CN112429199B - Unmanned aerial vehicle adopting full-dynamic elevator - Google Patents
Unmanned aerial vehicle adopting full-dynamic elevator Download PDFInfo
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- CN112429199B CN112429199B CN202011297716.4A CN202011297716A CN112429199B CN 112429199 B CN112429199 B CN 112429199B CN 202011297716 A CN202011297716 A CN 202011297716A CN 112429199 B CN112429199 B CN 112429199B
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
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Abstract
The application relates to the technical field of unmanned aerial vehicle pneumatic layout, in particular to an unmanned aerial vehicle adopting a full-motion elevator. The unmanned aerial vehicle comprises a vehicle body and a full-motion elevator; the full-motion elevator is arranged at the tail part of the machine body through a rotating shaft; the axis of the rotating shaft extends along the width direction of the machine body; the full-motion elevator comprises a horizontal tail wing and two side wings symmetrically arranged on two sides of the horizontal tail wing; the two side wings are arranged along the width direction of the machine body; the side wing is a curved surface structure which is obliquely arranged along the vertical direction, the bottom end of the side wing is fixedly connected with the horizontal tail wing, and the bottom end of the side wing and the horizontal tail wing form a semi-surrounding structure with an opening facing to the tail part of the machine body; the tail part of the machine body is matched with the opening in shape. Above-mentioned unmanned aerial vehicle adopts the full-motion elevator to replace current unmanned aerial vehicle's fin, vertical tail and elevator, has the characteristics that pneumatic efficiency is high, hinge moment is little, course stability is strong.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicle pneumatic layout, in particular to an unmanned aerial vehicle adopting a full-motion elevator.
Background
Along with the continuous improvement to freight transportation unmanned aerial vehicle performance requirement, freight transportation unmanned aerial vehicle's loading capacity is also higher and higher, and task load weight is more and more heavy, and the organism size is bigger and more. In order to accommodate more and heavier mission loads, the cargo compartments have to be lengthened and widened, correspondingly the wing area needs to be increased, and in order to keep the lift-drag ratio of the airplane high, the aspect ratio of the wing is generally kept, so that the wing chord length is increased, and the fuselage length is increased.
In the prior art, in order to enable an aircraft to have better course stability and pitching maneuverability, measures of increasing the distance between a vertical tail and a gravity center and increasing the distance between an elevator and the gravity center are generally adopted. Under the aircraft length constraint condition that satisfies the transportation requirement of shifting, traditional vertical fin overall arrangement form and elevator overall arrangement form can't satisfy the requirement because of aerodynamic efficiency is lower, if increase vertical fin and elevator's area, then can increase structural weight simultaneously, lead to the problem that can't satisfy big load capacity requirement.
Disclosure of Invention
The application provides an unmanned aerial vehicle who adopts full-motion elevator, this unmanned aerial vehicle adopt full-motion elevator to replace current unmanned aerial vehicle's fin, vertical fin and elevator, have characteristics that pneumatic efficiency is high, hinge moment is little, course stability is strong.
In order to achieve the purpose, the application provides the following technical scheme:
an unmanned aerial vehicle adopting a full-motion elevator comprises a body and the full-motion elevator;
the full-motion elevator is arranged at the tail part of the airframe through a rotating shaft and is used for enabling the full-motion elevator to swing around the rotating shaft so as to control the pitching of the unmanned aerial vehicle;
the shaft axis of the rotating shaft extends along the width direction of the machine body;
the full-motion elevator comprises a horizontal tail wing and two side wings symmetrically arranged on two sides of the horizontal tail wing; the two side wings are arranged along the width direction of the machine body;
the side wings are curved surface structures which are obliquely arranged along the vertical direction, the bottom ends of the side wings are fixedly connected to the horizontal tail wing, and the bottom ends of the side wings and the horizontal tail wing form a semi-surrounding structure with an opening facing the tail of the machine body;
the tail part of the machine body is matched with the opening in shape.
Optionally, the length of the bottom end of the side wing is greater than the length of the horizontal tail wing along the length direction of the fuselage;
the length of the side wings gradually decreases from the bottom ends to the top ends of the side wings, and the distance between the two side wings gradually increases.
Optionally, the length of the bottom end of the side wing is at least twice the length of the horizontal rear wing.
