CN215851829U - Ship body type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle - Google Patents

Abstract

The utility model discloses a hull type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle which comprises a hull type body structure, a plurality of sections of wings, a tail wing part and a double-power system, wherein the hull type body structure provides net buoyancy of the unmanned aerial vehicle staying on the water surface and power characteristics of the unmanned aerial vehicle during high-speed take-off and landing on the water surface, the plurality of sections of wings are used for generating lift force during ground effect or non-ground effect flight, the double-power system provides thrust and partial vector control, and the tail wing part realizes flight stability, course and pitching control performance. The high-speed stable gliding on the water surface, the flying take-off and landing and the water surface ground effect flying can be realized, the high-lift-force performance is realized, the load-carrying performance is excellent, and the high-lift-force aircraft has high potential application in water surface material throwing, water surface long-distance logistics transportation, armed support and the like.

Description

Ship body type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle

Technical Field

The utility model relates to a water surface take-off and landing ground effect unmanned aerial vehicle, in particular to a hull type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle.

Background

China has wide river, lake and ocean water areas, for land, the taking off and landing of lake surfaces and water surfaces can save a large amount of investment cost, and has the advantages of being suitable for local conditions, the taking off and landing of sea surfaces is also an important way for future logistics and transportation, and meanwhile, the taking off and landing on water also has great military application value. Researches and monitoring such as river basin ecological protection, water quality and water resource monitoring, ecological evolution rules of rivers, lakes, sea fishes, forest fire prevention and the like have great requirements on the water surface take-off and landing unmanned aerial vehicle on voyage time, voyage, load, take-off and landing performance and the like; meanwhile, the water logistics transportation, the material transportation, the coastline supervision, the water disaster emergency rescue and the like also provide higher requirements for the load, the flight speed, the adaptability and the like of the unmanned aerial vehicle. For realizing above market demand, from the unmanned aerial vehicle design, unmanned aerial vehicle global design, wing structure, fuselage design etc. have important influence to the surface of water take off and land, simultaneously, because the surface of water slides at a high speed, anti unrestrained, the long-term a great deal of requirements of surface of water that reside, all put forward great requirement to unmanned aerial vehicle's surface of water dynamic performance, high-speed stability and maneuverability of sliding. In order to solve the application problems, the utility model provides a hull type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle, which has the advantages that the comprehensive design of a hull type fuselage and multi-section wings is adopted to greatly improve the lift performance when taking the water surface take-off and landing, water surface sliding and air flight, particularly the high lift problem during ground effect flight, meanwhile, the high-performance ground effect unmanned aerial vehicle has high ground effect flight stability and maneuverability, and has great potential application value in water surface logistics transportation, water surface emergency rescue, water resource ecological monitoring, landing operation and the like.

For example, patent CN201821872530.5 discloses a tail boom type water unmanned aerial vehicle, which includes a fuselage, wings installed above the fuselage and extending along two sides of the central axis of the fuselage, an electronic pod installed below the front part of the fuselage, a propeller engine installed at the tail part of the fuselage, a fairing fixed on the fuselage, a tail boom connected to the fairing, an empennage connected to the tail boom, and a buoy connected below the fuselage and extending obliquely downward along two sides of the central axis. The patent does not describe the general layout and wing structure of the unmanned aerial vehicle, and the most common design is still adopted in the aspects of dynamic stability and control of high-speed gliding on the water surface.

The technical problem of the utility model is that the current water unmanned aerial vehicle has the following key problems: how to realize dynamic stability and control of high-speed sliding on the water surface; (2) in order to improve the lift performance of the unmanned aerial vehicle, how to design the overall layout and wing structure layout of the unmanned aerial vehicle; (3) in order to improve the lift force and the transportation performance, how to combine the characteristics of high-speed sliding on the water surface and the overall design of an unmanned aerial vehicle to realize the ground effect flight on the water surface. All are the important key problems of this type of unmanned aerial vehicle design.

Disclosure of Invention

The utility model aims to solve the problem that the ship hull type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle which improves the lift performance and the transportation performance of the unmanned aerial vehicle, has stable dynamics and can realize low-efficiency flight on the water surface is provided aiming at the defects in the prior art.

