CN214451787U - Double-fuselage compound wing layout multistage propulsion unmanned aerial vehicle - Google Patents
Double-fuselage compound wing layout multistage propulsion unmanned aerial vehicle Download PDFInfo
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Abstract
The utility model discloses a multistage unmanned aerial vehicle that impels of double fuselage composite wing overall arrangement, include: the double-fuselage structure is used for a main bearing structure, load loading, airborne system installation and the like, the composite wing structure generates main lift force in a flat flight state and carries effective load according to actual requirements, the multi-stage propulsion system consists of three groups of propeller systems and is used for functions of vertical take-off and landing, staged propulsion, flying speed adjustment and the like, the flight performance is optimized, and the composite rudder system realizes unmanned aerial vehicle flight attitude control. The utility model discloses can realize fixed wing unmanned aerial vehicle VTOL, the rolloff take off and land and perpendicularly to the stable switching that flies to the tie to have tertiary flat flying speed, flight performance is outstanding, and the load capacity is strong, and double fuselage composite wing overall arrangement has high-efficient advantages such as having fused big loading space, high lift, high structural strength, has important using value in aspects such as military reconnaissance, information collection, commodity circulation transportation, goods and materials input.
Description
Technical Field
The utility model relates to a compound wing unmanned aerial vehicle especially relates to a two fuselage compound wing overall arrangement multistage propulsion unmanned aerial vehicle.
Background
The unmanned aerial vehicle has great application value in directions such as military reconnaissance, information collection, logistics transportation, material and material input, and different application scenes put forward higher requirements on unmanned aerial vehicle take-off and landing conditions, flight speed, load size, flight safety, stability and the like. Generally, the fixed-wing unmanned aerial vehicle has great advantages in load, flight speed and range, but has certain requirements on take-off and landing conditions such as airport pavement, width and the like, so that smooth take-off and landing under poor conditions are difficult to meet, and meanwhile, the fixed-wing unmanned aerial vehicle has high requirements on large load, high economy, high speed and the like required by part of markets. Aiming at the market demands, the unmanned aerial vehicle has the technical goals of realizing vertical take-off and landing or short-distance take-off and landing, high lift force, switchable flight speed and the like, and is one of the important development directions. In order to realize vertical take-off and landing or short-distance take-off and landing, a fixed wing unmanned aerial vehicle generally needs to be realized by combining a multi-rotor design, but the conventional design method is easy to cause load reduction, unstable vertical and plane flight processes, and dead weight of a multi-rotor part is increased in the flight process, so that the flight performance is reduced; in order to meet the high lifting performance, a high-aspect-ratio wing can be adopted, but the high-aspect-ratio wing often brings about the constraint problems of wing structural strength and take-off and landing conditions, and meanwhile, the contradiction between the optimization of load space and flight performance is also an important problem to be solved; due to power limitation, the cruising performance of various speeds of a common fixed-wing unmanned aerial vehicle is difficult to realize, and the load-carrying performance, the time-of-flight limitation and the like of the unmanned aerial vehicle are influenced. In order to solve the problems, the double-body composite wing layout multistage propulsion unmanned aerial vehicle is provided to solve the power system problem, the high-lift problem, the multistage speed cruise performance problem and the like in the vertical and level flight states.
The technical problem of the utility model lies in following several key problems that current heavy load fixed wing unmanned aerial vehicle exists: (1) how to effectively utilize the multi-stage propulsion propeller to realize the functions of vertical take-off and landing and horizontal flight, simultaneously eliminate various weight problems caused by the vertical take-off and landing propeller, and solve the problem of aerodynamic stability of the vertical take-off and landing propeller to the horizontal flight state; (2) how to further improve the lift force of the fixed-wing unmanned aerial vehicle, increase the load, and simultaneously not reduce the flight performance and the structural performance of the unmanned aerial vehicle, the utility model improves the overall arrangement of the double-body and composite wing; (3) how to coordinate the contradiction between the take-off and landing conditions, the flight speed and the load-carrying performance, and the problem that the cruising speed of the conventional unmanned aerial vehicle is fixed is solved.
Disclosure of Invention
The utility model aims to solve the problem that to the shortcoming among the above-mentioned prior art, a multistage propulsion unmanned aerial vehicle who possesses double-fuselage composite wing overall arrangement is provided.
In order to solve the above problem, the utility model discloses a scheme as follows: the utility model provides a two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle, its characterized in that, two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle includes: double-fuselage structure, compound wing structure, multistage propulsion system, compound rudder face system.
