CN104554723A - Fixed-wing unmanned aerial vehicle - Google Patents
Fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN104554723A CN104554723A CN201510044025.6A CN201510044025A CN104554723A CN 104554723 A CN104554723 A CN 104554723A CN 201510044025 A CN201510044025 A CN 201510044025A CN 104554723 A CN104554723 A CN 104554723A
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Abstract
The invention discloses a fixed-wing unmanned aerial vehicle. The fixed-wing unmanned aerial vehicle comprises a fuselage, a pair of wings which is positioned on two sides of the fuselage and symmetrically arranged, and an empennage mechanism positioned on the rear part of the fuselage, wherein a pair of propellers is symmetrically arranged on the outer sides of the leading edges of the pair of wings, and a power driving device for providing power for the rotation of the propellers is arranged in the fuselage; the power driving device comprises a first driving motor, a second driving motor and a battery; a power arm of the first driving motor and a power arm of the second driving motor are respectively connected with different propellers, and the first driving motor and the second driving motor are connected in parallel with the battery. The fixed-wing unmanned aerial vehicle disclosed by the invention has the characteristics of low power, long flight time, convenience in disassembling and assembling, and stability in flight.
Description
Technical field
The present invention relates to a kind of aircraft field, more particularly, particularly relate to a kind of fixed-wing unmanned vehicle.
Background technology
Fixed-wing unmanned vehicle is a kind of based on radio telecommand or the not manned craft by self programming control, and now, fixed-wing unmanned vehicle develops rapidly as a kind of new concept aircraft.Fixed-wing unmanned vehicle is by carrying multiple sensors, and can realize image real-time Transmission, high-risk areas detecting function, be the important supplement of satellite remote sensing and traditional remote sensing.Tradition fixed-wing unmanned vehicle, owing to being subject to the restriction of capacity of cell and power of motor, traditional aircraft only has a machine operation, power demand is large, consumption of current is many, and executing the task after general battery is full of electricity can only continue about 50 minutes, and the time of executing the task is short, and frequently to change battery, affect work efficiency.Therefore, how Appropriate application battery, reduces the operating power of motor, makes full use of External Force Acting in the appropriate case, alleviate motor burden, enable the time of executing the task of fixed-wing unmanned vehicle reasonably extend the development new direction becoming fixed-wing unmanned vehicle.
Summary of the invention
The object of the present invention is to provide a kind of fixed-wing unmanned vehicle, this fixed-wing unmanned vehicle has that power is little, the feature of flight time length, easy accessibility, flight stability.
The technical solution used in the present invention is as follows:
A kind of fixed-wing unmanned vehicle, comprise fuselage, be positioned at a pair wing that fuselage bilateral symmetry is arranged and the empennage mechanism being positioned at fuselage afterbody, a pair screw propeller is symmetrically arranged with outside the leading edge of wing described in a pair, be provided with as propeller rotational provides the Power Drive Unit of power in described fuselage, wherein, described Power Drive Unit comprises the first drive motor, second drive motor and battery, the power arm of described first drive motor is connected from different screw propellers respectively with the power arm of the second drive motor, described first drive motor and the second drive motor are connected in parallel battery.
Further, described first drive motor and the second drive motor are the motor that model is identical.
Further, the upper surface of described wing is from leading edge of a wing projection curved surface, and the lower surface of wing is from leading edge of a wing lower convexity curved surface.
Further, described wing is formed by fixedly connecting with the back segment wing being positioned at wing wing tail side by the leading portion wing being positioned at wing wing root side, the vertical projection of described leading portion wing is rectangle, the vertical projection of described back segment wing is trapezoidal, the leading edge sweep angular range of back segment wing is 7 ~ 10 degree, and the dihedral angle angular range of back segment wing is 2 ~ 5 degree.
Further, the leading edge sweep angle of described back segment wing is 8.6 degree, and the dihedral angle angle of back segment wing is 2.5 degree.
Further, the projection height of described wing and lower convexity height ratio scope are 2 ~ 4:1.
Further, a pair empennage that described empennage mechanism comprises empennage connecting portion and is fixedly connected with empennage connecting portion, empennage described in a pair is symmetrical arranged along the vertical surface of empennage connecting portion line of centers, be provided with the connection chamber be connected with fuselage afterbody in the middle part of described empennage connecting portion, described connection chamber and fuselage afterbody are detachable being fixedly connected with.
