CN109733599A - A kind of combined dual-purpose unmanned plane - Google Patents
A kind of combined dual-purpose unmanned plane Download PDFInfo
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- CN109733599A CN109733599A CN201910144258.1A CN201910144258A CN109733599A CN 109733599 A CN109733599 A CN 109733599A CN 201910144258 A CN201910144258 A CN 201910144258A CN 109733599 A CN109733599 A CN 109733599A
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- empennage
- fuselage
- aileron
- unmanned plane
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- 238000010276 construction Methods 0.000 claims abstract description 17
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 54
- 229910052799 carbon Inorganic materials 0.000 claims description 54
- 230000005484 gravity Effects 0.000 claims description 13
- 230000033001 locomotion Effects 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 4
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 2
- 239000007787 solid Substances 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract 1
- 239000002131 composite material Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 238000005194 fractionation Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004584 weight gain Effects 0.000 description 1
- 235000019786 weight gain Nutrition 0.000 description 1
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Abstract
The invention discloses a kind of combined dual-purpose unmanned planes, belong to unmanned plane equipment technical field.Combined dual-purpose unmanned plane includes the fuselage and an empennage and two ailerons of four axle construction；Fuselage afterbody is equipped with the motor of horizontal thrust, and aileron can be plugged into the two sides of the fuselage, the pluggable rear end to the fuselage of empennage respectively；It is more rotor modes after disassembly aileron and empennage；It connects aileron and empennage is fixed-wing mode.This technology promotes aeroperformance and structural reliability, realizes a tractor serves several purposes, expands the usage scenario of unmanned plane.
Description
Technical field
The invention discloses a kind of combined dual-purpose unmanned planes, belong to unmanned plane equipment technical field.
Background technique
Unmanned plane is a kind of unmanned vehicle that can execute a variety of low latitude tasks.Pass through unmanned plane carry optics phase
The precision measurement equipments such as machine, environmental sensor, realize take photo by plane, survey and draw, emergency management and rescue, the fields such as environment inspection are extensively answered
With.
Unmanned plane can be divided into 3 major class: the composite wing that multi-rotor unmanned aerial vehicle, fixed-wing unmanned plane and two kinds of structures combine nobody
Machine.Relative motion of the lift of fixed-wing unmanned plane from wing and air, thus fixed-wing unmanned plane must have it is certain
Speed could normal flight.Its advantage is that long endurance, big flight operation can be realized, but disadvantage is that landing condition is high, needs
Barnyard that will be openr and runway etc..Multiple rotors, gesture stability pass through the different rotors of change to multi-rotor unmanned aerial vehicle lift
Revolving speed realize, therefore can VTOL, do not limited by site condition, and can hover or slower flight, realize fine make
Industry.The disadvantage is that efficiency is poor, job area is small.The rotor mode of composite wing unmanned plane is mainly used for landing process, when operation with
Fixed-wing mode flight.
Current unmanned plane specific aim is stronger, usually in actual job, selects unmanned plane type according to specific needs.
If the design of unmanned plane can be advanced optimized, a tractor serves several purposes is realized, will can expand the usage scenario of unmanned plane, improve using effect
Rate.
In the prior art, patent CN206914636U discloses a kind of dual-purpose unmanned plane comprising fuselage, aileron, empennage
With horizontal power motor；Aileron is two two sides for being located at fuselage, can dismantle installation；Empennage setting can be torn open in fuselage afterbody
Unload installation；Composite wing and more rotor two ways operations can be respectively adopted in fuselage afterbody in horizontal power motor.But the case is simultaneously
Undisclosed more possible technique details, and by its attached drawing it is found that its horizontal power motor that fuselage afterbody is arranged in and tail
The wing mutually limits.The reliability of the more preferably aeroperformance and housing construction of solution promotion fixed-wing mode should be taken.
