CN108569399A - A kind of short take-off and landing unmanned plane using distributed duct power - Google Patents
A kind of short take-off and landing unmanned plane using distributed duct power Download PDFInfo
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- CN108569399A CN108569399A CN201810315808.7A CN201810315808A CN108569399A CN 108569399 A CN108569399 A CN 108569399A CN 201810315808 A CN201810315808 A CN 201810315808A CN 108569399 A CN108569399 A CN 108569399A
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- wing
- unmanned plane
- duct power
- trailing edge
- landing
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/08—Aircraft not otherwise provided for having multiple wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/60—Take-off or landing of UAVs from a runway using their own power
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
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- Wind Motors (AREA)
- Supply And Distribution Of Alternating Current (AREA)
Abstract
The present invention provides a kind of short take-off and landing unmanned planes using distributed duct power, it is related to air vehicle technique field, the fuselage of the present invention is two, it preceding wing unicom and traverses in two fore-bodies, wing is connected to and traverses in two afterbodies afterwards, vertical tail is separately mounted to right over the tail portion of two fuselages, and the present invention improves the cruise duration of unmanned plane using oil electric mixed dynamic scheme, reduces weight, vibrations and the oil consumption rate of dynamical system；Boundary-layer by being arranged in the duct power packages suction upper surface of the airfoil of wing trailing edge flaps upper surface improves the pneumatic efficiency of wing；The distribution arrangement of dynamical system avoids the problem that single engine breakdown causes unmanned plane out of control, improves the safety of unmanned plane；It drives the deflection of duct power packages to change the ground run distance that thrust direction shortens the unmanned plane landing stage by trailing edge flap, improves the takeoff and landing performance of unmanned plane, expanded the application range of unmanned plane.
Description
Technical field
The present invention relates to air vehicle technique field, especially a kind of short take-off and landing unmanned plane.
Background technology
It is dynamic and electronic two kinds to be broadly divided into oil for the power form of unmanned plane at present, long but starts in oil dynamic unmanned plane cruise duration
Weight, vibrations and the noise of machine are all very big, and the tail gas discharged can cause environmental pollution.Electronic unmanned plane green cleaning,
Light-weight and noise is small, but is limited by current battery technology is horizontal, and dynamical system power is smaller and cruise duration is short.This
Outside, unmanned plane mostly uses single-shot form at present, and engine is installed on head or afterbody, and dynamical system redundancy is low, once
Failure easily leads to unmanned plane crash out of control.To solve the above-mentioned problems, existing patented technology such as application number
201710123934.8 Chinese invention patent discloses that " a kind of variant efficient small using distributed hybrid power vertically rises
Unmanned plane drops ", the propeller to be distributed on wing that generated electricity by internal combustion engine provides electric energy, makes it while there is oil to move nobody
The advantages of machine and electronic unmanned plane.Avoiding single propeller failure by using distributed propeller scheme causes unmanned plane to lose
The problem of control.But the patent does not couple the dynamical system of distribution in turn favorably with Pneumatic components progress such as the wings of unmanned plane
Improve the pneumatic efficiency and propulsive efficiency of unmanned plane.
Invention content
For overcome the deficiencies in the prior art, the present invention propose a kind of short take-off and landing using distributed duct power nobody
Machine, using oil electric mixed dynamic system scheme, aerodynamic arrangement uses twin fuselage tandem wing distribution form, duct power packages is distributed
In the top airfoil of the trailing edge flap of forward and backward wing, the pneumatic of unmanned plane is improved by wing and the coordination arrangement of duct power packages
Efficiency and propulsive efficiency.The wing trailing edge flaps that duct power packages are installed by deflection change the thrust direction reality of duct power packages
Existing unmanned plane short take-off and landing.
