a length of 30% of the wing span of the connected tail (23). The rudder (34) is located at the trailing edge of the vertical tail (24) and has an area of 20% of the area of the vertical tail (24).

[0033] The dual-propulsion system is composed of a propulsion paddle (41), a propulsion motor (42), and a power support frame (43). The propulsion paddle (41) is connected to the propulsion motor (42). The propulsion paddle (41) is a 2-blade paddle. The propulsion motor (42) is located at the top end of the power support frame (43) and has a cross section of a symmetric airfoil NACA0006. The power support frame (43) is located on the upper side of the front end of the two side hulls (12) and is 5% of the length of the two side hulls (12) away from the head of the two side hulls (12).

[0034] The body material, propulsion system, and the like are all waterproof materials. Example 2

[0035] The difference between Example 2 and Example 1 is that:

[0036] The length of the two side hulls (12) is 40% of the length of the central main body hull (11), the lateral spacing is 30% of the length of the central main body hull (11), the ship bottom step (13) is located at the bottom of the central main body hull (11) and the two side hulls (12) 45% away from the head of the two side hulls (12), and the rear-raised ship stern (14) has a rear-raised angle of 8 degrees.

[0037] The inner segment main wing (21) adopts an upper single-wing design and is 25% of the length of the central main body hull (11) away from the head of the central main body hull (11). The forward sweep angle is 8 degrees, the lower dihedral angle is 2 degrees, and the airfoil is a laminar flow airfoil. The outer segment main wing (22) has an upper dihedral angle of 3 degrees, an aspect ratio of 5, and an airfoil of a laminar flow airfoil. The vertical tail (24) is 3% of the length of the central main body hull (11) away from the stern of the central main body hull (11) and has an airfoil of a symmetric airfoil NACA0008.

[0038] The length of the inner segment flap (31) is 45% of the wing span of the inner segment main wing (21). The length of the outer segment aileron (32) is 45% of the wing span of the outer segment main wing (22). The length of the elevator (33) is 45% of the wing span of the connected tail (23). The area of the rudder (34) is 30% of the area of the vertical tail (24).

[0039] The propeller (41) is a 3-blade propeller, the propeller motor (42) has a cross section of a symmetrical airfoil NACA0008, and the power support frame (43) is 8% of the length of the two side hulls (12) from the head of the two side hulls (12). Example 3

[0040] Example 3 differs from Example 1 in that:

[0041] The length of the two side hulls (12) is 50% of the length of the central main hull (11), the lateral spacing is 50% of the length of the central main hull (11), the bottom step (13) is located at the bottom of the central main hull (11) and the two side hulls (12) 50% from the head of the hull, and the rear-raised stern (14) has a rear-raised angle of 12 degrees.

[0042] The inner main wing (21) is designed as an upper single wing, is 35% of the length of the central main hull (11) from the head of the central main hull (11), has a forward-swept angle of 15 degrees, a downward-cambered angle of 5 degrees, and a supercritical airfoil shape; the outer main wing (22) has an upward-cambered angle of 8 degrees, an aspect ratio of 6, and a supercritical airfoil shape; and the vertical tail (24) is 7% of the length of the central main hull (11) from the stern of the central main hull (11) and has a symmetrical airfoil shape NACA0012.

[0043] The inner flap (31) has a length of 50% of the wingspan of the inner main wing (21), the outer aileron (32) has a length of 50% of the wingspan of the outer main wing (22), the elevator (33) has a length of 50% of the wingspan of the connected tail (23), and the rudder (34) has an area of 55% of the area of the vertical tail (24).

[0044] The propeller (41) is a 4-blade propeller, the propeller motor (42) has a cross section of a symmetrical airfoil NACA0012, and the power support frame (43) is 18% of the length of the two side hulls (12) from the head of the two side hulls (12). Example 4

[0045] Example 4 differs from Example 1 in that:

[0046] The length of the two side hulls (12) is 75% of the length of the central main hull (11), the lateral spacing is 65% of the length of the central main hull (11), the bottom step (13) is located at the bottom of the central main hull (11) and the two side hulls (12) 58% from the head of the hull, and the rear-raised stern (14) has a rear-raised angle of 25 degrees.