Optionally, the rear end of the side wing remote from the fuselage is flush with the rear end of the horizontal rear wing.
Optionally, the projection shape of the horizontal tail on the horizontal plane is a rectangle;
the projection shape of the side wing on the horizontal plane is trapezoidal.
Optionally, the horizontal rear wing and the two side wings are of an integrally formed structure.
Optionally, the horizontal rear wing and the side wings are made of an aluminum alloy material.
Optionally, the device further comprises a driving device for driving the rotating shaft to rotate;
the rotating shaft is fixedly connected with the two side wings.
Compared with the prior art, the method has the following beneficial effects:
the embodiment of the application provides an unmanned aerial vehicle adopting a full-motion elevator, the unmanned aerial vehicle adopts the full-motion elevator with angle compensation to replace an empennage, a vertical tail and an elevator of the existing unmanned aerial vehicle, the full-motion elevator comprises a horizontal empennage and two side wings symmetrically arranged on the horizontal empennage, the side wings are obliquely arranged along the vertical direction, when the unmanned aerial vehicle flies and crosswinds occur, the full-motion elevator contributes to the unmanned aerial vehicle to improve the lateral deviation moment with stable course, when the full-motion elevator needs to provide pitching moment during flying, the surface pressure of the side wings at the front and the rear of a rotating shaft is uniformly distributed, the hinge moment needing to be overcome by a steering engine is smaller, no structural reinforcement is needed, and the control moment of the full-motion elevator is safely overcome; the full-motion elevator is arranged at the tail, so that the steering engine is convenient to mount, the projection area of the tail rudder is large, the pneumatic efficiency is high, and the moment requirement of flight pitching control can be met under the constraint of the length of the unmanned aerial vehicle; therefore, the unmanned aerial vehicle adopts the full-motion elevating rudder to have the characteristics of high pneumatic efficiency, small hinge moment and strong course stability.
Drawings
Fig. 1 is a schematic perspective view of a tail of an unmanned aerial vehicle according to an embodiment of the present application;
fig. 2 is a top view of the tail structure of the drone of fig. 1;
FIG. 3 is a schematic view of the full action elevator of FIG. 1 during a swing;
fig. 4 is a schematic perspective view of the full-motion elevator of the drone in fig. 1.
Reference numerals:
1-a fuselage; 2-full-motion elevator; 21-horizontal tail; 22-a first side flap; 23-a second flank; 24-opening.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The embodiment of the application provides an unmanned aerial vehicle adopting a full-motion elevator 2, for example, fig. 1 shows a schematic view of a three-dimensional structure of a tail part of the unmanned aerial vehicle provided with the full-motion elevator 2, fig. 2 is a top view of the tail part of the unmanned aerial vehicle provided with the full-motion elevator 2, fig. 3 is a schematic view of the structure of the unmanned aerial vehicle provided with the full-motion elevator 2 when the full-motion elevator 2 is controlled to swing, and fig. 4 is a three-dimensional structure of the full-motion elevator 2 installed in the unmanned aerial vehicle; for convenience of description, the direction from the nose to the tail of the unmanned aerial vehicle is defined as the length direction of the body 1, the vertical direction is defined as the height direction of the body 1, and the direction perpendicular to both the length direction and the height direction of the body 1 is defined as the width direction of the body 1; wherein:
the unmanned aerial vehicle comprises a machine body 1 and a full-motion elevator 2 arranged at the tail part of the machine body 1; the full-motion elevator 2 is arranged at the tail part of the airframe 1 through a rotating shaft (not shown in the figure) and is used for enabling the full-motion elevator 2 to swing around the rotating shaft so as to control the pitching of the unmanned aerial vehicle; the full-motion elevator 2 shown in the structure of fig. 3 is a working state diagram after swinging a certain angle around a rotating shaft;
the axial lead of the rotating shaft extends along the width direction of the machine body 1, so that the full-motion elevator 2 can swing along the clockwise direction or the anticlockwise direction relative to the machine body 1; in order to realize the control of the full-motion elevator 2, the unmanned aerial vehicle can further comprise a driving device for driving the rotating shaft to rotate, the driving device generates driving force for driving the rotating shaft to rotate, the rotating shaft can be an output shaft of the driving device, and the rotating shaft can also be in transmission connection with the output shaft of the driving device through a transmission mechanism; the rotating shaft is fixedly connected with the two side wings and used for transmitting the driving force of the driving device to the side wings, and the whole full-motion elevator 2 is driven by the side wings to realize angle adjustment, so that the control of the lifting force of the unmanned aerial vehicle is realized, and the pitching control of the unmanned aerial vehicle is realized; the rotating shafts can be of an integral structure or a split structure, namely, one rotating shaft is arranged corresponding to each side wing, and the two rotating shafts synchronously rotate;