The technical solution adopted by the present invention to solve the technical problems is：
A kind of short take-off and landing unmanned plane using distributed duct power, including fuselage, preceding wing, rear wing, the rear flap
The wing, elevator, aileron, nose-gear, main landing gear, vertical tail, rudder, duct power packages and generator bay, wherein machine
As two, and fuselage be smaller than before wing span length, two fuselages are longitudinally placed side by side, preceding wing unicom and traverse in
Two fore-bodies, the connection of rear wing and are traversed in two afterbodies, and two vertical tails are separately mounted to two fuselages
Right over tail portion, two nose-gears are separately mounted to the lower front of two fuselages, and two main landing gears are separately mounted to two
The lower rear of a fuselage；
Elevator is mounted on the left right lateral posterior border position of preceding wing, and aileron is mounted on the left right lateral rear position of rear wing
It sets, trailing edge flap shares 4, is mounted in preceding wing wing panel in the posterior border position, rear wing of wing panel respectively with articulated form
The posterior border position of posterior border position and rear wing or so outer panel realizes trailing edge flap with respect to machine by the driving mechanism inside wing
0~90 ° of thriving face rotates, and rudder is equipped on rear side of vertical tail, and generator bay is installed on the root of vertical tail,
Turbogenerator is installed, turbine engine combustion fuel oil drives generator operation to provide electricity for duct power packages in generator bay
Energy.
The duct power packages share 4 groups, are separately mounted to the top airfoil of four trailing edge flaps, and every group of duct power packages are equal
Including 4~10 duct power units, each duct power unit includes duct, motor, electron speed regulator and propeller, duct
Power packages are deflected with trailing edge flap changes thrust direction.
It is 8~16 that the preceding wing and rear wing, which use the straight wing formula of high aspect ratio, aspect ratio, and angle of sweep is 0 °,
The upper counterangle is 0~10 °.
The present invention improves the cruise duration of unmanned plane using oil electric mixed dynamic scheme, reduces the weight of dynamical system
Amount, vibrations and oil consumption rate；Duct power packages by being arranged in wing trailing edge flaps upper surface aspirate upper surface of the airfoil
Boundary-layer improves the pneumatic efficiency of wing；The distribution arrangement of dynamical system, which avoids single engine breakdown, leads to nobody
Machine problem out of control, improves the safety of unmanned plane；The deflection of duct power packages is driven to change thrust direction by trailing edge flap
The ground run distance for shortening the unmanned plane landing stage improves the takeoff and landing performance of unmanned plane, has expanded the application range of unmanned plane.
Description of the drawings
Fig. 1 is unmanned plane structural schematic diagram under efficient cruising condition；
Fig. 2 is unmanned plane structure upward view under efficient cruising condition；
Fig. 3 is unmanned plane structural schematic diagram under VTOL state；
Fig. 4 is unmanned plane structure upward view under VTOL state.
In figure：1- fuselages, wing before 2-, wing after 3-, 4- trailing edge flaps, 5- elevators, 6- ailerons, 7- nose-gears,
8- main landing gears, 9- vertical tails, 10- rudders, 11- duct power packages, 12- generator bays.
Specific implementation mode
Present invention will be further explained below with reference to the attached drawings and examples.
A kind of short take-off and landing unmanned plane using distributed duct power, including fuselage, preceding wing, rear wing, the rear flap
The wing, elevator, aileron, nose-gear, main landing gear, vertical tail, rudder, duct power packages and generator bay, wherein machine
As two, and fuselage be smaller than before wing span length, two fuselages are longitudinally placed side by side, preceding wing unicom and traverse in
Two fore-bodies, the connection of rear wing and are traversed in two afterbodies, and two vertical tails are separately mounted to two fuselages
Right over tail portion, two nose-gears are separately mounted to the lower front of two fuselages, and two main landing gears are separately mounted to two
The lower rear of a fuselage；
The elevator is mounted on the left right lateral posterior border position of preceding wing, is used for unmanned plane landing and in-flight pitching
The manipulation in direction；The aileron is mounted on the left right lateral posterior border position of rear wing, for unmanned plane landing and in-flight
Roll guidance；The trailing edge flap shares 4, respectively with articulated form be mounted on preceding wing in wing panel posterior border position, after
The posterior border position of the posterior border position of wing panel and rear wing or so outer panel in wing, after being realized by the driving mechanism inside wing
0~90 ° rotation of the edge wing flap relative to aerofoil surface.