Summary of the invention
The invention discloses a kind of combined dual-purpose unmanned plane, it can be achieved that composite wing and more rotor both of which are flown
Operation.Used technical solution is:
A kind of combined dual-purpose unmanned plane comprising the fuselage and an empennage of four axle construction and two ailerons；It is described
Fuselage constitutes skeleton by carbon pipe comprising longitudinal direction is fixedly installed in the lateral carbon pipe of two side by side, the two side ends of lateral carbon pipe respectively
Each motor of four axle construction is respectively set in carbon pipe, each end of longitudinal carbon pipe；
The rear portion of the fuselage is equipped with the motor of horizontal thrust, is located between two longitudinal carbon pipes；
The aileron is equipped with two aileron carbon pipes side by side as skeleton；The aileron carbon pipe, the transverse direction of outer diameter and fuselage
The matching of carbon bore, and position is corresponding therewith, makes aileron that can be plugged into the two sides of the fuselage respectively；
The empennage comprising two empennage carbon pipes side by side and the aerofoil being fixed between empennage carbon pipe；The empennage carbon pipe,
Its outer diameter is matched with longitudinal carbon bore of fuselage, and position is corresponding therewith, makes the pluggable rear end to the fuselage of empennage；
It is more rotor modes after disassembly aileron and empennage；It connects aileron and empennage is fixed-wing mode.
Further, the empennage comprising two aerofoils form inverted V-shaped shape/positive V-shape, two side ends and the tail
Wing carbon pipe is fixedly connected, and constitutes the stern construction of falling V/positive V stern construction.
Further, two aerofoils of the empennage, are respectively equipped with empennage rudder face along side thereafter, to control fixed-wing mould
Lifting and direction when formula；The movement of the empennage rudder face is controlled by steering engine, and the line of the steering engine of empennage is bound to empennage carbon
The outside of pipe, there are corresponding interfaces for fuselage afterbody.
Further, two ailerons, are respectively equipped with aileron rudder face along side thereafter, when controlling fixed-wing mode
Turning；The movement of the aileron rudder face is controlled by steering engine, is stretched in the line embedment aileron of steering engine and from the end face for closing on fuselage
Out, there are corresponding interfaces for the two sides of fuselage.
Further, the aileron and the junction of the fuselage are respectively equipped with that position is opposite and opposite polarity strong magnetic
Iron is attracted after so that the aileron is plugged into the two sides of the fuselage respectively by strong magnet.
Further, the empennage, after the insertion of empennage carbon pipe connects longitudinal carbon pipe of the fuselage, using bolt from cross
To through its lap and by nut check, empennage is made not depart from fuselage.
Further, the fuselage, wherein when the position distribution of each component makes to meet fixed-wing mode unmanned plane entirety
Position of centre of gravity is located on the lift axis of the aileron；And the front-rear position of longitudinal carbon pipe is determined with the position of centre of gravity, make
The diagonal line central point of each motor of four axle construction is overlapped with the position of centre of gravity.
Further, the aileron is EPO material.
Further, the aerofoil of the empennage is EPO material.
The invention has the following advantages: this case realizes a tractor serves several purposes, expands the use of unmanned plane by rationally designing
Scene can meet more diversified mission requirements.And ensure reliability of structure, reduce failure rate；It is removable, it is convenient for collecting
It carries；Excessive parts are dismantled when more rotor modes, mitigate weight, promote continuation of the journey；The aeroperformance of fixed-wing mode is promoted, is improved
Flight efficiency has given full play to the advantage of combined type unmanned plane.
Detailed description of the invention
Attached drawing 1 is the fractionation structural representation of combined dual-purpose unmanned plane of the invention；
Attached drawing 2 is the rearview of combined dual-purpose unmanned plane of the invention；
Attached drawing 3 is aileron end structure illustration of the invention；
Attached drawing 4 is the side view of combined dual-purpose unmanned plane of the invention；
Attached drawing 5 is empennage carbon pipe connection schematic diagram of the invention；
Attached drawing 6 is more rotor mode schematic diagrames of combined dual-purpose unmanned plane of the invention；
Attached drawing 7 is the fixed-wing pattern diagram of combined dual-purpose unmanned plane of the invention.
Specific embodiment
This case is described further below in conjunction with attached drawing:
As shown in Fig. 1, which includes fuselage (2), empennage (4) and two ailerons (1).Fuselage (2)
For a four basic axle construction, skeleton is constituted including two lateral carbon pipes (5) side by side, the two side ends of lateral carbon pipe (5)
It is fixedly installed longitudinal carbon pipe (7), each motor of four axle construction of each end setting of longitudinal carbon pipe (7) respectively.
It is equipped with the motor of horizontal thrust between the longitudinal carbon pipe (7) in two, the rear portion of fuselage (2), it can will when four axis mode flights
Its propeller (3) is laid down.