Further, described fuselage afterbody is provided with at least 1 fixed plate, and described fixed plate is provided with the check screw be fixed on by fuselage afterbody in connection chamber, described fixed plate shape is identical with connection chamber cavity cross-section shape.
Further, empennage described in a pair is V-shaped to be symmetrical arranged, and the angle angular range of empennage described in a pair is 100 ~ 111 degree.
Further, the material of described fuselage, wing and empennage mechanism is carbon cloth, Ba Ersha cork wood and aviation laminate.
Compared with prior art, the beneficial effect that the present invention has is:
A kind of fixed-wing unmanned vehicle of the present invention by being provided with Power Drive Unit in fuselage, Power Drive Unit comprises the first drive motor, the second drive motor and battery, first drive motor and the second drive motor are respectively two screw propellers provides power first drive motor and the second drive motor to be connected in parallel battery, like this, the drive motor of two low-powers is utilized to instead of a large drive motor job of transmission, the gross horsepower of two low-power drive motor is less than large drive motor power, power is less, and the flight time is longer; By arranging on empennage mechanism, connection chamber and fuselage afterbody are detachable to be fixedly connected with, and enables empennage mechanism fast speed from fuselage dismounting or is mounted to fuselage, convenient carrying or use; Wing is by being positioned at leading portion wing and back segment wing is formed by fixedly connecting, the vertical projection of leading portion wing is rectangle, the vertical projection of described back segment wing is trapezoidal, the leading-edge sweep of back segment wing and anti-upper, better alleviate the stressed of the windward side of wing, avoid breakking away, unmanned vehicle is flown more stable.
Accompanying drawing explanation
Fig. 1 is structural representation Fig. 1 of the present invention;
Fig. 2 is structural representation Fig. 2 of the present invention;
Fig. 3 is wing profile figure of the present invention;
Fig. 4 is the structural representation of empennage mechanism of the present invention.
Detailed description of the invention
Below in conjunction with detailed description of the invention, technical scheme of the present invention is described in further detail, but does not form any limitation of the invention.
With reference to shown in Fig. 1 ~ 4, a kind of fixed-wing unmanned vehicle of the present invention, comprise fuselage 1, be positioned at a pair wing 2 that fuselage 1 bilateral symmetry is arranged and the empennage mechanism 3 being positioned at fuselage 1 rear portion, a pair screw propeller 4 is symmetrically arranged with outside the leading edge of a pair wing 2, be provided with as screw propeller 4 rotates the Power Drive Unit 5 providing power in fuselage 1, wherein, Power Drive Unit 5 comprises the first drive motor 51, second drive motor 52 and battery 53, the power arm of the first drive motor 51 is connected from different screw propellers 4 respectively with the power arm of the second drive motor 52, first drive motor 51 and the second drive motor 52 are connected in parallel battery 53.Traditional fixed-wing unmanned vehicle uses a high-performance drive motor to drive the rotation of two screw propellers, power is relatively large, fixed-wing unmanned vehicle of the present invention utilizes the drive motor of two low-powers to drive two propeller rotational respectively, the gross horsepower of two low-power drive motor is less than high-power driving power of motor, power is less, when battery is constant, the aircraft flight time is longer.
First drive motor 51 is the motor that model is identical with the second drive motor 52, like this, can ensure that power and the rotating speed of the first drive motor 51 and the second drive motor 52 are consistent, make velocity of rotation during two propeller works identical, the front pulling force produced is consistent, avoids aircraft, because of flight thrust overbalance, course deviation occurs.
The upper surface of wing 2 is from wing 2 leading edge projection curved surface 6, and the lower surface of wing 2 is from wing 2 leading edge lower convexity curved surface 7.Projection curved surface 6 and the lower convexity curved surface 7 of this spline structure, can make the static pressure of lower convexity curved surface 7 be greater than projection curved surface 6 static pressure, makes aircraft better rise.
Wing 2 is formed by fixedly connecting with the back segment wing 9 being positioned at wing 2 wing tail side by the leading portion wing 8 being positioned at wing 2 wing root side, the vertical projection of leading portion wing 8 is rectangle, the vertical projection of back segment wing 9 is trapezoidal, the leading edge sweep angular range of back segment wing 9 is 7 ~ 10 degree, and the dihedral angle angular range of back segment wing 9 is 2 ~ 5 degree.By by back segment wing 9 leading-edge sweep, alleviate the forward space resistance of wing, and by anti-on back segment wing 9, if aircraft is when flying, the wind area that the dihedral angle can make aircraft meet to side, sideslip direction wing is more much bigger than opposite side wing area, makes aircraft produce the strength of oppositely breakking away, thus reach the effect revised rapidly and break away, unmanned vehicle flight is more stable, and when unmanned vehicle of the present invention performs and takes photo by plane, captured picture effect is better.The wing structure of unmanned vehicle of the present invention can also make aircraft glide, and decreases part flying power, extends mission time.