In order to solve the problems, the utility model adopts the following scheme: a ship-type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle is characterized in that the ship-type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle consists of a ship-type body structure, a plurality of sections of wings, an empennage part and a double power system; the multiple sections of wings are symmetrically arranged on two sides of the hull type machine body structure and are positioned in the middle of the hull type machine body structure; the empennage part is fixedly arranged at the tail part of the hull type machine body structure; the double-engine power systems are symmetrically arranged on the multiple sections of wings and are positioned on two sides of the hull type engine body structure; the hull type engine body structure provides the net buoyancy of the unmanned aerial vehicle staying on the water surface and the dynamic characteristics of the unmanned aerial vehicle during high-speed take-off and landing on the water surface; the multi-section wings are used for generating lift force during ground effect or non-ground effect flight; the double-engine power system is used for providing thrust and partial vector control; the empennage part is used for realizing flight stability, course and pitching operation performance.

Further, according to the design scheme, the ship-type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle is characterized in that the ship-type body structure consists of an upper streamline-shaped body, a front-section ship-type body and a rear-section ship-type body; the upper streamline fuselage is arranged above the front-section hull type fuselage and the rear-section hull type fuselage, is positioned above the water surface, and is provided with a loading space for unmanned aerial vehicle load, a power battery, a GPS and a circuit system; the front-section hull type fuselage extends to the nose before the step is broken; the rear-section hull type fuselage extends to the tail of the fuselage after the step is broken; the hull type machine body structures are all made of waterproof materials and are sealed by contacting with the water surface.

Further, according to the hull type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle of the design scheme, the unmanned aerial vehicle is characterized in that the tail part is a T-shaped tail wing structure consisting of a vertical tail, a rudder, a horizontal tail and an elevator; the vertical fin is arranged above the tail part of the hull type machine body structure; the rudder is arranged at the rear edge of the vertical tail; the horizontal tail is arranged on the upper end surface of the vertical tail; the sweepback angle of the front edge of the horizontal tail is 0-30 degrees; the elevator is arranged at the rear edge of the horizontal tail.

Further, according to the design scheme, the ship body type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle is characterized in that the multi-section wing is composed of an inner wing, a middle wing, a wing floating barrel, an outer wing, a wing hydrofoil and an aileron; the inner wings are symmetrically connected with two sides of the upper streamline fuselage; the middle wing is connected with the inner wing; the wing floating barrels are hull type floating barrels and are connected with the middle wings; the external wings are connected with the wing floating barrels; the wing hydrofoil is connected with the wing floating barrel and is positioned at the inner side of the wing floating barrel and inclines inwards; the ailerons are arranged at the trailing edge of the outer wing.

Further, according to the design scheme, the ship body type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle is characterized in that the inner wings are connected to two sides of the upper streamlined body, the span length is 20% -25% of the total span length of the multi-section wings, the upper single-wing layout is adopted, the inner wings are located in the circumferential middle of the ship body type body structure, the installation angle is 2-5 degrees, the sweepback angle is 0 degree, and the wing type is a low-speed wing type or a laminar flow wing type; the front edge forward sweep angle of the middle wing is 5-15 degrees, the rear edge and the inner wing are in the same straight line, the rear edge forward sweep angles are fixed angles of 30-45 degrees, the down-reflecting angle is 3-10 degrees, the spanwise length is 40% -55% of the total spanwise length of the multi-section wing, and the wing type is a low-speed wing type or a laminar flow wing type; the wing floating barrel is used for direction control during water surface sliding and is matched with the front-section hull type body and the rear-section hull type body to improve the ground effect lift force, and the wing floating barrel is made of waterproof composite materials; the external wing is positioned at the outermost end of the wing, the sweepback angle of the front edge is 25-45 degrees, the span length is 20% -30% of the total span length of the multi-section wing, the dihedral angle is 5-25 degrees, and the wing type is a low-speed wing type or a laminar flow wing type; the included angle between the hydrofoil of the wing and the horizontal plane is 40-60 degrees, the span length of the hydrofoil of the wing is 10-15% of the total span length of the multi-section wing, the wing is a laminar flow wing section or a low-speed wing section, and the hydrofoil is used for controlling the sailing stability of water surface sliding and generating lift force by high-speed water surface sliding, so that the raising and water leaving of the unmanned aerial vehicle are facilitated, the lift force improvement of the unmanned aerial vehicle during air flight is improved, and a light high-strength composite material is adopted; the chord length of the ailerons is 25% -40% of the chord length of the corresponding positions, and the ailerons are matched with each control surface of the tail part to realize the aerial attitude control of the unmanned aerial vehicle.