The double-body structure consists of double bodies, a support column type undercarriage and double vertical tails which are symmetrically arranged in parallel; the strut type undercarriage is arranged at the bottom of the double-body; the double vertical tails are arranged at the rear ends of the double bodies.
The double-fuselage structure is used for a main bearing structure, load loading, airborne system installation and the like, the composite wing structure generates main lift force in a flat flight state and carries effective loads according to actual requirements, the multi-stage propulsion system is composed of three groups of propeller systems and used for functions of vertical take-off and landing, staged propulsion, adjustment of flying speed and the like, the flying performance is optimized, and the composite control surface system realizes unmanned aerial vehicle flying attitude control.
The composite wing structure consists of a front duck wing, a main wing, a rear wing, a horizontal tail, a wingtip winglet of the main wing and a horizontal tail wingknife; the front duck wing is arranged at the head position of the double-body; the main wing is fixedly arranged in the middle of the double bodies; the left wing tip and the right wing tip of the rear wing are connected to the main wing, and the other end of the rear wing is fixedly connected with the upper parts of the double vertical tails and connected with the horizontal tail wing tips; the horizontal tail is fixedly connected with the upper ends of the double vertical tails; the winglet is arranged on the outer side of the wing tip of the main wing; the horizontal tail winged knife is arranged in the middle of the upper wing surface of the horizontal tail.
The horizontal tail is fixedly connected with the upper ends of the double vertical tails, and the symmetrical wing type is adopted to realize the net stability in the longitudinal direction; the winglet of the wing tip of the main wing is positioned outside the wing tip of the main wing, and can adopt a combination of an upper reverse type, a lower reverse type and an upper reverse type, so that the induced resistance of the main wing is reduced, and the flight performance is improved; the horizontal tail winged knife is positioned in the middle of the upper wing surface of the horizontal tail, so that the lateral interference of surface flow is reduced.
The multi-stage propulsion system consists of a first-stage propulsion propeller, a second-stage propulsion propeller and a third-stage propulsion propeller; the first-stage propulsion propeller is arranged at the front edge of the connecting point of the main wing and the rear wing; the secondary propulsion propeller is arranged outside a connecting point of the front duck wing and the double-fuselage and is positioned at the rear edge of the front duck wing; the three-stage propulsion propeller is arranged at the junction of the horizontal tail and the rear wing.
The first-stage propulsion propeller is positioned at the front edge of the connecting point of the main wing and the rear wing; the secondary propulsion propeller is positioned outside the connecting point of the front canard wing and the aircraft body and at the rear edge of the front canard wing, so that vertical and horizontal tilting can be realized; the three-stage propulsion propeller is positioned at the intersection of the horizontal tail and the rear wing, and vertical and horizontal tilting switching can be realized. Multistage propulsion system can realize unmanned aerial vehicle's VTOL, different cruise speed flight switch, the wheeled take-off and land of short distance, realizes VTOL when adopting one-level, tertiary perpendicular, changes the propulsion step by step after the flat flight, improves flying speed, adopts one-level, second grade, tertiary different flat speed that flies to switch, and when wheeled take-off and land, adopts one-level, tertiary perpendicular lift that provides, the reduction distance of taking off and land. The first-stage propulsion propeller, the second-stage propulsion propeller and the third-stage propulsion propeller can be selected from 2-blade, 3-blade and 4-blade blades and are made of wood or composite materials.
The composite control surface system comprises a canard control surface, an aileron, a flap, a rear wing control surface and a horizontal tail elevator; the duck wing control surface is arranged on the rear edge of the outer side of the front duck wing; the ailerons are arranged at the rear edge of the outer end of the main wing; the flap is arranged on the trailing edge of one side, close to the double-body, of the main wing; the rear wing rudder surface is arranged on the rear edge of the rear wing close to one side of the double vertical tails; the horizontal tail elevator is arranged at the rear edge of the horizontal tail.
The duck wing control surface is positioned at the rear edge of the outer side of the front duck wing and is used for the auxiliary operation of the maneuverability of the unmanned aerial vehicle; the ailerons are positioned at the rear edge of the outer end of the main wing and used for the transverse control of the unmanned aerial vehicle; the flap is positioned at the rear edge of the main wing close to one side of the double-fuselage and is used for increasing lift force during takeoff; the rear wing rudder surface is positioned at the rear edge of the rear wing close to one side of the double vertical tails and is used for course control; the horizontal tail elevating rudder is positioned at the rear edge of the horizontal tail, so that the pitching operation of the unmanned aerial vehicle is realized.
