CN113682469A - Overall layout of small long-endurance unmanned aerial vehicle - Google Patents
Overall layout of small long-endurance unmanned aerial vehicle Download PDFInfo
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- CN113682469A CN113682469A CN202111164477.XA CN202111164477A CN113682469A CN 113682469 A CN113682469 A CN 113682469A CN 202111164477 A CN202111164477 A CN 202111164477A CN 113682469 A CN113682469 A CN 113682469A
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- aerial vehicle
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
Abstract
The invention provides the overall layout of a small-sized long-endurance unmanned aerial vehicle, which takes the improvement of the endurance time of the unmanned aerial vehicle as a main target, adopts a slender wing, a streamline-shaped fuselage and a large-diameter thrust propeller, and reasonably arranges all components to form a high-efficiency pneumatic layout. And a vehicle-mounted take-off mode is adopted, so that the weight is reduced, and the oil consumption rate is reduced. The small-sized long-endurance unmanned aerial vehicle has the characteristics of large lift force, small resistance and high efficiency, is flexible to use, can be used for leaving air for a long time to execute tasks, and far exceeds the average level of the same type of unmanned aerial vehicle in the endurance capacity.
Description
Technical Field
The invention relates to a general layout of a small-sized long-endurance unmanned aerial vehicle.
Background
The small-sized long-endurance unmanned aerial vehicle is generally considered to be an unmanned aerial vehicle with the takeoff weight within 100kg and the continuous flight time of more than 24 hours. At present, unmanned aerial vehicle's the longest duration has generally can reach about 20 hours, however, along with the continuous change of international situation and the continuous development of science and technology level, military and civilian field all propose for a long time to unmanned aerial vehicle cruise and use nimble task demand, patrol and examine like extra-high voltage transmission line total length, forest fire prevention lasts reconnaissance, island reef real time monitoring etc. current small-size long time unmanned aerial vehicle during voyage is at the time of the voyage, all is difficult to satisfy these task demands on the voyage. Therefore, on the basis of keeping the advantage of small size, the unmanned aerial vehicle with long endurance needs to be designed to increase endurance as a main target and to use a small unmanned aerial vehicle with long endurance flexibly.
Disclosure of Invention
For a small unmanned aerial vehicle, the oil carrying capacity of the small unmanned aerial vehicle is limited to a certain extent, the oil consumption rate is reduced when the flight time is improved, the overall consideration and the comprehensive optimization of the aspects of aerodynamic force, propellers, take-off and landing forms and the like are required in the overall layout design, and the purposes of light weight, small resistance, high energy utilization rate and small oil consumption rate are finally achieved.
According to an aspect of the present invention, there is provided a small-sized long-endurance unmanned aerial vehicle, comprising: wings, a fuselage, a steel cable, a horizontal tail wing, a vertical tail wing, a tail boom and a propeller,
wherein:
the wing and the fuselage are in front,
the horizontal tail wing and the vertical tail wing are arranged at the back,
the propeller is arranged at the tail part of the machine body, namely the middle part of the whole machine
The wings are positioned on the upper side of the fuselage, above the integral center of gravity,
the tail support is arranged above the propeller, provides sufficient space for the propeller to operate, and is arranged on the machine body,
the horizontal tail wing and the vertical tail wing are arranged on the tail boom,
the horizontal tail wing is positioned at the rear upper part of the wing to avoid the interference of the wing wake flow and improve the pneumatic efficiency of the horizontal tail wing,
the horizontal and vertical rear wings are arranged to avoid the propulsive airflow so that the propulsive airflow flows smoothly,
the vertical tail is arranged behind the horizontal tail to provide the unmanned aerial vehicle with lateral stability,
the inclined tip winglet is arranged at the outer end of the wing, so that the wing is slender, the aerodynamic efficiency of the wing is improved, the projection area of the wing on the horizontal plane can be increased, and when the wing is under the action of the same lift force, the load on the wing can be dispersed, so that the structure of the wing is safer when being loaded
The position of the wing close to the outside is provided with an aileron to control the rolling attitude of the unmanned aerial vehicle,
the machine body is formed by smoothly connecting a cylinder and a dorsal fin,
the left side and the right side of the aircraft body are respectively provided with an air inlet at the middle rear part, and can provide cooling air for the engine in the flying process,
the middle section of the wing is provided with a steel cable connected with the fuselage and used for sharing aerodynamic load on the wing and reducing the structural weight of the wing.