the full-motion elevator 2 comprises a horizontal tail wing 21 and two side wings symmetrically arranged at two sides of the horizontal tail wing 21, wherein the two side wings are a first side wing 22 and a second side wing 23; the two side wings are arranged along the width direction of the machine body 1; as shown in the structure of fig. 1 and 4, the horizontal rear wing 21 is located right behind the fuselage 1, two side wings are respectively located at two sides of the tail of the fuselage 1, and the two side wings are symmetrically arranged at two sides of the horizontal rear wing 21; the horizontal tail 21 and the two side wings can be of a split structure or an integrally formed structure; the projection shape of the horizontal rear wing 21 on the horizontal plane can be rectangular, trapezoidal or polygonal; the projection shape of the side wing on the horizontal plane can be trapezoid or polygon; the horizontal tail 21 and the side wings can be made of aluminum alloy materials, can also be made of other metal materials or non-metal materials, and can also be made of composite materials;
the side wing is a curved surface structure which is obliquely arranged along the vertical direction, the bottom end of the side wing is fixedly connected with the horizontal tail wing 21, and the bottom end of the side wing and the horizontal tail wing 21 form a semi-surrounding structure with an opening 24 facing the tail part of the fuselage 1; as shown in fig. 1 and 4, the side wing has an included angle with the vertical surface, extends from the horizontal tail wing 21 to be inclined upwards, has an irregular shape, and is of a smooth curved surface structure in order to prevent the stress concentration phenomenon; the bottom end of each side wing is fixedly connected with the horizontal tail wing 21, the top end of each side wing is higher than the horizontal tail wing 21, an opening 24 facing the front end direction of the fuselage 1 is formed by the two side wings and the horizontal tail wing 21 which are oppositely arranged at the bottom of each side wing, the opening 24 is used for accommodating the tail of the fuselage 1, and the tail of the fuselage 1 is matched with the opening 24 in shape.
In an alternative embodiment, as shown in the structure of fig. 1, 2 and 4, the length of the bottom end of the side wing is greater than the length of the horizontal rear wing 21 in the length direction of the fuselage 1, and the length of the bottom end of the side wing may be at least twice as long as the length of the horizontal rear wing 21, i.e., the length of the bottom end of the side wing is not only longer than the length of the horizontal rear wing 21, but also much longer than the length of the horizontal rear wing 21; from the bottom end to the top end of the side wing, the length of the side wing gradually decreases, and the distance between the two side wings gradually increases, that is, the side wing gradually decreases in length from the bottom to the top, and gradually inclines to the outer side of the body 1.
Meanwhile, as shown in the structure of fig. 2, the rear end portion of the side wing, which is far from the fuselage 1, is flush with the rear end portion of the horizontal rear wing 21, that is, although the length of the side wing is longer than that of the horizontal rear wing 21, the rear end portion of the side wing may be in the same vertical plane as the rear end portion of the horizontal rear wing 21.
The unmanned aerial vehicle adopting the structure is provided with the full-motion elevator 2 with angle compensation, a vertical tail in the prior art is eliminated, the full-motion elevator 2 is adopted to replace an empennage, a vertical tail and an elevator of the existing unmanned aerial vehicle, when crosswind occurs in the flight process of the unmanned aerial vehicle, the full-motion elevator 2 provides a lateral deviation moment for enhancing stable course for the unmanned aerial vehicle, when the full-motion elevator 2 is required to provide a pitching moment in the flight process of the unmanned aerial vehicle, the surface pressure of the front flank and the rear flank of a rotating shaft is uniformly distributed, the hinge moment required to be overcome by a steering engine is smaller, structural reinforcement is not required, and the control moment of the full-motion elevator 2 is safely overcome; the full-motion elevator 2 is arranged at the tail, so that the steering engine is convenient to mount, the projection area of the tail rudder is large, the pneumatic efficiency is high, and the moment requirement of flight pitching control can be met under the constraint of the length of the unmanned aerial vehicle; therefore, the unmanned aerial vehicle adopts the full-motion elevator 2 to have the characteristics of high pneumatic efficiency, small hinge moment and strong course stability.