Further, according to the design scheme, the double-fuselage compound wing layout multistage propulsion unmanned aerial vehicle is characterized in that the front duck wing adopts any one of a low-speed wing profile, a laminar flow wing profile and a supercritical wing profile, and the spread length of the front duck wing is 55% -70% of the span length of the main engine.
Further, according to the design scheme, the double-body composite wing layout multistage propulsion unmanned aerial vehicle is characterized in that the main wing is arranged at a position 55% -60% of the length of the double-body machine head; the main wing adopts any one of a low-speed wing profile, a laminar flow wing profile and a supercritical wing profile, the sweepback angle of the front edge of the main wing is 0-20 degrees, and the sweepback angle of the rear edge of the main wing is 0-15 degrees.
Further, according to the design scheme, the double-fuselage compound wing layout multistage propulsion unmanned aerial vehicle is characterized in that the left wing tip and the right wing tip of the rear wing are connected to the positions 8% -18% away from the wing tip of the main wing in the extending direction; the rear wing adopts a laminar flow wing profile or a supercritical wing profile.
Further, according to above-mentioned design the multistage unmanned aerial vehicle that impels of double fuselage composite wing overall arrangement, its characterized in that, the horizontal tail adopts symmetrical wing section, realizes vertical net stability. The winglet of the wing tip of the main wing is positioned outside the wing tip of the main wing, and can adopt a combination of an upper reverse type, a lower reverse type and an upper reverse type, so that the induced resistance of the main wing is reduced, and the flight performance is improved; the horizontal tail winged knife is positioned in the middle of the upper wing surface of the horizontal tail, so that the lateral interference of surface flow is reduced.
Further, according to the above design scheme, the two-fuselage compound wing layout multistage propulsion unmanned aerial vehicle is characterized in that the winglet adopts any one of an upper-reverse type, a lower-reverse type or an upper-lower reverse type, and is used for reducing induced resistance of the main wing and improving flight performance.
Further, according to the design scheme, the double-fuselage compound wing layout multistage propulsion unmanned aerial vehicle is characterized in that the distance between the double fuselages is 15% -30% of the wingspan length of a main engine, the cross section of a single fuselage is in a circular, rectangular or trapezoidal shape, and the nose of the single fuselage is subjected to raindrop type contraction treatment to reduce flight resistance; the strut type undercarriage is symmetrically located on the lower side of the double-fuselage, the front wheels are single wheels and are 10% -20% of the length of the fuselage from the nose, and the rear wheels are double wheels and are main bearing parts of gravity and located on the lower side of a connecting point of the main wing and the double-fuselage. The double vertical tails are positioned at the rear ends of the double bodies and are connected with the double bodies and the horizontal tails, so that the structural strength of the unmanned aerial vehicle is improved.
Further, according to the above design scheme, the two-fuselage compound wing layout multistage propulsion unmanned aerial vehicle is characterized in that the one-level propulsion propeller, the two-level propulsion propeller and the three-level propulsion propeller can be selected from any one of 2-blade, 3-blade and 4-blade propellers, and the material is wood or a composite material.
Further, according to the above design scheme, the two-fuselage compound wing layout multistage propulsion unmanned aerial vehicle is characterized in that chord length of each control surface of the canard wing control surface, the ailerons, the flaps, the rear wing control surface and the horizontal tail elevator is 15-30% of chord length of the wing profile at the corresponding position.
The technical effects of the utility model are as follows: (1) adopt multistage propulsion system screw system, can realize fixed wing unmanned aerial vehicle's VTOL, short distance take off and land, overcome the unstable phenomenon of the process of hanging down to flat flight process, promote the adaptability of heavy load fixed wing unmanned aerial vehicle to the take off and land condition by a wide margin, combine with the composite wing, have comparatively outstanding structural performance.
(2) Effectively combine composite wing overall arrangement, double fuselage structure, increased the lift performance by a wide margin, through the overall arrangement form that duck wing, even wing combine for lift promotes about 35~65%, has realized big load problem, adopts double fuselage structure simultaneously, has optimized load loading space, provides high strength structure.
(3) By adopting a multistage propulsion mode, the switching design of different speeds is completed on the basis of the existing basic conditions according to different task requirements, and three flight modes of cruising speeds are realized.