Drawings
Fig. 1 is a general schematic perspective view of a small-sized long endurance drone according to one embodiment of the present invention.
Fig. 2 is a side view of a small long endurance drone according to one embodiment of the present invention.
Fig. 3 is a top view of a wing of a small long endurance drone according to one embodiment of the present invention.
Fig. 4 is an enlarged schematic view of a winglet of a wing of a small-sized drone for long endurance according to an embodiment of the invention.
Fig. 5 is a schematic view of the fuselage of a small long endurance drone according to one embodiment of the present invention.
Fig. 6 is an enlarged schematic view of the tail of a small long endurance drone according to one embodiment of the present invention.
Detailed Description
As shown in fig. 1, the small-sized long-endurance unmanned aerial vehicle according to one embodiment of the present invention includes a wing (6), a fuselage (5), a wire rope (4), a horizontal tail (2), a vertical tail (1), a tail boom (7), and a propeller (3); the wing (6) and the fuselage (5) are arranged in front, the horizontal tail wing (2) and the vertical tail wing (1) are arranged behind, and the propeller (3) is arranged at the tail part of the fuselage (5), namely the middle part of the whole aircraft. As shown in fig. 2, the wings (6) are located on the upper side of the fuselage (5) above the overall center of gravity, so that the overall lateral stability of the unmanned aerial vehicle is better. The tail support (7) is positioned above the propeller (3), provides sufficient space for the operation of the propeller (3), and is arranged on the machine body (5). The horizontal tail wing (2) and the vertical tail wing (1) are arranged on the tail support (7). The horizontal tail wing (2) is positioned above the rear part of the wing (6), so that the interference of the wake flow of the wing (6) can be avoided, the pneumatic efficiency of the horizontal tail wing (2) is improved, meanwhile, the shielding of the propulsion air flow (8) is avoided, the propulsion air flow (8) is smooth, and the propulsion efficiency of the propeller (3) is improved. The vertical tail (1) is arranged at the rearmost part, and provides sufficient lateral stability for the unmanned aerial vehicle.
1) Wing
The plane shape of the single-sided wing (6) is shown in figure 3, and the single-sided wing is characterized by being slender, generating large lift force, meanwhile, having small resistance and high aerodynamic efficiency. The outer end of the wing (6) is provided with the oblique tip winglet (10) which has the effect of making the wing (6) more slender and improves the aerodynamic efficiency, meanwhile, the oblique tip winglet (10) can increase the projection area of the wing (6) on the horizontal plane, and when the wing is under the action of the same lift force, the load on the wing (6) can be dispersed, so that the structure of the wing (6) is safer when bearing. An enlarged schematic view of the raked tip winglet (10) is shown in figure 4. A pair of ailerons (9) is arranged at the outer position of the wing (6) and can control the rolling attitude of the unmanned aerial vehicle.
2) Fuselage body
The fuselage (5) is formed by smoothly connecting a cylinder (17) and a dorsal fin (18), as shown in fig. 5. The head and the tail of the cylinder (17) and the dorsal fin (18) are both rectified, the whole body is streamline, and the resistance is small. The left side and the right side of the aircraft body (5) are provided with a pair of air inlets (11) at the middle rear part, and cooling air can be provided for an engine in the flying process. Set up nose cover (16), top cover (19), tail cover (13) and side flap (12) on fuselage (5), can dismantle fast, conveniently install and maintain airborne equipment in fuselage (5). The invention adopts the taking-off and landing mode of vehicle-mounted taking-off and belly ground rubbing landing, so that a pair of ground rubbing foams (15) and taking-off pin holes (14) are arranged without arranging a landing gear on a machine body (5), and the weight and the resistance are reduced. When the unmanned aerial vehicle takes off, the unmanned aerial vehicle can be pushed to advance through the take-off pin hole (14). The structure of the body of the ground wiping foam (15) can be protected when the ground wiping foam lands, and the center of gravity of the whole unmanned aerial vehicle is located between the two ground wiping foams (15), so that the attitude of the unmanned aerial vehicle is kept stable in the landing process.