Further, according to the design scheme, the ship-body type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle is characterized in that the double-engine power system consists of propeller bases and propulsion propellers which are symmetrically distributed on two sides of a machine body; the propeller base is arranged above the internal wing and close to the trailing edge part, is higher than the body and can meet the requirement of the radius work of propeller blades; the propulsion propeller is arranged above the propeller base, a back-pushing power mode is adopted, propeller blades adopt 2, 3 and 4 blades, and the propeller blades are made of light high-strength water discharge composite materials.

Further, according to above-mentioned design scheme hull formula multistage wing surface of water take off and land imitate unmanned aerial vehicle, its characterized in that, the wing hydrofoil adopts the glass fiber material.

Further, according to above-mentioned design scheme hull formula multistage wing surface of water ground effect unmanned aerial vehicle that takes off and land, its characterized in that, the screw paddle adopts the glass fiber material.

The multi-section wing and hull type body structure in the design scheme is matched with the upper tail wing part and the double-engine power system, so that the dynamic stability and control of high-speed sliding on the water surface can be realized. The ship body type body structure provides net buoyancy of the unmanned aerial vehicle staying on the water surface and dynamic characteristics of the unmanned aerial vehicle when the unmanned aerial vehicle takes off and lands at a high speed on the water surface, the multiple sections of wings are used for generating lift force when the unmanned aerial vehicle flies in a ground effect or a non-ground effect, the double-engine power system provides thrust and partial vector control, and the tail wing part realizes flight stability, course and pitching control performance. The high-speed stable gliding on the water surface, the flying take-off and landing and the water surface ground effect flying can be realized, the high-lift-force performance is realized, the load-carrying performance is excellent, and the high-lift-force aircraft has high potential application in water surface material throwing, water surface long-distance logistics transportation, armed support and the like. Finally, the lift force and the transportation performance are improved through the overall layout of the hull type body structure, the multiple sections of wings and the tail wing part.

The utility model has the following technical effects: compared with the existing similar water take-off and landing unmanned aerial vehicle, the utility model has the following advantages:

(1) the multi-section wing and the multi-section different leading edge sweepback or sweepfront are provided to improve the flight performance of low altitude or ground effect flight and facilitate the realization of low speed take-off and landing performance.

(2) The high-speed sliding stability of the unmanned aerial vehicle on the water surface and the generation of the lift force of the low altitude on the water surface are improved together by adopting a hull type body, double floating barrels attached to wings and hydrofoils fixedly connected to the floating barrels;

(3) the water surface take-off and landing ground effect unmanned aerial vehicle overall layout has excellent lift characteristic and low-speed water surface take-off and landing capability, and when the ground effect flies, the lift performance is improved by 30% -35%.

Drawings

Fig. 1 is a perspective view of an unmanned aerial vehicle.

Fig. 2 is a side view of the drone.

Fig. 3 is a top view of the drone.

Fig. 4 is an owner view of the unmanned aerial vehicle.

The airplane comprises a hull type airframe structure 1, a plurality of sections of wings 2, a tail part 3, a double-engine system 4, an upper streamline fuselage 11, a front-section hull type fuselage 12, a rear-section hull type fuselage 13, an inner wing 21, a middle wing 22, a floating bucket 23, an outer wing 24, a hydrofoil 25, an aileron 26, a vertical tail 31, a rudder 32, a horizontal tail 33, a lift rudder 34, a propeller base 41 and a propeller propelling propeller 42.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

Example 1:

the utility model provides an unmanned aerial vehicle is imitated to hull formula multistage wing surface of water take off and land, unmanned aerial vehicle is imitated to hull formula multistage wing surface of water take off and land comprises hull formula organism structure 1, multistage wing 2, fin part 3, two power system 4 that send out, hull formula organism structure 1 provides the net buoyancy that unmanned aerial vehicle stayed the surface of water and the dynamic characteristic when the high-speed take off and land of surface, lift when multistage wing 2 is used for producing ground effect or non-ground effect flight, two power system 4 that send out provide thrust and partial vector control, fin part 3 realizes flight stability, course and every single move manipulation property.