Drawings
Fig. 1 is a perspective view of the unmanned aerial vehicle of the present invention;
fig. 2 is a top view of the unmanned aerial vehicle of the present invention;
fig. 3 is a front view of the unmanned aerial vehicle of the present invention;
fig. 4 is a side view of the unmanned aerial vehicle of the present invention;
in the figure, 11 double bodies, 12 strut type landing gears, 13 double vertical tails, 21 front duck wings, 22 main wings, 23 rear wings, 24 horizontal tails, 25 main wing tip winglets, 26 horizontal tail winglets, 31 first-stage propulsion propellers, 32 second-stage propulsion propellers, 33 third-stage propulsion propellers, 41 wing control surfaces, 42 ailerons, 43 flaps, 44 rear wing control surfaces and 45 horizontal tail elevators.
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", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific 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 is to 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 meaning of the above terms in the present invention can be understood in specific cases by those skilled in the art.
Example 1:
the utility model provides a two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle, two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle include: the double-fuselage structure is used for a main bearing structure, load loading, airborne system installation and the like, the composite wing structure generates main lift force in a flat flight state and carries effective load according to actual requirements, the multi-stage propulsion system consists of three groups of propeller systems and is used for functions of vertical take-off and landing, staged propulsion, flying speed adjustment and the like, the flight performance is optimized, and the composite rudder system realizes unmanned aerial vehicle flight attitude control.
The double-body structure consists of a double body 11, a strut type undercarriage 12 and double vertical tails 13. The distance between the two machine bodies 11 is 18 percent of the span length of the wing, the cross section is in a circular shape 8, and the machine head adopts raindrop type contraction treatment to reduce the flight resistance; the strut type undercarriage 12 is symmetrically positioned at the lower side of the double-fuselage, the front wheel is a single wheel and is 10 percent of the length of the fuselage from the nose, the rear wheel is a double wheel and is a main bearing part of gravity and is positioned at the lower side of the connecting point of the main wing 22 and the double-fuselage 11; double vertical tails 13 are located double fuselage 11 rear end, connect double fuselage 11 and horizontal tail 24, improve unmanned aerial vehicle structural strength.
The composite wing structure is composed of a front duck wing 21, a main wing 22, a rear wing 23, a horizontal tail 24, a wingtip winglet 25 of the main wing and a horizontal tail wingknife 26. The front duck wing 21 is positioned near the head of the double-fuselage, a low-speed wing type is adopted, and the spreading length of the front duck wing 21 is 55% of that of the main wing 22; the main wing 22 is positioned in the middle of the double-body 11 and is 55% of the length of the double-body from the machine head, the main wing 22 adopts a low-speed wing shape, the front edge sweepback angle is 0-20 degrees, and the rear edge sweepback angle is 0-15 degrees; the left and right wingtips of the rear wing 23 are connected to the wing tips 8% -18% of the span length from the main wing 22, the rear wing 23 is fixedly connected to the upper part of the double vertical tails 13 and is connected with the wingtips of the horizontal tails 24, and the rear wing 23 adopts a laminar flow wing type and a supercritical wing type; the horizontal tail 24 is fixedly connected with the upper ends of the double vertical tails 13, and a symmetrical wing type is adopted to realize the longitudinal net stability; the winglet 25 on the wing tip of the main wing is positioned on the outer side of the wing tip of the main wing, and can adopt a combination of up-turning, down-turning and up-turning, so that the induced resistance of the main wing is reduced, and the flight performance is improved; the horizontal tail winged knife 26 is positioned in the middle of the upper wing surface of the horizontal tail 24, and the lateral interference of surface flow is reduced.
The multi-stage propulsion system is composed of a first-stage propulsion propeller 31, a second-stage propulsion propeller 32 and a third-stage propulsion propeller 33. The primary propulsion propeller 31 is positioned at the front edge of the connecting point of the main wing 22 and the rear wing 23; the secondary propulsion propeller 32 is positioned outside the connection point of the front duck wing 21 and the airplane body and at the rear edge of the front duck wing 21, so that vertical and horizontal tilting can be realized; the three-stage propulsion propeller 33 is positioned at the junction of the horizontal tail 24 and the rear wing 23, and can realize vertical and horizontal tilting switching. Multistage propulsion system can realize unmanned aerial vehicle's VTOL, different cruise speed flight switch, the wheeled take-off and land of short distance, realizes VTOL when adopting one-level, tertiary perpendicular, changes the propulsion step by step after the flat flight, improves flying speed, adopts one-level, second grade, tertiary different flat speed that flies to switch, and when wheeled take-off and land, adopts one-level, tertiary perpendicular lift that provides, the reduction distance of taking off and land. The first-stage propulsion propeller 31, the second-stage propulsion propeller 32 and the third-stage propulsion propeller 33 are respectively made of 2-blade, 3-blade and 2-blade blades and are made of wood.