3) Steel cable
Because the wing (6) is slender, if the load of the wing (6) is only born by the structure of the wing, the internal force of the root of the wing is large, and in order to ensure that the root of the wing has enough strength, the weight of the required structure is increased remarkably. Therefore, the middle section of the wing (6) is provided with the steel cable (4) which is connected with the fuselage (5) to share the aerodynamic load on the wing (6), so that the structural weight of the wing (6) can be reduced.
4) Tail wing
An enlarged view of the tail is shown in fig. 6, where both the horizontal tail (2) and the vertical tail (1) are mounted on the tail boom (7). The horizontal tail wing (2) is a whole movable control surface and is positioned below the tail support (7). Vertical tail (1) is the immovable fin of a monoblock, therefore simple structure can alleviate afterbody weight, avoids the excessive back shift of full quick-witted focus, influences unmanned aerial vehicle's longitudinal stability.
5) Propeller
In order to make the propeller (3) more efficient, a larger diameter propeller (3) is selected. The high tail support (7) provides sufficient space for the operation of the large-diameter propeller (3). Screw (3) are arranged at fuselage (5) afterbody, therefore screw (3) are the thrust type, provide forward thrust for unmanned aerial vehicle. Because the horizontal tail wing (2) and the vertical tail wing (1) avoid the propulsion air flow (8), the propulsion air flow (8) flows smoothly, and the propulsion efficiency is higher.
The advantages and beneficial effects of the invention include:
1) and a high-efficiency pneumatic layout is adopted, so that the pneumatic efficiency is high. The wings are slender wings, so that the lift force is large, and the resistance is small. The whole body is streamline and has small resistance. The large-diameter thrust type propeller is adopted, and the high tail wing reduces the blockage to the thrust air flow, so that the propulsion efficiency is high.
2) The landing and taking-off mode of vehicle-mounted take-off and belly ground rubbing landing is adopted, the landing gear required by the conventional unmanned aerial vehicle is omitted, and the weight and the aerodynamic resistance are reduced. The friction resistance of ground running is overcome through the car, can select for use the engine that power is littleer for unmanned aerial vehicle, and the oil consumption is lower, can improve during the voyage. Because the automobile has good acceleration, the effect of short-distance take-off and landing can be achieved. The vehicle-mounted take-off mode has low requirements on take-off fields, does not need a long-distance regular runway, can take off on grasslands and dirt roads, and is flexible and convenient to take off. Because unmanned aerial vehicle lift is big, the landing process is comparatively gentle, consequently adopt wipe ground foam to carry out simple buffering to the organism can, light in weight, the resistance is little.
The small-sized long-endurance unmanned aerial vehicle has the advantages of large overall lift, small resistance, light weight, high propulsion efficiency, improvement on energy utilization rate, low oil consumption, contribution to improvement on endurance time, exertion of the advantage of flexible and convenient use of the small-sized unmanned aerial vehicle, and capability of meeting the requirements of flexible use and long-time air-staying task execution. The endurance time of a small-sized long-endurance unmanned aerial vehicle model machine in an example of the invention reaches 80 hours in an actual flight test, and far exceeds the average level of the same type of unmanned aerial vehicle.