The leading edge sweep angle of back segment wing 9 is 8.6 degree, and the dihedral angle angle of back segment wing 9 is 2.5 degree.Utilizing the sweepback angle of back segment wing 9, wing 2 forward space resistance when flying can being reduced; The best results utilizing the dihedral angle degree of back segment wing 3 to make the correction of wing 2 to break away, stress balance is best.
Projection height and the lower convexity height ratio scope of wing 2 are 2 ~ 4:1, the projection height of wing 2 and lower convexity height ratio within the scope of this, make the static pressure of lower convexity curved surface 7 and projection curved surface 6 static pressure proportion relatively good, make the lift of aircraft better.
A pair empennage 32 that empennage mechanism 3 comprises empennage connecting portion 31 and is fixedly connected with empennage connecting portion 31, empennage 32 described in a pair is symmetrical arranged along the vertical surface of empennage connecting portion 31 line of centers, be provided with the back-connected connection chamber 10 with fuselage 1 in the middle part of empennage connecting portion 31, connection chamber 10 is detachable being fixedly connected with fuselage 1 rear portion.Like this, by detachable being fixedly connected with of connection chamber 10 with fuselage 1 afterbody, empennage mechanism 3 can be dismantled from fuselage or is mounted to fuselage by fast speed, convenient carrying or use; And symmetrically arranged a pair empennage 32 in empennage mechanism 3, both made the better handling of aircraft, the weight of fuselage 1 can have been alleviated again, and made the flight of aircraft more stable.
Fuselage 1 rear portion is provided with at least 1 fixed plate 11, fixed plate 11 is provided with the check screw 12 be fixed at fuselage 1 rear portion in connection chamber 10, fixed by the combination of fixed plate 11 and check screw 12, make empennage mechanism 3 more firmly can be fixed on the rear portion of fuselage 1.Fixed plate 11 shape is identical with connection chamber 10 cavity cross-section shape, makes being bonded with each other of the rear portion of fuselage 1 and connection chamber 10 more tight, relative displacement can not occur, thus have impact on the flight effect of aircraft, make it better handling.
A pair empennage 32 is V-shaped to be symmetrical arranged, now, a pair empennage 32 form respectively horizontal stabilizer and fixed fin, when aircraft be subject to vertically upward or downward aerodynamic force time, horizontal stabilizer makes aircraft produce an antagonistic force moment at the stressed reversing sense of aerodynamic force; When aircraft is subject to level deflection aerodynamic force or to the right left, fixed fin makes aircraft produce an antagonistic force moment at the stressed reversing sense of deflection aerodynamic force, help to regulate aircraft to adjust to the state of original flight, make it better handling, fly more stable.And the deflection aerodynamic force that usual aircraft is subject to is larger, the antagonistic force moment that stabilator produces is larger.When the angle angular range of a pair empennage 32 is 100 ~ 111 degree, the horizontal stabilizer formed and the ratio of fixed fin best, the flight requirement of aircraft can be met.
The material of fuselage 1, wing 2 and empennage mechanism 3 is carbon cloth, Ba Ersha cork wood and aviation laminate, and the vehicle mass utilizing these materials to do is lighter and firm in structure, and flight effect is good.
The foregoing is only preferred embodiment of the present invention, all do within the scope of the spirit and principles in the present invention any amendment, equivalent to replace and improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a fixed-wing unmanned vehicle, comprise fuselage (1), be positioned at a pair wing (2) that fuselage (1) bilateral symmetry is arranged and the empennage mechanism (3) being positioned at fuselage (1) rear portion, a pair screw propeller (4) is symmetrically arranged with outside the leading edge of wing described in a pair (2), be provided with as screw propeller (4) rotates the Power Drive Unit (5) providing power in described fuselage (1), it is characterized in that, described Power Drive Unit (5) comprises the first drive motor (51), second drive motor (52) and battery (53), the power arm of described first drive motor (51) is connected from different screw propellers (4) respectively with the power arm of the second drive motor (52), described first drive motor (51) and the second drive motor (52) are connected in parallel battery (53).