The composite control surface system is composed of a canard control surface 41, an aileron 42, a flap 43, a rear wing control surface 44 and a horizontal tail elevator 45, and the chord-wise length of each control surface is 15% of the chord length of an airfoil at a corresponding position. The duck wing control surface 41 is positioned at the rear edge of the outer side of the front duck wing 21 and is used for the auxiliary operation of maneuverability of the unmanned aerial vehicle; the ailerons 42 are positioned at the rear edge of the outer end of the main wing 22 and are used for the transverse control of the unmanned plane; the flap 43 is positioned at the rear edge of the main wing 22 close to one side of the double-fuselage and is used for increasing lift force during takeoff; the rear wing rudder surface 44 is positioned at the rear edge of the rear wing close to one side of the double vertical tails 13 and is used for course control; the horizontal tail elevator 45 is positioned at the rear edge of the horizontal tail, so that the pitching operation of the unmanned aerial vehicle is realized.
Example 2:
the utility model provides a two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle, two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle include: the double-fuselage structure is used for a main bearing structure, load loading, airborne system installation and the like, the composite wing structure generates main lift force in a flat flight state and carries effective load according to actual requirements, the multi-stage propulsion system consists of three groups of propeller systems and is used for functions of vertical take-off and landing, staged propulsion, flying speed adjustment and the like, the flight performance is optimized, and the composite rudder system realizes unmanned aerial vehicle flight attitude control.
The double-body structure consists of a double body 11, a strut type undercarriage 12 and double vertical tails 13. The distance between the two machine bodies 11 is 25% of the span length of the wing, the cross section is circular, and the machine head adopts raindrop type contraction treatment to reduce flight resistance; the strut type undercarriage 12 is symmetrically positioned at the lower side of the double-fuselage, the front wheel is a single wheel and is 15 percent of the length of the fuselage from the nose, the rear wheel is a double wheel and is a main bearing part of gravity, and the rear wheel is positioned at the lower side of a connecting point of the main wing 22 and the double-fuselage 11; double vertical tails 13 are located double fuselage 11 rear end, connect double fuselage 11 and horizontal tail 24, improve unmanned aerial vehicle structural strength.
The composite wing structure is composed of a front duck wing 21, a main wing 22, a rear wing 23, a horizontal tail 24, a wingtip winglet 25 of the main wing and a horizontal tail wingknife 26. The front duck wing 21 is positioned near the head of the double-fuselage, a low-speed wing type is adopted, and the spreading length of the front duck wing 21 is 60% of that of the main wing 22; the main wing 22 is positioned in the middle of the double-body 11 and is 58% of the length of the double-body from the machine head, the main wing 22 adopts a low-speed wing shape, the front edge sweepback angle is 0-20 degrees, and the rear edge sweepback angle is 0-15 degrees; the left and right wingtips of the rear wing 23 are connected to the wing tips 8% -18% of the span length from the main wing 22, the rear wing 23 is fixedly connected to the upper part of the double vertical tails 13 and is connected with the wingtips of the horizontal tails 24, and the rear wing 23 adopts a laminar flow wing type and a supercritical wing type; the horizontal tail 24 is fixedly connected with the upper ends of the double vertical tails 13, and a symmetrical wing type is adopted to realize the longitudinal net stability; the winglet 25 on the wing tip of the main wing is positioned on the outer side of the wing tip of the main wing, and can adopt a combination of up-turning, down-turning and up-turning, so that the induced resistance of the main wing is reduced, and the flight performance is improved; the horizontal tail winged knife 26 is positioned in the middle of the upper wing surface of the horizontal tail 24, and the lateral interference of surface flow is reduced.