As shown in attached drawing 1 and 2, aileron (1) is equipped with two aileron carbon side by side corresponding with fuselage transverse direction carbon pipe (5) position
It manages (6) and is used as skeleton；Aileron carbon pipe (6) outer diameter is matched with lateral carbon pipe (5) internal diameter, makes aileron (1) that can be plugged into fuselage respectively
(2) two sides.
As shown in Fig. 3, aileron (1) and the end face of the junction of fuselage (2) are respectively set that position is opposite and polarity phase
Anti- strong magnet (9) is attracted aileron (1) and fuselage (2) directly.It is other to active force because aileron mainly provides upward lift
Almost without so aileron is not fallen off when the suction of strong magnet is enough to ensure flight, and capable of ensureing flexible dismounting performance again.
As shown in attached drawing 1,2 and 4, empennage (4) is the stern construction of falling V, two aerofoils including forming inverted V-shaped shape, inverted V-shaped
The two side ends of aerofoil are fixed on two empennage carbon pipes (8) side by side；Equally, empennage carbon pipe (8) and longitudinal carbon pipe (7) of fuselage are right
It answers, makes the pluggable rear end to fuselage (2) of empennage (4).
As shown in Fig. 5, after longitudinal carbon pipe (7) of empennage carbon pipe (8) insertion connection fuselage, in the overlapping portion of two carbon pipes
Divide using bolt (10) from extending transversely through and being locked with nut (11), does not fall off empennage when flight.
The aerofoil of empennage (4) and the rear of aileron (1) are equipped with rudder face along side, and the movement of each rudder face is controlled by steering engine, empennage
(4) lifting and direction, aileron (1) when controlling fixed-wing mode are turned to realize.The line of empennage steering engine is bound to empennage
The outside of carbon pipe (8), there are corresponding interfaces for fuselage afterbody.In line embedment aileron (1) of aileron steering engine and from closing on fuselage
End face is stretched out, and there are corresponding interfaces for the two sides of fuselage.
The position of each components such as flight control system, each sensor, battery in fuselage (2) is rationally arranged along longitudinal direction, makes to meet
In addition whole position of centre of gravity is located on the lift axis of aileron when fixed-wing mode after the components such as aileron (1), empennage (4)；And
The front-rear position that longitudinal carbon pipe (7) is determined with the position of centre of gravity, makes the diagonal line center of each motor of four axle construction
Point is overlapped with the position of centre of gravity.
Even if the flight structure of four axle construction more meets fixed-wing mode, in favor of the VTOL of fixed-wing mode and outstanding
Stop controlling.Although when more rotor modes, the disassembly of empennage (4) causes center of gravity Forward, and (dismounting of aileron has little influence on center of gravity position
Set), because the weight and its wind being subject to that have reduced aileron (1) and empennage (4) are disturbed, also completely in the control range of four spindle motors
It is interior.
The aerofoil of aileron (1) and empennage (4) is EPO material, to reduce weight gain, and is reduced to the greatest extent plus after empennage (4)
Center of gravity move back.
As shown in Fig. 6, it is more rotor modes after disassembly aileron and empennage, is no different with common multi-rotor unmanned aerial vehicle.It can fit
When adjusting battery location forward, center of gravity is corrected, further promotes four axis flying qualitys.
As shown in Fig. 7, each steering engine line is connected, aileron and empennage and fixation, the spiral of upper horizontal thrust motor are connected
After paddle, retain the VTOL function of more rotor modes, and allows hand over to equal winged fixed-wing mode.
Above description is a specific embodiment of the invention, and each Composition of contents for the essence of the present invention that illustrates not limits
System, person of ordinary skill in the field makes an amendment or deforms to specific embodiment above-mentioned, without departing substantially from essence of the invention.
Claims (9)
1. a kind of combined dual-purpose unmanned plane, fuselage and an empennage and two ailerons including four axle construction；It is special
Sign is that the fuselage constitutes skeleton by carbon pipe comprising the lateral carbon pipe of two side by side, the two side ends of lateral carbon pipe are solid respectively
Fixed that longitudinal carbon pipe is arranged, each motor of four axle construction is respectively set in each end of longitudinal carbon pipe；
The rear portion of the fuselage is equipped with the motor of horizontal thrust, is located between two longitudinal carbon pipes；
The aileron is equipped with two aileron carbon pipes side by side as skeleton；The aileron carbon pipe, the transverse direction of outer diameter and fuselage
The matching of carbon bore, and position is corresponding therewith, makes aileron that can be plugged into the two sides of the fuselage respectively；
The empennage comprising two empennage carbon pipes side by side and the aerofoil being fixed between empennage carbon pipe；The empennage carbon pipe,
Its outer diameter is matched with longitudinal carbon bore of fuselage, and position is corresponding therewith, makes the pluggable rear end to the fuselage of empennage；
It is more rotor modes after disassembly aileron and empennage；It connects aileron and empennage is fixed-wing mode.