Adopt the unmanned aerial vehicle of above-mentioned structure to have following beneficial effect:
1. the full-motion elevator 2 has large projection area and large longitudinal control moment, and can improve the balancing and operating capability of the unmanned aerial vehicle;
2. the reinforcing structure of the full-motion elevator 2 is light in weight, so that the unmanned aerial vehicle can load larger weight load;
3. the side wings of the full-motion elevator 2 can generate a stable moment under the condition of sideslip, so that a course stable moment is provided when no vertical tail exists, and a vertical tail wing structure can be omitted;
4. the drag produced by the vertical fin is reduced during cruising and flying, the lift-drag ratio is improved, and the flying distance can be increased.
By adopting the structure, the unmanned aerial vehicle solves the contradiction between the efficiency of the unmanned aerial vehicle for large space and large load freight transportation, which is limited by the length and the size of the aircraft, and the efficiency of the elevator. The aerodynamic efficiency of the elevator is improved and the additional structural weight is reduced while the wing area is enlarged. The unmanned aerial vehicle is suitable for being used in the pneumatic layout of carrier-based aircrafts and freight unmanned aerial vehicles needing large-scale transport aircraft for transportation. Compared with the conventional layout freight unmanned aerial vehicle with the same freight capacity, the unmanned aerial vehicle provided by the embodiment of the application has the advantages of lighter structural weight, lower aerodynamic resistance and higher lift-drag ratio.
It will be apparent to those skilled in the art that various changes and modifications may be made in the embodiments of the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (6)
1. An unmanned aerial vehicle adopting a full-motion elevator comprises a machine body and is characterized by further comprising a full-motion elevator;
the full-motion elevator is arranged at the tail part of the airframe through a rotating shaft and is used for enabling the full-motion elevator to swing around the rotating shaft so as to control the pitching of the unmanned aerial vehicle;
the shaft axis of the rotating shaft extends along the width direction of the machine body;
the full-motion elevator comprises a horizontal tail wing and two side wings symmetrically arranged on two sides of the horizontal tail wing; the two side wings are arranged along the width direction of the machine body;
the side wings are curved surface structures which are obliquely arranged along the vertical direction, the bottom ends of the side wings are fixedly connected to the horizontal tail wing, and the bottom ends of the side wings and the horizontal tail wing form a semi-surrounding structure with an opening facing the tail of the machine body;
the tail part of the machine body is matched with the opening in shape;
the unmanned aerial vehicle also comprises a driving device for driving the rotating shaft to rotate;
the rotating shaft is fixedly connected with the two side wings;
wherein, along the length direction of the fuselage, the bottom length of flank is greater than at least twice the length of tailplane.
2. The drone of claim 1, wherein the lateral wings gradually decrease in length and increase in spacing between the two lateral wings from their bottom ends to their top ends.
3. The drone of claim 2, wherein the wing aft end distal from the fuselage is flush with the tailplane aft end.
4. The unmanned aerial vehicle of claim 2, wherein the horizontal tail has a rectangular projection shape on a horizontal plane;
the projection shape of the side wing on the horizontal plane is trapezoidal.
5. The drone of claim 1, wherein the horizontal tail and the two side wings are of integrally formed construction.
6. The unmanned aerial vehicle of claim 5, wherein the horizontal tail and the side wings are made of an aluminum alloy material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011297716.4A CN112429199B (en) | 2020-11-18 | 2020-11-18 | Unmanned aerial vehicle adopting full-dynamic elevator |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011297716.4A CN112429199B (en) | 2020-11-18 | 2020-11-18 | Unmanned aerial vehicle adopting full-dynamic elevator |
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| CN112429199A CN112429199A (en) | 2021-03-02 |
| CN112429199B true CN112429199B (en) | 2021-09-24 |
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