The multi-stage propulsion system is composed of a first-stage propulsion propeller 31, a second-stage propulsion propeller 32 and a third-stage propulsion propeller 33. The primary propulsion propeller 31 is positioned at the front edge of the connecting point of the main wing 22 and the rear wing 23; the secondary propulsion propeller 32 is positioned outside the connection point of the front duck wing 21 and the airplane body and at the rear edge of the front duck wing 21, so that vertical and horizontal tilting can be realized; the three-stage propulsion propeller 33 is positioned at the junction of the horizontal tail 24 and the rear wing 23, and can realize vertical and horizontal tilting switching. Multistage propulsion system can realize unmanned aerial vehicle's VTOL, different cruise speed flight switch, the wheeled take-off and land of short distance, realizes VTOL when adopting one-level, tertiary perpendicular, changes the propulsion step by step after the flat flight, improves flying speed, adopts one-level, second grade, tertiary different flat speed that flies to switch, and when wheeled take-off and land, adopts one-level, tertiary perpendicular lift that provides, the reduction distance of taking off and land. The first-stage propulsion propeller 31, the second-stage propulsion propeller 32 and the third-stage propulsion propeller 33 are 2-blade, 2-blade and 2-blade blades respectively and are made of composite materials.
The composite control surface system is composed of a canard control surface 41, an aileron 42, a flap 43, a rear wing control surface 44 and a horizontal tail elevator 45, and the chord-wise length of each control surface is 20% of the chord length of an airfoil at a corresponding position. The duck wing control surface 41 is positioned at the rear edge of the outer side of the front duck wing 21 and is used for the auxiliary operation of maneuverability of the unmanned aerial vehicle; the ailerons 42 are positioned at the rear edge of the outer end of the main wing 22 and are used for the transverse control of the unmanned plane; the flap 43 is positioned at the rear edge of the main wing 22 close to one side of the double-fuselage and is used for increasing lift force during takeoff; the rear wing rudder surface 44 is positioned at the rear edge of the rear wing close to one side of the double vertical tails 13 and is used for course control; the horizontal tail elevator 45 is positioned at the rear edge of the horizontal tail, so that the pitching operation of the unmanned aerial vehicle is realized.
Example 3
The utility model provides a two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle, two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle include: the double-fuselage structure is used for a main bearing structure, load loading, airborne system installation and the like, the composite wing structure generates main lift force in a flat flight state and carries effective load according to actual requirements, the multi-stage propulsion system consists of three groups of propeller systems and is used for functions of vertical take-off and landing, staged propulsion, flying speed adjustment and the like, the flight performance is optimized, and the composite rudder system realizes unmanned aerial vehicle flight attitude control.
The double-body structure consists of a double body 11, a strut type undercarriage 12 and double vertical tails 13. The distance between the two machine bodies 11 is 30% of the span length of the wing, the cross section is circular, and the machine head adopts raindrop type contraction treatment to reduce flight resistance; the strut type undercarriage 12 is symmetrically positioned at the lower side of the double-fuselage, the front wheel is a single wheel and is 20 percent of the length of the fuselage from the nose, the rear wheel is a double wheel and is a main bearing part of gravity and is positioned at the lower side of a connecting point of the main wing 22 and the double-fuselage 11; double vertical tails 13 are located double fuselage 11 rear end, connect double fuselage 11 and horizontal tail 24, improve unmanned aerial vehicle structural strength.
The composite wing structure is composed of a front duck wing 21, a main wing 22, a rear wing 23, a horizontal tail 24, a wingtip winglet 25 of the main wing and a horizontal tail wingknife 26. The front duck wing 21 is positioned near the double-fuselage nose, a low-speed wing profile, a laminar flow wing profile and a supercritical wing profile can be adopted, and the extension length of the front duck wing 21 is 65% of that of the main wing 22; the main wing 22 is positioned in the middle of the double-body 11 and is 60% of the length of the double-body from the machine head, the main wing 22 adopts a low-speed wing shape, the front edge sweepback angle is 0-20 degrees, and the rear edge sweepback angle is 0-15 degrees; the left and right wingtips of the rear wing 23 are connected to the wing tips 8% -18% of the span length from the main wing 22, the rear wing 23 is fixedly connected to the upper part of the double vertical tails 13 and is connected with the wingtips of the horizontal tails 24, and the rear wing 23 adopts a laminar flow wing type and a supercritical wing type; the horizontal tail 24 is fixedly connected with the upper ends of the double vertical tails 13, and a symmetrical wing type is adopted to realize the longitudinal net stability; the winglet 25 on the wing tip of the main wing is positioned on the outer side of the wing tip of the main wing, and can adopt a combination of up-turning, down-turning and up-turning, so that the induced resistance of the main wing is reduced, and the flight performance is improved; the horizontal tail winged knife 26 is positioned in the middle of the upper wing surface of the horizontal tail 24, and the lateral interference of surface flow is reduced.