The duct power packages share 4 groups, are separately mounted to the top airfoil of four trailing edge flaps, and every group of duct power packages are equal
Including 4~10 duct power units, each duct power unit includes duct, motor, electron speed regulator and propeller, duct
Power packages are deflected with trailing edge flap changes thrust direction.
Rudder is installed on rear side of the vertical tail, is used for unmanned plane landing and the in-flight manipulation in course.
The generator bay is installed on the root of vertical tail, and turbogenerator, turbine hair are installed in generator bay
Motivation non-combusted fuels drive generator operation to provide electric energy for the duct power packages being arranged on wing.
The present invention distributed duct power short take-off and landing unmanned plane be divided into the short takeoff stage, efficient cruising phase and
Short landing stage, flight course are as follows：
A, the short takeoff stage provides electricity by four groups of duct power packages on the energy-storage battery in fuselage forwards, backwards wing
Can, four groups of duct power packages are operated under maximum power state；Wherein, before being driven by control mechanism in wing wing and
Afterwards in wing the trailing edge flap of wing panel and the two groups of duct power packages installed thereon deflect down 90 ° to and horizontal plane, be
Unmanned plane provides the thrust of vertical direction；The two groups of duct power packages installed on the trailing edge flap of wing or so outer panel afterwards are kept
Horizontal direction provides forward thrust for unmanned plane；Slide after running that unmanned plane is liftoff takes off by short distance, when unmanned plane rise to it is pre-
The trailing edge flap of wing panel in preceding wing and rear wing is controlled by the control mechanism installed in wing after determining height and is installed thereon
Two groups of duct power packages deflect back to horizontal position, four groups of power packages continuously decrease power to the required horsepower that cruises.
B, efficient cruising phase, the turbogenerator in generator bay drive generator operation, generated electric energy one
The energy-storage battery being diverted into fuselage charges, and another part is four groups of duct power packages energy supply on front and back wing, at this time
Positioned at trailing edge position duct power packages by aspirate upper surface of the airfoil boundary-layer air-flow improve wing pneumatic efficiency.
C, the short landing stage controls the trailing edge flap of wing panel in preceding wing and rear wing by the control mechanism in wing
Drive duct power packages thereon deflect down 90 ° to and horizontal plane, the thrust of vertical direction is provided for unmanned plane, gradually
The power of two groups of duct power packages after reduction on the trailing edge flap of wing or so outer panel makes unmanned plane gradually slow down and reduce
Height to ground connection completes landing operation.
It is 8~16 that the preceding wing and rear wing, which use the straight wing formula of high aspect ratio, aspect ratio, and angle of sweep is 0 °,
The upper counterangle is 0~10 °.