The hull type airframe structure 1 is composed of an upper streamline airframe 11, a front-section hull type airframe 12 and a rear-section hull type airframe 13. Streamlined fuselage 11 in upper portion is located the surface of water more, provides loading space for unmanned aerial vehicle load, power battery, GPS, circuit system etc. and anterior segment hull formula fuselage 12 extends to the aircraft nose before the broken rank, and back end hull formula fuselage 13 extends to the fuselage afterbody after the broken rank. The fuselage airframe structure all adopts waterproof material and contacts the surface of water partly sealed.

The multi-section wing comprises an inner wing 21, a middle wing 22, a wing floating barrel 23, an outer wing 24, a wing hydrofoil 25 and an aileron 26. The inner wings 21 are connected to two sides of the upper streamline fuselage 11, the span length is 20% of the total span length of the multiple sections of wings, an upper single wing layout is adopted, the inner wings are located in the middle of the circumference of the fuselage, the installation angle is 2 degrees, the sweepback angle is 0 degree, and the wing profiles are low-speed wing profiles or laminar flow wing profiles with large thickness; the middle wing 22 is connected with the inner wing 21, the forward sweep angle of the front edge is 5 degrees, the rear edge of the front edge and the inner wing 21 are in the same straight line, the forward sweep angles of the rear edge are all fixed angles within 30 degrees, the down-camber angle is 3 degrees, the spanwise length is 50 percent of the total spanwise length of the plurality of sections of wings, and the wing type is a low-speed wing type or a laminar flow wing type; the wing floating barrels 23 are hull type floating barrels, are used for direction control during water surface sliding and are matched with the front-segment hull type machine body 12 and the rear-segment hull type machine body 13 to improve the ground effect lift force, and are made of waterproof composite materials; the outer wing 24 is positioned at the outermost end of the wing, the sweepback angle of the front edge is 25 degrees, the span length is 30 percent of the total span length of the multi-section wing, the dihedral angle is 5 degrees, and the wing profile is a low-speed wing profile or a laminar flow wing profile; the wing hydrofoil 25 is connected with the wing floating barrel 23 and is positioned at the inner side of the wing floating barrel to incline inwards, the included angle between the wing hydrofoil 25 and the horizontal plane is 40 degrees, the hydrofoil span length is 10 percent of the total span length of a plurality of sections of wings, and the wing section is a laminar flow wing section or a low-speed wing section and is used for controlling the sailing stability of water surface sliding and generating lift force by high-speed water surface sliding, so that the unmanned aerial vehicle can lift head and leave water, the lift force of the unmanned aerial vehicle during air flight is improved, and glass fiber or other light high-strength composite materials are adopted; the ailerons 26 are positioned at the rear edge of the external wing 24, the chord length is 25 percent of the chord length at the corresponding position, and the ailerons are matched with each control surface of the empennage to realize the aerial attitude control of the unmanned aerial vehicle.

The tail part is a T-shaped tail structure consisting of a vertical tail 31, a rudder 32, a horizontal tail 33 and an elevator 34. The vertical tail 31 is positioned at the tail part of the airplane body, the rudder 32 is positioned at the rear edge of the vertical tail, the horizontal tail 33 is positioned on the upper end surface of the vertical tail 31, the sweepback angle of the front edge of the horizontal tail 33 is 10 degrees, and the elevator 34 is positioned at the rear edge of the horizontal tail.

The double-engine power system consists of propeller bases 41 and propulsion propellers 42 which are symmetrically distributed on two sides of the machine body. The propeller base 41 is positioned on the part of the inner wing 21 close to the trailing edge, the height of the propeller base is slightly higher than that of the airplane body, and the propeller base can meet the requirement of propeller blade radius work; the propulsion propeller 42 is arranged above the propeller base 41 and adopts a back-push type power mode, and propeller blades can adopt 2-blade propellers made of glass fiber composite materials.