The multi-stage propulsion system is composed of a first-stage propulsion propeller 31, a second-stage propulsion propeller 32 and a third-stage propulsion propeller 33. The primary propulsion propeller 31 is positioned at the front edge of the connecting point of the main wing 22 and the rear wing 23; the secondary propulsion propeller 32 is positioned outside the connection point of the front duck wing 21 and the airplane body and at the rear edge of the front duck wing 21, so that vertical and horizontal tilting can be realized; the three-stage propulsion propeller 33 is positioned at the junction of the horizontal tail 24 and the rear wing 23, and can realize vertical and horizontal tilting switching. Multistage propulsion system can realize unmanned aerial vehicle's VTOL, different cruise speed flight switch, the wheeled take-off and land of short distance, realizes VTOL when adopting one-level, tertiary perpendicular, changes the propulsion step by step after the flat flight, improves flying speed, adopts one-level, second grade, tertiary different flat speed that flies to switch, and when wheeled take-off and land, adopts one-level, tertiary perpendicular lift that provides, the reduction distance of taking off and land. The first-stage propulsion propeller 31, the second-stage propulsion propeller 32 and the third-stage propulsion propeller 33 are respectively 2-blade, 3-blade and 3-blade blades and are made of wood.
The composite control surface system is composed of a canard control surface 41, an aileron 42, a flap 43, a rear wing control surface 44 and a horizontal tail elevator 45, and the chord-wise length of each control surface is 25% of the chord length of an airfoil at a corresponding position. The duck wing control surface 41 is positioned at the rear edge of the outer side of the front duck wing 21 and is used for the auxiliary operation of maneuverability of the unmanned aerial vehicle; the ailerons 42 are positioned at the rear edge of the outer end of the main wing 22 and are used for the transverse control of the unmanned plane; the flap 43 is positioned at the rear edge of the main wing 22 close to one side of the double-fuselage and is used for increasing lift force during takeoff; the rear wing rudder surface 44 is positioned at the rear edge of the rear wing close to one side of the double vertical tails 13 and is used for course control; the horizontal tail elevator 45 is positioned at the rear edge of the horizontal tail, so that the pitching operation of the unmanned aerial vehicle is realized.
The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications, additions and substitutions for the specific embodiments described herein may be made by those skilled in the art without departing from the spirit of the invention or exceeding the scope of the invention as defined in the accompanying claims.
Although terms such as the double fuselage 11, the strut landing gear 12, the double vertical tail 13, the forward canard wing 21, the main wing 22, the rear wing 23, the horizontal tail 24, the main wing tip winglet 25, the horizontal tail wing knife 26, the primary propulsion propeller 31, the secondary propulsion propeller 32, the tertiary propulsion propeller 33, the wing rudder surface 41, the aileron 42, the flap 43, the rear wing rudder surface 44, the horizontal tail elevator 45, 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 in a manner that is inconsistent with the spirit of the invention.
Claims (9)
1. The utility model provides a two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle, its characterized in that, two fuselage composite wing overall arrangement multistage propulsion unmanned aerial vehicle includes: the system comprises a double-fuselage structure, a composite wing structure, a multi-stage propulsion system and a composite control surface system;
the double-body structure consists of a double body (11), a strut type undercarriage (12) and double vertical tails (13) which are symmetrically arranged in parallel; the strut type undercarriage (12) is arranged at the bottom of the double machine body (11); the double vertical tails (13) are arranged at the rear ends of the double bodies (11);
the composite wing structure consists of a front duck wing (21), a main wing (22), a rear wing (23), a horizontal tail (24), a wingtip winglet (25) of the main wing and a horizontal tail wingknife (26); the front duck wing (21) is arranged at the head position of the double-body (11); the main wing (22) is fixedly arranged in the middle of the double-body (11); the left wing tip and the right wing tip of the rear wing (23) are connected to the main wing (22), and the other end of the rear wing (23) is fixedly connected with the upper part of the double vertical tails (13) and is connected with the wing tips of the horizontal tails (24); the horizontal tail (24) is fixedly connected with the upper ends of the double vertical tails (13); the winglet (25) is arranged on the outer side of the wing tip of the main wing (22); the horizontal tail winged knife (26) is arranged in the middle of the upper wing surface of the horizontal tail (24);
the multistage propulsion system consists of a first-stage propulsion propeller (31), a second-stage propulsion propeller (32) and a third-stage propulsion propeller (33); the primary propulsion propeller (31) is arranged at the front edge of the connecting point of the main wing (22) and the rear wing (23); the two-stage propulsion propeller (32) is arranged outside the connection point of the front duck wing (21) and the double-body (11) and is positioned at the rear edge of the front duck wing (21); the three-stage propulsion propeller (33) is arranged at the junction of the horizontal tail (24) and the rear wing (23);
the composite control surface system comprises a canard control surface (41), an aileron (42), a flap (43), a rear wing control surface (44) and a horizontal tail elevator (45); the duck wing control surface (41) is arranged on the rear edge of the outer side of the front duck wing (21); the ailerons (42) are arranged on the rear edge of the outer end of the main wing (22); the flap (43) is arranged on the trailing edge of one side, close to the double-body, of the main wing (22); the rear wing control surface (44) is arranged on the rear edge of the rear wing (23) close to one side of the double vertical tails (13); the horizontal tail elevator (45) is arranged at the rear edge of the horizontal tail (24).
