CN211468780U - Short-distance take-off and landing unmanned conveyor - Google Patents
Short-distance take-off and landing unmanned conveyor Download PDFInfo
- Publication number
- CN211468780U CN211468780U CN201922167148.5U CN201922167148U CN211468780U CN 211468780 U CN211468780 U CN 211468780U CN 201922167148 U CN201922167148 U CN 201922167148U CN 211468780 U CN211468780 U CN 211468780U
- Authority
- CN
- China
- Prior art keywords
- wing
- aerial vehicle
- unmanned aerial
- lift
- landing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model belongs to unmanned cargo airplane field discloses an unmanned cargo airplane of short distance take-off and landing, include: fuselage, preceding wing, rear wing still include: the aircraft comprises a plurality of high-lift propellers arranged at the front edge of a front wing, a plurality of high-lift propellers arranged at the front edge of a rear wing, and two cruise propellers correspondingly arranged at the left wingtip and the right wingtip of the rear wing, wherein each high-lift propeller is a foldable propeller. By adopting the oil-electricity hybrid power scheme, the high-speed slipstream generated by the additionally distributed high-lift propellers on the wings and the rear wing tip cruise propellers improve the pneumatic efficiency and the propulsion efficiency of the unmanned aerial vehicle by means of the energy of the wing tip vortex, thereby realizing the short-distance take-off and landing performance of the unmanned aerial vehicle. In addition, when the transport plane is in level flight and cruise, the distributed high-lift propellers of the front wing and the rear wing stop working and are folded and retracted, and only the cruise propeller at the wing tip of the rear wing works, so that the resistance is reduced, and the energy is reasonably distributed.
Description
Technical Field
The utility model belongs to unmanned cargo airplane field especially relates to an unmanned cargo airplane that is suitable for short distance take off and land.
Background
The difficulty and danger of plateau transportation always restrict the local resident life and the logistics support and guarantee task of the army, especially the Qinghai-Tibet plateau with the average altitude of more than 4000 meters is always an old and hard matter for liberating the logistics guarantee of the military. This dilemma began to alleviate after the Qinghai-Tibet railway was built into a traffic in 2006, 7 months. However, the long way and time consumption of land transportation are always not favorable for rapid military deployment. However, since the service of large-scale transport aircraft in China, such a dilemma is broken, but the requirement of the large-scale transport aircraft on the airport is high (such as the length of a runway), and the altitude environment reduces the take-off and landing performance of the aircraft (such as the take-off and landing sliding distance is lengthened), so that in order to adapt to the plateau airports with various runway lengths, the transport aircraft with short take-off and landing distances needs to be developed.
At present, an active-service fixed wing conveyor with short take-off and landing does not exist, the only conveyor with short take-off and landing is a helicopter, but the plateau environment seriously reduces the capacity of transporting the helicopter, and the helicopter has a low flying speed and is not beneficial to rapid transportation.
There are also various patents on fixed-wing aircraft with vertical take-off and landing functions, such as "a variant high-efficiency small vertical take-off and landing drone using distributed hybrid power" which generates electricity by an internal combustion engine to provide electric energy to propellers distributed on the wings. The problem that the unmanned aerial vehicle is out of control due to failure of a single propeller is avoided by adopting a distributed propeller scheme. However, the distributed power system is not favorably coupled with the aerodynamic components such as wings of the unmanned aerial vehicle, so that the aerodynamic efficiency and the propulsion efficiency of the unmanned aerial vehicle are improved. The short-distance take-off and landing unmanned aerial vehicle adopting distributed duct power also provides electric energy for duct fans distributed on front and rear wings through power generation of an internal combustion engine, the duct fans are located on the upper surfaces of wing trailing edge flaps, the pneumatic efficiency of the wings is improved through the boundary layer of the upper surfaces of the suction wing upper surfaces of duct power sets, and the duct fans can change the thrust direction along with flap deflection to shorten the take-off and landing sliding distance of the unmanned aerial vehicle and the like. But this patent unmanned aerial vehicle duct fan brings great resistance under the state of cruising, and all duct fans all work and have the energy extravagant.