2. a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, described first drive motor (51) and the second drive motor (52) are the identical motor of model.
3. a kind of fixed-wing unmanned vehicle according to claim 1, it is characterized in that, the upper surface of described wing (2) is from wing (2) leading edge projection curved surface (6), and the lower surface of wing (2) is from wing (2) leading edge lower convexity curved surface (7).
4. a kind of fixed-wing unmanned vehicle according to claim 3, it is characterized in that, described wing (2) is formed by fixedly connecting by the leading portion wing (8) being positioned at wing (2) wing root side and the back segment wing (9) that is positioned at wing (2) wing tail side, the vertical projection of described leading portion wing (8) is rectangle, the vertical projection of described back segment wing (9) is trapezoidal, the leading edge sweep angular range of back segment wing (9) is 7 ~ 10 degree, and the dihedral angle angular range of back segment wing (9) is 2 ~ 5 degree.
5. a kind of fixed-wing unmanned vehicle according to claim 4, is characterized in that, the leading edge sweep angle of described back segment wing (9) is 8.6 degree, and the dihedral angle angle of back segment wing (9) is 2.5 degree.
6. a kind of fixed-wing unmanned vehicle according to claim 3, is characterized in that, projection height and the lower convexity height ratio scope of described wing (2) are 2 ~ 4:1.
7. a kind of fixed-wing unmanned vehicle according to claim 1, it is characterized in that, a pair empennage (32) that described empennage mechanism (3) comprises empennage connecting portion (31) and is fixedly connected with empennage connecting portion (31), empennage described in a pair (32) is symmetrical arranged along the vertical surface of empennage connecting portion (31) line of centers, described empennage connecting portion (31) middle part is provided with and fuselage (1) back-connected connection chamber (10), and described connection chamber (10) is detachable being fixedly connected with fuselage (1) rear portion.
8. a kind of fixed-wing unmanned vehicle according to claim 7, it is characterized in that, described fuselage (1) rear portion is provided with at least 1 fixed plate (11), described fixed plate (11) is provided with the check screw (12) be fixed at fuselage (1) rear portion in connection chamber (10), described fixed plate (11) shape is identical with connection chamber (10) cavity cross-section shape.
9. a kind of fixed-wing unmanned vehicle according to claim 7, is characterized in that, empennage described in a pair (32) is V-shaped to be symmetrical arranged, and the angle angular range of empennage described in a pair (32) is 100 ~ 111 degree.
10. a kind of fixed-wing unmanned vehicle according to claim 1, is characterized in that, the material of described fuselage (1), wing (2) and empennage mechanism (3) is carbon cloth, Ba Ersha cork wood and aviation laminate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510044025.6A CN104554723A (en) | 2015-01-28 | 2015-01-28 | Fixed-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510044025.6A CN104554723A (en) | 2015-01-28 | 2015-01-28 | Fixed-wing unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN104554723A true CN104554723A (en) | 2015-04-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510044025.6A Pending CN104554723A (en) | 2015-01-28 | 2015-01-28 | Fixed-wing unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021128674A1 (en) * | 2019-12-27 | 2021-07-01 | 南京祖航航空科技有限公司 | High-strength wing structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2663295Y (en) * | 2003-12-09 | 2004-12-15 | 中山市三乡镇顺达塑胶五金制品厂 | Electric remote controlled airplane controlled by single-chip microcomputer |
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN103434640A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | High-altitude unmanned plane equipped with Magnus effect propulsion system |
| CN103538714A (en) * | 2013-11-06 | 2014-01-29 | 张明 | Vertical take-off and landing model aircraft unmanned aerial vehicle |
-
2015
- 2015-01-28 CN CN201510044025.6A patent/CN104554723A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2663295Y (en) * | 2003-12-09 | 2004-12-15 | 中山市三乡镇顺达塑胶五金制品厂 | Electric remote controlled airplane controlled by single-chip microcomputer |
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN103434640A (en) * | 2013-08-25 | 2013-12-11 | 西北工业大学 | High-altitude unmanned plane equipped with Magnus effect propulsion system |
| CN103538714A (en) * | 2013-11-06 | 2014-01-29 | 张明 | Vertical take-off and landing model aircraft unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021128674A1 (en) * | 2019-12-27 | 2021-07-01 | 南京祖航航空科技有限公司 | High-strength wing structure |
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Application publication date: 20150429 |