Example 2:

the utility model provides an unmanned aerial vehicle is imitated to hull formula multistage wing surface of water take off and land, unmanned aerial vehicle is imitated to hull formula multistage wing surface of water take off and land comprises hull formula organism structure 1, multistage wing 2, fin part 3, two power system 4 that send out, hull formula organism structure 1 provides the net buoyancy that unmanned aerial vehicle stayed the surface of water and the dynamic characteristic when the high-speed take off and land of surface, lift when multistage wing 2 is used for producing ground effect or non-ground effect flight, two power system 4 that send out provide thrust and partial vector control, fin part 3 realizes flight stability, course and every single move manipulation property.

The hull type airframe structure 1 is composed of an upper streamline airframe 11, a front-section hull type airframe 12 and a rear-section hull type airframe 13. Streamlined fuselage 11 in upper portion is located the surface of water more, provides loading space for unmanned aerial vehicle load, power battery, GPS, circuit system etc. and anterior segment hull formula fuselage 12 extends to the aircraft nose before the broken rank, and back end hull formula fuselage 13 extends to the fuselage afterbody after the broken rank. The fuselage airframe structure all adopts waterproof material and contacts the surface of water partly sealed.

The multi-section wing 2 consists of an inner wing 21, a middle wing 22, a wing floating barrel 23, an outer wing 24, a wing hydrofoil 25 and an aileron 26. The inner wings 21 are connected to two sides of the upper streamline fuselage 11, the span length is 25% of the total span length of the multiple sections of wings, an upper single wing layout is adopted, the inner wings are located in the middle of the circumference of the fuselage, the installation angle is 3 degrees, the sweepback angle is 0 degree, and the wing profiles are low-speed wing profiles or laminar wing profiles with large thickness; the middle wing 22 is connected with the inner wing 21, the forward sweep angle of the front edge is 10 degrees, the rear edge of the front edge and the inner wing 21 are in the same straight line, the forward sweep angles of the rear edge are fixed angles within 35 degrees, the down-turning angle is 5 degrees, the spanwise length is 45 percent of the total spanwise length of the plurality of sections of wings, and the wing type is a low-speed wing type or a laminar flow wing type; the wing floating barrels 23 are hull type floating barrels, are used for direction control during water surface sliding and are matched with the front-segment hull type machine body 12 and the rear-segment hull type machine body 13 to improve the ground effect lift force, and are made of waterproof composite materials; the outer wing 24 is positioned at the outermost end of the wing, the sweepback angle of the front edge is 30 degrees, the span length is 30 percent of the total span length of the multi-section wing, the dihedral angle is 10 degrees, and the wing profile is a low-speed wing profile or a laminar flow wing profile; the wing hydrofoil 25 is connected with the wing floating barrel 23 and is positioned on the inner side of the wing floating barrel to incline inwards, the included angle between the wing hydrofoil 25 and the horizontal plane is 45 degrees, the hydrofoil span length is 12 percent of the total span length of the multiple sections of wings, and the wing section is a laminar flow wing section or a low-speed wing section and is used for controlling the sailing stability of water surface sliding and generating lift force by high-speed water surface sliding, so that the unmanned aerial vehicle can lift head and leave water, the lift force of the unmanned aerial vehicle during air flight is improved, and glass fiber or other light high-strength composite materials are adopted; the ailerons 26 are positioned at the rear edge of the external wing 24, the chord length is 30 percent of the chord length at the corresponding position, and the ailerons are matched with each control surface of the empennage to realize the aerial attitude control of the unmanned aerial vehicle.

The tail part 3 is a T-shaped tail structure consisting of a vertical tail 31, a rudder 32, a horizontal tail 33 and an elevator 34. The vertical tail 31 is positioned at the tail part of the airplane body, the rudder 32 is positioned at the rear edge of the vertical tail, the horizontal tail 33 is positioned on the upper end surface of the vertical tail 31, the sweepback angle of the front edge of the horizontal tail 33 is 15 degrees, and the elevator 34 is positioned at the rear edge of the horizontal tail.