[0047] The inner main wing (21) is 45% of the length of the central body (11) from the head of the central body (11), has a forward sweep angle of 30 degrees and a downward angle of 10 degrees; the outer main wing (22) has an upward angle of 10 degrees and a span ratio of 10; the vertical tail (24) is 10% of the length of the central body (11) from the tail of the central body (11).

[0048] The inner flap (31) is 65% of the span of the inner main wing (21), the outer aileron (32) is 65% of the span of the outer main wing (22), the elevator (33) is 65% of the span of the connected tail (23), and the rudder (34) is 70% of the area of the vertical tail (24).

[0049] The propeller (41) is a 5-blade propeller, and the power support frame (43) is 25% of the length of the two side bodies (12) from the head of the two side bodies (12).

[0050] The specific embodiments described herein are merely illustrative of the spirit of the present application. Those skilled in the art to which the present application belongs can make various modifications or supplements to the described specific embodiments or use similar ways to replace them, without deviating from the spirit of the present application or exceeding the scope defined by the appended claims.

[0051] Although the terms 11 central body, 12 two side bodies, 13 bottom step, 14 rearwardly curved stern, 21 inner main wing, 22 outer main wing, 23 connected tail, 24 vertical tail, 31 inner flap, 32 outer aileron, 33 elevator, 34 rudder, 41 propeller, 42 propulsion motor, 43 power support frame are used more frequently herein, the possibility of using other terms is not excluded. The use of these terms is only to facilitate the description and explanation of the essence of the present application; any additional limitation is contrary to the spirit of the present application.

Claims

1. A tri-hull segmented wing twin jet propelled heavy lift water borne transport unmanned aerial vehicle characterized by, The aircraft is composed of a parallel three-hull, a combined wing surface, a control surface system and a double-propeller propulsion system. The parallel three-hull comprises a central main hull and two side hulls, and load spaces are arranged in the central main hull and the two side hulls. The combined wing surface comprises an inner main wing, an outer main wing, a connected tail plane and a vertical tail. The control surface system comprises an inner flap, an outer aileron, an elevator and a rudder. The double-propeller propulsion system comprises a propeller, a propulsion motor and a power support frame. The inner sides of the two side hulls are fixedly arranged on the two sides of the central main hull through the inner main wing, and the outer sides of the two side hulls are fixedly connected with the outer main wing.

2. The trihull segmented wing dual jet-propelled heavy watercraft unmanned aerial vehicle of claim 1, wherein, The vertical tail is arranged at the tail of the central main hull.

3. The trihull segmented wing dual jet-propelled heavy watercraft unmanned aerial vehicle of claim 1, wherein, The connected tail plane connects the two side hulls with the vertical tail.

4. The trihull segmented wing dual jet-propelled heavy watercraft unmanned aerial vehicle of claim 1, wherein, The propeller is connected with the propulsion motor and is fixedly arranged at the front end of the two side hulls through the power support frame.

5. The trihull segmented wing dual jet-propelled heavy watercraft unmanned aerial vehicle of claim 1, wherein, The power support frame is arranged obliquely to the inner side of the aircraft.

6. The trihull segmented wing dual jet-propelled heavy watercraft transport drone of claim 1, wherein, The length of the two side hulls is 30-85% of the length of the central main hull, and the lateral spacing is 20-70% of the length of the central main hull. The bottom of the central main hull and the two side hulls is provided with a bottom step, which is located at 40-60% from the head of the hull, and the central main hull and the two side hulls adopt a rear-raised stern with a rear-raised angle of 5-30 degrees. The wing root of the inner main wing is located on the outer side of the central main hull, and the wing tip is connected with the two side hulls. The wing root of the outer main wing is located on the outer side of the two side hulls, and the wing tip is connected with the inner main wing. The vertical tail is located at the tail of the central main hull and is connected with the connected tail plane. The length of the inner flap is 35-65% of the wingspan of the inner main wing, the length of the outer aileron is 35-65% of the wingspan of the outer main wing, the length of the elevator is 30-65% of the wingspan of the connected tail plane, and the area of the rudder is 20-75% of the area of the vertical tail. The propeller is a 2-, 3-, 4- or 5-blade propeller. The propulsion motor is located at the top end of the power support frame. The power support frame is located on the upper side of the front end of the two side hulls and is 5-25% of the length of the two side hulls from the head of the two side hulls. The cross section of the power support frame is a symmetrical airfoil NACA0006, NACA0008 or NACA0012.

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