2. The unmanned aerial vehicle with the double-fuselage compound wing layout and the multistage propulsion function as claimed in claim 1, wherein the forward duck wing (21) is any one of a low-speed wing, a laminar wing and a supercritical wing, and the span length of the forward duck wing (21) is 55% -70% of that of the main wing (22).
3. The twin fuselage compound wing layout multi-stage propulsion drone of claim 1, wherein the main wing (22) is located 55% to 60% of the fuselage length from the nose of the twin fuselage; the main wing (22) adopts any one of a low-speed wing type, a laminar flow wing type and a supercritical wing type, and the sweep angle of the front edge is 0-20 degrees, and the sweep angle of the rear edge is 0-15 degrees.
4. The twin fuselage compound wing layout multistage propulsion drone of claim 1, wherein the rear wing (23) left and right wing tips are connected at 8% to 18% spanwise position from the main wing (22) wing tip; the rear wing (23) adopts a laminar flow wing profile or a supercritical wing profile.
5. The twin fuselage compound wing layout multistage propulsion drone of claim 1, wherein the horizontal tail (24) is of symmetrical wing profile to achieve a net longitudinal stability.
6. The unmanned aerial vehicle with the double-fuselage composite wing layout and the multistage propulsion function as claimed in claim 1, wherein the winglet (25) is configured to be either an upper-reverse type winglet, a lower-reverse type winglet or a combination of an upper-reverse type winglet and a lower-reverse type winglet, so as to reduce induced drag of the main wing and improve flight performance.
7. The unmanned aerial vehicle with the double-fuselage compound wing layout and the multistage propulsion according to claim 1 is characterized in that the distance between the double fuselages (11) is 15% -30% of the span length of the main wing (22), the cross section of each fuselage is circular, rectangular or trapezoidal, and the nose of each fuselage is subjected to raindrop type contraction treatment for reducing flight resistance; the strut type undercarriage (12) is symmetrically arranged on the lower side of the double-fuselage, the front wheels are single wheels and are 10% -20% of the length of the fuselage from the nose, the rear wheels are double wheels and are main bearing parts of gravity, and the strut type undercarriage is arranged on the lower side of a connecting point of the main wing (22) and the double-fuselage (11).
8. The unmanned aerial vehicle with the double-fuselage compound wing layout and the multi-stage propulsion as claimed in claim 1, wherein the first-stage propulsion propeller (31), the second-stage propulsion propeller (32) and the third-stage propulsion propeller (33) can be any one of 2-blade, 3-blade and 4-blade propellers, and the material is wood or composite material.
9. The twin-fuselage compound wing layout multistage propulsion drone according to claim 1, wherein the chord length of the control surfaces of the canard wing control surface (41), the aileron (42), the flap (43), the rear wing control surface (44) and the horizontal tail elevator (45) is 15-30% of the chord length of the wing profile at the corresponding position.
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| CN202120531690.9U CN214451787U (en) | 2021-03-15 | 2021-03-15 | Double-fuselage compound wing layout multistage propulsion unmanned aerial vehicle |
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| CN202120531690.9U CN214451787U (en) | 2021-03-15 | 2021-03-15 | Double-fuselage compound wing layout multistage propulsion unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911336A (en) * | 2021-11-29 | 2022-01-11 | 南京航空航天大学 | Double-fuselage type tilt rotorcraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911336A (en) * | 2021-11-29 | 2022-01-11 | 南京航空航天大学 | Double-fuselage type tilt rotorcraft |
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