The double-engine power system 4 is composed of propeller bases 41 and propulsion propellers 42 which are symmetrically distributed on two sides of the machine body. The propeller base 41 is positioned on the part of the inner wing 21 close to the trailing edge, the height of the propeller base is slightly higher than that of the airplane body, and the propeller base can meet the requirement of propeller blade radius work; the propulsion propeller 42 is arranged above the propeller base 41 and adopts a back-push type power mode, and the propeller blades can adopt 3-blade propeller which is made of glass fiber or other light high-strength water-discharging composite materials.

Example 3:

the utility model provides an unmanned aerial vehicle is imitated to hull formula multistage wing surface of water take off and land, unmanned aerial vehicle is imitated to hull formula multistage wing surface of water take off and land comprises hull formula organism structure 1, multistage wing 2, fin part 3, two power system 4 that send out, hull formula organism structure 1 provides the net buoyancy that unmanned aerial vehicle stayed the surface of water and the dynamic characteristic when the high-speed take off and land of surface, lift when multistage wing 2 is used for producing ground effect or non-ground effect flight, two power system 4 that send out provide thrust and partial vector control, fin part 3 realizes flight stability, course and every single move manipulation property.

The hull type airframe structure 1 is composed of an upper streamline airframe 11, a front-section hull type airframe 12 and a rear-section hull type airframe 13. Streamlined fuselage 11 in upper portion is located the surface of water more, provides loading space for unmanned aerial vehicle load, power battery, GPS, circuit system etc. and anterior segment hull formula fuselage 12 extends to the aircraft nose before the broken rank, and back end hull formula fuselage 13 extends to the fuselage afterbody after the broken rank. The fuselage airframe structure all adopts waterproof material and contacts the surface of water partly sealed.

The multi-section wing 2 consists of an inner wing 21, a middle wing 22, a wing floating barrel 23, an outer wing 24, a wing hydrofoil 25 and an aileron 26. The inner wings 21 are connected to two sides of the upper streamline fuselage 11, the span length is 20% of the total span length of the multiple sections of wings, an upper single wing layout is adopted, the inner wings are located in the middle of the circumference of the fuselage, the installation angle is 5 degrees, the sweepback angle is 0 degree, and the wing profiles are low-speed wing profiles or laminar flow wing profiles with large thickness; the middle wing 22 is connected with the inner wing 21, the forward sweep angle of the leading edge is 15 degrees, the trailing edge and the inner wing 21 are in the same straight line, the forward sweep angles of the trailing edge are fixed angles within 40 degrees, the down-camber angle is 10 degrees, the spanwise length is 55 percent of the total spanwise length of the plurality of sections of wings, and the wing type is a low-speed wing type or a laminar flow wing type; the wing floating barrels 23 are hull type floating barrels, are used for direction control during water surface sliding and are matched with the front-segment hull type machine body 12 and the rear-segment hull type machine body 13 to improve the ground effect lift force, and are made of waterproof composite materials; the outer wing 24 is positioned at the outermost end of the wing, the sweepback angle of the front edge is 40 degrees, the span length is 25 percent of the total span length of the multi-section wing, the dihedral angle is 20 degrees, and the wing profile is a low-speed wing profile or a laminar flow wing profile; the wing hydrofoil 25 is connected with the wing floating barrel 23 and is positioned on the inner side of the wing floating barrel to tilt inwards, the included angle between the wing hydrofoil and the horizontal plane is 50 degrees, the hydrofoil span length is 15 percent of the total span length of a plurality of sections of wings, and the wing section is a laminar flow wing section or a low-speed wing section and is used for controlling the sailing stability of water surface sliding and generating lift force by high-speed water surface sliding, so that the unmanned aerial vehicle can lift head and leave water, the lift force of the unmanned aerial vehicle during air flight is improved, and glass fiber or other light high-strength composite materials are adopted; the ailerons 26 are positioned at the rear edge of the external wing 24, the chord length is 35 percent of the chord length at the corresponding position, and the ailerons are matched with each control surface of the empennage to realize the aerial attitude control of the unmanned aerial vehicle.