As Figure 1-Figure 4, the present embodiment uses the short take-off and landing unmanned plane of distributed duct power, by fuselage, preceding machine
The wing, rear wing, trailing edge flap, elevator, aileron, nose-gear, main landing gear, vertical tail, rudder, duct power packages and
Generator bay forms；The middle part section of fuselage is rounded corner rectangle, is respectively forwardly tapered backward at head and tail；Preceding wing
Simultaneously mounted on the lower front of two fuselages, aspect ratio 8.93, angle of sweep is 0 °, and the upper counterangle is 0 °；Wing is simultaneously afterwards
Mounted on the upper rear of two fuselages, aspect ratio 13.60, angle of sweep is 0 °, and the upper counterangle is 0 °；Before elevator is mounted on
The left right lateral posterior border position of wing；Aileron is mounted on the left right lateral posterior border position of rear wing；4 trailing edge flaps are with hinged shape
Formula is separately mounted to the posterior border position of the interior wing panel of the posterior border position of the interior wing panel of preceding wing, rear wing and rear wing or so outer wing
The posterior border position of section realizes 0~90 ° rotation of the trailing edge flap relative to aerofoil surface by the driving mechanism inside wing；Every
Respectively one group of duct power packages of installation, every group of duct power packages include 6 duct power units to the top airfoil of a trailing edge flap, often
A duct power unit includes duct, motor, electron speed regulator and propeller, and duct power packages change with trailing edge flap deflection to be pushed away
Force direction；Two vertical tails are respectively arranged in the upper rear of two fuselages；Rudder is installed at the rear portion of vertical tail；
Two generator bays are respectively arranged in the root of two vertical tails；Two nose-gears are separately mounted to the front of two fuselages
Lower section, two main landing gears are separately mounted to the lower rear of two fuselages.
When a certain motor in flight course in duct power packages breaks down, the present invention is using distributed duct power
Short take-off and landing unmanned plane the thrust at left and right sides of unmanned plane can be made to keep flat by adjusting the output power of remaining each motor
Weighing apparatus, ensures the flight safety of unmanned plane.
Claims (2)
1. a kind of short take-off and landing unmanned plane using distributed duct power, it is characterised in that：
The short take-off and landing unmanned plane of the distributed duct power, including fuselage, preceding wing, rear wing, trailing edge flap, lifting
Rudder, aileron, nose-gear, main landing gear, vertical tail, rudder, duct power packages and generator bay, wherein fuselage two
It is a, and fuselage be smaller than before wing span length, two fuselages are longitudinally placed side by side, preceding wing unicom and traverse in two machines
Body front, rear wing are connected to and traverse in two afterbodies, and two vertical tails are being separately mounted to the tail portion of two fuselages just
Top, two nose-gears are separately mounted to the lower front of two fuselages, and two main landing gears are separately mounted to two fuselages
Lower rear；
Elevator is mounted on the left right lateral posterior border position of preceding wing, and aileron is mounted on the left right lateral posterior border position of rear wing,
Trailing edge flap shares 4, is mounted on the rear of wing panel in the posterior border position, rear wing of wing panel in preceding wing with articulated form respectively
The posterior border position of position and rear wing or so outer panel realizes trailing edge flap with respect to the wing wing by the driving mechanism inside wing
0~90 ° of face rotates, and is equipped with rudder on rear side of vertical tail, generator bay is installed on the root of vertical tail, is generating electricity
Turbogenerator is installed, turbine engine combustion fuel oil drives generator operation to provide electric energy for duct power packages in cabin；
The duct power packages share 4 groups, are separately mounted to the top airfoil of four trailing edge flaps, and every group of duct power packages include
4~10 duct power units, each duct power unit include duct, motor, electron speed regulator and propeller, duct power
Group is deflected with trailing edge flap changes thrust direction.