2. combined dual-purpose unmanned plane as described in claim 1, which is characterized in that the empennage comprising two aerofoil groups
At inverted V-shaped shape/positive V-shape, two side ends are fixedly connected with the empennage carbon pipe, constitute the stern construction of falling V/positive V stern construction.
3. combined dual-purpose unmanned plane as claimed in claim 2, which is characterized in that two aerofoils of the empennage, thereafter edge
While be respectively equipped with empennage rudder face, to when controlling fixed-wing mode lifting and direction；The movement of the empennage rudder face is by rudder
Machine control, the line of the steering engine of empennage are bound to the outside of empennage carbon pipe, and there are corresponding interfaces for fuselage afterbody.
4. combined dual-purpose unmanned plane as described in claim 1, which is characterized in that two ailerons, thereafter along side point
Not She You aileron rudder face, to control turning when fixed-wing mode；The movement of the aileron rudder face is controlled by steering engine, steering engine
It is stretched out in line embedment aileron and from the end face for closing on fuselage, there are corresponding interfaces for the two sides of fuselage.
5. combined dual-purpose unmanned plane as described in claim 1, which is characterized in that the junction of the aileron and the fuselage
It is respectively equipped with that position is opposite and opposite polarity strong magnet, by strong magnetic after making the aileron be plugged into the two sides of the fuselage respectively
Iron is attracted.
6. combined dual-purpose unmanned plane as described in claim 1, which is characterized in that the empennage, the insertion of empennage carbon pipe connect
After connecing longitudinal carbon pipe of the fuselage, using bolt from its lap is extended transversely through and by nut check, do not depart from empennage
Fuselage.
7. combined dual-purpose unmanned plane as described in claim 1, which is characterized in that the fuselage, wherein the position of each component
The whole position of centre of gravity of unmanned plane is located on the lift axis of the aileron when distribution makes to meet fixed-wing mode；And with the center of gravity
Position determines the front-rear position of longitudinal carbon pipe, makes diagonal line central point and the center of gravity position of each motor of four axle construction
Set coincidence.
8. combined dual-purpose unmanned plane as described in claim 1, which is characterized in that the aileron is EPO material.
9. combined dual-purpose unmanned plane as described in claim 1, which is characterized in that the empennage, aerofoil are EPO material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910144258.1A CN109733599A (en) | 2019-02-27 | 2019-02-27 | A kind of combined dual-purpose unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910144258.1A CN109733599A (en) | 2019-02-27 | 2019-02-27 | A kind of combined dual-purpose unmanned plane |
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| CN109733599A true CN109733599A (en) | 2019-05-10 |
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Cited By (4)
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| CN110435895A (en) * | 2019-07-05 | 2019-11-12 | 嘉兴安行信息科技有限公司 | A kind of replaceable unmanned plane load storehouse |
| CN110562452A (en) * | 2019-09-23 | 2019-12-13 | 浙江驭云航空科技有限公司 | Can dismantle VTOL unmanned aerial vehicle of use |
| CN110562448A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | Tailstock type unmanned aerial vehicle |
| CN114852326A (en) * | 2022-05-20 | 2022-08-05 | 成都纵横大鹏无人机科技有限公司 | A modular composite wing unmanned aerial vehicle and quick release connecting assembly |
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| US9120560B1 (en) * | 2011-10-13 | 2015-09-01 | Latitude Engineering, LLC | Vertical take-off and landing aircraft |
| KR20170072069A (en) * | 2015-12-16 | 2017-06-26 | 주식회사 샘코 | Multi-purpose hybrid VTOL UAV with a detachable wings |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110435895A (en) * | 2019-07-05 | 2019-11-12 | 嘉兴安行信息科技有限公司 | A kind of replaceable unmanned plane load storehouse |
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Application publication date: 20190510 |