The tail part 3 is a T-shaped tail structure consisting of a vertical tail 31, a rudder 32, a horizontal tail 33 and an elevator 34. The vertical tail 31 is positioned at the tail part of the airplane body, the rudder 32 is positioned at the rear edge of the vertical tail, the horizontal tail 33 is positioned on the upper end surface of the vertical tail 31, the sweepback angle of the front edge of the horizontal tail 33 is 25 degrees, and the elevator 34 is positioned at the rear edge of the horizontal tail.

The double-engine power system 4 is composed of propeller bases 41 and propulsion propellers 42 which are symmetrically distributed on two sides of the machine body. The propeller base 41 is positioned on the part of the inner wing 21 close to the trailing edge, the height of the propeller base is slightly higher than that of the airplane body, and the propeller base can meet the requirement of propeller blade radius work; the propulsion propeller 42 is arranged above the propeller base 41 and adopts a back-push type power mode, and 4 propellers can be adopted as propeller blades and are made of glass fiber or other light high-strength water-discharging composite materials.

The specific embodiments described herein are merely illustrative of the spirit of the utility model. Various modifications or additions may be made to the described embodiments or alternatives may be employed by those skilled in the art without departing from the spirit or ambit of the utility model as defined in the appended claims.

Although the terms upper faired fuselage 11, forward hull fuselage 12, aft hull fuselage 13, inner wing 21, middle wing 22, wing pontoon 23, outer wing 24, wing hydrofoil 25, aileron 26, vertical tail 31, rudder 32, horizontal tail 33, elevator 34, propeller base 41, propeller 42, etc. are used more herein, the possibility of using other terms is not excluded. These terms are used merely to more conveniently describe and explain the nature of the present invention; they are to be construed as being without limitation to any additional limitations that may be imposed by the spirit of the present invention.

Claims (8)

1. A ship-type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle is characterized in that the ship-type multi-section wing water surface take-off and landing ground effect unmanned aerial vehicle consists of a ship-type body structure (1), a plurality of sections of wings (2), an empennage part (3) and a double-engine power system (4); the multiple sections of wings (2) are symmetrically arranged on two sides of the hull type engine body structure (1) and are positioned in the middle of the hull type engine body structure (1); the empennage part (3) is fixedly arranged at the tail part of the hull type machine body structure (1); the double-engine power systems (4) are symmetrically arranged on the multiple sections of wings (2) and are positioned on two sides of the hull type engine body structure (1); the hull type engine body structure (1) provides the net buoyancy of the unmanned aerial vehicle staying on the water surface and the dynamic characteristics of the unmanned aerial vehicle when the unmanned aerial vehicle takes off and lands at high speed; the multi-section wings (2) are used for generating lift force during ground effect or non-ground effect flight; the double-engine power system (4) is used for providing thrust and partial vector control; the empennage part (3) is used for realizing flight stability, course and pitching operation performance.

2. The hull type multi-segment wing water surface take-off and landing WIG (unmanned aerial vehicle) according to claim 1, wherein the hull type airframe structure (1) is composed of an upper streamlined fuselage (11), a front segment hull type fuselage (12) and a rear segment hull type fuselage (13); the upper streamline fuselage (11) is arranged above the front-section hull-type fuselage (12) and the rear-section hull-type fuselage (13), is positioned above the water surface, and is provided with a loading space for unmanned aerial vehicle loads, a power battery, a GPS (global positioning system) and a circuit system; the forepart hull type fuselage (12) extends to the nose before the step is broken; the rear-section hull-type fuselage (13) extends to the tail of the fuselage after the step is broken; the ship body type machine body structures (1) are all made of waterproof materials and are sealed by contacting with the water surface.

3. The hull type multi-segment wing surface taking off and landing WIV (unmanned aerial vehicle) of claim 1, wherein the tail part (3) is a T-shaped tail structure composed of a vertical tail (31), a rudder (32), a horizontal tail (33) and an elevator (34); the vertical fin (31) is arranged above the tail part of the hull type machine body structure (1); the rudder (32) is arranged at the rear edge of the vertical tail; the horizontal tail (33) is arranged on the upper end surface of the vertical tail (31); the sweepback angle of the front edge of the horizontal tail (33) is 0-30 degrees; the elevator (34) is arranged at the rear edge of the horizontal tail.