2. the short take-off and landing unmanned plane according to claim 1 using distributed duct power, it is characterised in that：
It is 8~16 that the preceding wing and rear wing, which use the straight wing formula of high aspect ratio, aspect ratio, and angle of sweep is 0 °, upper anti-
Angle is 0~10 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810315808.7A CN108569399B (en) | 2018-04-10 | 2018-04-10 | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810315808.7A CN108569399B (en) | 2018-04-10 | 2018-04-10 | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power |
Publications (2)
| Publication Number | Publication Date |
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| CN108569399A true CN108569399A (en) | 2018-09-25 |
| CN108569399B CN108569399B (en) | 2022-07-26 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143282A (en) * | 2019-06-18 | 2019-08-20 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aircraft using high aspect ratio twin fuselage Flying-wing |
| CN110228590A (en) * | 2019-06-30 | 2019-09-13 | 郑州航空工业管理学院 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
| CN110450948A (en) * | 2019-08-19 | 2019-11-15 | 西安因诺航空科技有限公司 | A kind of vertically taking off and landing flyer |
| CN110450949A (en) * | 2019-08-19 | 2019-11-15 | 西安因诺航空科技有限公司 | A kind of twin fuselage vertically taking off and landing flyer |
| CN110510116A (en) * | 2019-09-20 | 2019-11-29 | 北京大学 | Rotor and vector propulsion system combined type aircraft |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN111619823A (en) * | 2020-06-02 | 2020-09-04 | 西北工业大学 | Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed |
| CN112722243A (en) * | 2021-01-19 | 2021-04-30 | 西北工业大学 | Distributed electric ducted fan power system for short-distance/vertical take-off and landing |
| CN112896529A (en) * | 2021-03-10 | 2021-06-04 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Auxiliary propulsion device and electric aircraft |
| CN115489716A (en) * | 2022-09-22 | 2022-12-20 | 中国商用飞机有限责任公司 | Wing integrated with distributed ducted fans and electric aircraft |
| FR3135703A1 (en) * | 2022-05-20 | 2023-11-24 | Institut Supérieur De L'aéronautique Et De L'espace | METHOD FOR ACTIVE CONTROL OF WAKE-NACEL INTERACTION AND CORRESPONDING AIRCRAFT |
| FR3135705A1 (en) * | 2022-05-19 | 2023-11-24 | Institut Supérieur De L'aéronautique Et De L'espace | POWERTRAIN, AIRCRAFT AND IMPLEMENTATION AT THE TIME OF TAKEOFF |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143282A (en) * | 2019-06-18 | 2019-08-20 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aircraft using high aspect ratio twin fuselage Flying-wing |
| CN110228590A (en) * | 2019-06-30 | 2019-09-13 | 郑州航空工业管理学院 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
| CN110450948A (en) * | 2019-08-19 | 2019-11-15 | 西安因诺航空科技有限公司 | A kind of vertically taking off and landing flyer |
| CN110450949A (en) * | 2019-08-19 | 2019-11-15 | 西安因诺航空科技有限公司 | A kind of twin fuselage vertically taking off and landing flyer |
| CN110510116A (en) * | 2019-09-20 | 2019-11-29 | 北京大学 | Rotor and vector propulsion system combined type aircraft |
| CN111268120B (en) * | 2020-03-11 | 2022-03-22 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN111619823A (en) * | 2020-06-02 | 2020-09-04 | 西北工业大学 | Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed |
| CN112722243A (en) * | 2021-01-19 | 2021-04-30 | 西北工业大学 | Distributed electric ducted fan power system for short-distance/vertical take-off and landing |
| CN112722243B (en) * | 2021-01-19 | 2022-11-11 | 西北工业大学 | Distributed electric ducted fan power system for short-distance/vertical take-off and landing |
| CN112896529A (en) * | 2021-03-10 | 2021-06-04 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Auxiliary propulsion device and electric aircraft |
| FR3135705A1 (en) * | 2022-05-19 | 2023-11-24 | Institut Supérieur De L'aéronautique Et De L'espace | POWERTRAIN, AIRCRAFT AND IMPLEMENTATION AT THE TIME OF TAKEOFF |
| FR3135703A1 (en) * | 2022-05-20 | 2023-11-24 | Institut Supérieur De L'aéronautique Et De L'espace | METHOD FOR ACTIVE CONTROL OF WAKE-NACEL INTERACTION AND CORRESPONDING AIRCRAFT |
| CN115489716A (en) * | 2022-09-22 | 2022-12-20 | 中国商用飞机有限责任公司 | Wing integrated with distributed ducted fans and electric aircraft |
| CN115489716B (en) * | 2022-09-22 | 2023-12-29 | 中国商用飞机有限责任公司 | Wing and electric aircraft integrated with distributed ducted fans |
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| Publication number | Publication date |
|---|---|
| CN108569399B (en) | 2022-07-26 |
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