Claims (8)
1. The utility model provides a unmanned aerial vehicle during small-size long voyage, its characterized in that includes: wings (6), a fuselage (5), a steel cable (4), a horizontal tail wing (2), a vertical tail wing (1), a tail boom (7) and a propeller (3),
wherein:
the wing (6) and the fuselage (5) are in front,
the horizontal tail wing (2) and the vertical tail wing (1) are arranged at the back,
the propeller (3) is arranged at the tail part of the machine body (5), namely the middle part of the whole machine,
the wings (6) are positioned on the upper side of the fuselage (5) above the integral gravity center,
the tail support (7) is arranged above the propeller (3), provides sufficient space for the operation of the propeller (3) and is arranged on the machine body (5),
the horizontal tail wing (2) and the vertical tail wing (1) are arranged on a tail boom (7),
the horizontal tail wing (2) is positioned at the rear upper part of the wing (6) to avoid the interference of the wake flow of the wing (6) and improve the pneumatic efficiency of the horizontal tail wing (2),
the horizontal tail fin (2) and the vertical tail fin (1) are arranged to avoid the propulsive gas flow (8) to make the propulsive gas flow (8) flow smoothly,
the vertical tail (1) is arranged behind the horizontal tail (2) to provide the unmanned plane with the stability of the horizontal direction,
the outer end of the wing (6) is provided with the oblique tip winglet (10) which has the effect of making the wing (6) more slender and improves the aerodynamic efficiency, the oblique tip winglet (10) can increase the projection area of the wing (6) on the horizontal plane, and when the wing is under the action of the same lift force, the load on the wing (6) can be dispersed, so that the structure of the wing (6) is safer when bearing the load
An aileron (9) is arranged at the position close to the outer part of the wing (6) to control the rolling attitude of the unmanned plane,
the fuselage (5) is formed by smoothly connecting a cylinder (17) and a dorsal fin (18),
the left side and the right side of the fuselage (5) are respectively provided with an air inlet (11) at the middle rear part, and can provide cooling air for the engine in the flying process,
the middle section of the wing (6) is provided with a steel cable (4) connected with the fuselage (5) for sharing aerodynamic load on the wing (6) and reducing the structural weight of the wing (6).
2. A small-sized long endurance drone according to claim 1, wherein:
the wing (6) is an elongated wing.
3. A small-sized long endurance drone according to claim 1, wherein:
the head and the tail of the cylinder (17) and the dorsal fin (18) are both rectified, the whole body is streamline, and the resistance is small.
4. A small-sized long endurance drone according to claim 1, wherein:
a nose cover (16), a top cover (19), a tail cover (13) and a side cover (12) are arranged on the machine body (5).
5. A small-sized long endurance drone according to claim 1, wherein:
a pair of wiping foam (15) and take-off pin holes (14) are arranged on the fuselage (5) and are used for taking off and landing in a vehicle-mounted manner and in a belly wiping landing manner,
wherein:
the take-off pin hole (14) is used for pushing the unmanned aerial vehicle to advance during take-off,
the floor wiping foam (15) is used for protecting the body structure when landing,
the center of gravity of the whole unmanned aerial vehicle is positioned between a pair of ground wiping foams (15), so that the attitude of the unmanned aerial vehicle is kept stable in the landing process.
6. A small-sized long endurance drone according to claim 1, wherein:
the horizontal tail wing (2) is a whole movable control surface and is positioned below the tail support (7).
7. A small-sized long endurance drone according to claim 1, wherein:
the vertical tail (1) is a whole immovable stabilizing surface.
8. A small-sized long endurance drone according to claim 1, wherein:
the propeller (3) is a thrust propeller with a large diameter.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111164477.XA CN113682469B (en) | 2021-09-30 | 2021-09-30 | Overall layout of small long-endurance unmanned aerial vehicle |
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| CN202111164477.XA CN113682469B (en) | 2021-09-30 | 2021-09-30 | Overall layout of small long-endurance unmanned aerial vehicle |
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| CN113682469A true CN113682469A (en) | 2021-11-23 |
| CN113682469B CN113682469B (en) | 2023-03-10 |
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