4. The hull type multi-segment wing water surface take-off and landing ground effect unmanned aerial vehicle of claim 2, wherein the multi-segment wing (2) is composed of an inner wing (21), a middle wing (22), a wing float bucket (23), an outer wing (24), a wing hydrofoil (25) and an aileron (26); the internal wings are symmetrically connected with two sides of the upper streamline fuselage (11); the middle wing (22) is connected with the inner wing (21); the wing floating barrels (23) are hull type floating barrels and are connected with the middle wing (22); the external wing (24) is connected with the wing floating barrel (23); the wing hydrofoil (25) is connected with the wing floating barrel (23) and is positioned at the inner side of the wing floating barrel and inclines inwards; the ailerons (26) are disposed at the trailing edge of the outer wing (24).

5. The hull type multi-segment wing water surface take-off and landing ground effect unmanned aerial vehicle of claim 4, wherein the inner wings (21) are connected to two sides of the upper streamlined fuselage (11), the span length is 20% -25% of the total span length of the multi-segment wings (2), an upper single wing layout is adopted, the inner wings are located in the middle of the circumference of the hull type airframe structure (1), the installation angle is 2-5 degrees, the sweepback angle is 0 degree, and the wing profiles are low-speed wing profiles or laminar flow wing profiles; the leading edge forward sweep angle of the middle wing (22) is 5-15 degrees, the trailing edge and the inner wing (21) are the same straight line, the trailing edge forward sweep angles are fixed angles of 30-45 degrees, the down-turning angle is 3-10 degrees, the spanwise length is 40% -55% of the total spanwise length of the multi-section wing (2), and the wing profile is a low-speed wing profile or a laminar flow wing profile; the wing floating barrels (23) are used for controlling the direction when the wing floating barrels slide on the water and are matched with the front-section hull type machine body (12) and the rear-section hull type machine body (13) to improve the ground effect lift force, and the wing floating barrels are made of waterproof composite materials; the outer wing (24) is positioned at the outermost end of the wing, the sweepback angle of the front edge is 25-45 degrees, the span length is 20-30 percent of the total span length of the multi-section wing (2), the dihedral angle is 5-25 degrees, and the wing type is a low-speed wing type or a laminar flow wing type; the included angle between the wing hydrofoil (25) and the horizontal plane is 40-60 degrees, the span length of the wing hydrofoil (25) is 10-15% of the total span length of the multi-section wing (2), the wing section is a laminar flow wing section or a low-speed wing section, and is used for controlling the sailing stability of water surface sliding and generating lift force by high-speed water surface sliding, so that the unmanned aerial vehicle can lift and leave water easily, the lift force of the unmanned aerial vehicle during air flight is improved, and a light high-strength composite material is adopted; the chord length of the ailerons (26) is 25-40% of the chord length of the corresponding positions, and the ailerons are matched with each control surface of the tail part (3) to realize the aerial attitude control of the unmanned aerial vehicle.

6. The hull type multi-segment wing water surface take-off and landing WIG (unmanned aerial vehicle) as claimed in claim 4, wherein the dual-engine power system (4) is composed of propeller bases (41) and propulsion propellers (42) which are symmetrically distributed on two sides of the fuselage; the propeller base (41) is arranged above the inner wing (21) and close to the rear edge part, is higher than the fuselage and can meet the requirement of the radial work of propeller blades; the propulsion propeller (42) is arranged above the propeller base (41) and adopts a back-push type power mode, propeller blades adopt 2, 3 and 4 blades, and the propeller blades are made of light high-strength water discharge composite materials.

7. The hull type multi-segment wing surface take-off and landing WIG (unmanned aerial vehicle) of claim 4, wherein the wing hydrofoils (25) are made of glass fiber materials.

8. The hull-type multi-segment wing surface take-off and landing WIG unmanned aerial vehicle of claim 6, wherein the propeller blades are made of glass fiber materials.

Images