SUMMERY OF THE UTILITY MODEL
For realizing short-distance take-off and landing at plateau airport and overcoming the not enough of current short-distance take-off and landing technique, the utility model provides an adopt wing distributing type high lift screw and wing tip cruise screw's short-distance take-off and landing unmanned aerial vehicle. Adopt oil-electricity hybrid power system scheme, for satisfying the great focus variation range of cargo airplane, pneumatic layout adopts vertical difference in height tandem wing (duck formula) overall arrangement form, and arrange distributed high lift screw respectively in front wing and back wing leading edge, the wingtip arranges the screw that cruises respectively about the back wing, high-speed slipstream that additionally produces the wing through distributed high lift screw and back wing wingtip cruises the screw and improves unmanned aerial vehicle's aerodynamic efficiency and propulsive efficiency with the help of wingtip vortex energy, thereby realize unmanned aerial vehicle short-range take-off and landing performance. In addition, when the transport plane is in level flight and cruise, the distributed high-lift propellers of the front wing and the rear wing stop working and are folded and retracted, and only the cruise propeller at the wing tip of the rear wing works, so that the resistance is reduced, and the energy is reasonably distributed.
The utility model provides a technical scheme that its technical problem adopted is:
a short take-off and landing unmanned aerial vehicle comprising: fuselage, preceding wing, rear wing still include: the aircraft comprises a plurality of high-lift propellers arranged at the front edge of a front wing, a plurality of high-lift propellers arranged at the front edge of a rear wing, and two cruise propellers correspondingly arranged at the left wingtip and the right wingtip of the rear wing, wherein each high-lift propeller is a foldable propeller.
The utility model discloses technical scheme's characteristics and further improvement do:
(1) the high-lift propellers are arranged on the front edge of the front wing and are used for accelerating the airflow velocity on the surface of the front wing when the unmanned transport plane takes off and lands;
the high-lift propellers are arranged on the front edge of the rear wing and are used for accelerating the airflow velocity on the surface of the rear wing when the unmanned transport plane takes off and lands;
two cruise propellers arranged at the left wingtip and the right wingtip of the rear wing are used for providing pulling force or pushing force when the unmanned aerial vehicle flies flatly.
The high-speed slipstream generated by the distributed high-lift propellers additionally to the wings and the rear wing tip cruise propellers improve the pneumatic efficiency and the propulsion efficiency of the unmanned aerial vehicle by means of the energy of wing tip vortexes, so that the short-distance take-off and landing performance of the unmanned aerial vehicle is realized.
In addition, when the transport plane is in level flight and cruise, the distributed high-lift propellers of the front wing and the rear wing stop working and are folded and retracted, and only the cruise propeller at the wing tip of the rear wing works, so that the resistance is reduced, and the energy is reasonably distributed.
(2) Each cruise propeller is driven by a corresponding fuel engine, and each fuel engine drives a set of generators;
each high-lift propeller is driven by a corresponding motor;
the electric energy output by one set of generators provides a power source for half of the motors corresponding to all the high-lift propellers.
(3) Four high-lift propellers are arranged at the front edge of the front wing and are arranged at equal intervals from left to right;
six high-lift propellers are arranged at the front edge of the rear wing and are arranged at equal intervals from left to right.
(4) The fuselage is in streamline layout with the lower front end and the higher rear end, the front wings traverse the front end of the fuselage, and the rear wings traverse the rear end of the fuselage;
the pneumatic layout adopts a vertical height difference tandem wing duck type layout form, and the height difference of the front wing and the rear wing is arranged to reduce the interference of front wing airflow on the rear wing, so that the larger gravity center change range of the conveyor is met. In addition, the rear wing is higher in ground clearance, so that the rear cabin door is convenient to design, and goods and personnel can be far away from the propeller when entering and exiting from the rear cabin door.
The short-distance take-off and landing unmanned aerial vehicle further comprises: two elevators, two flaperons, two flaps, vertical tails and rudders;
the two elevators are respectively arranged at the left and right rear edge positions of the front wing, the two flaperons are respectively arranged at the left and right outer rear edge positions of the rear wing, the two flaps are respectively arranged at the left and right inner rear edge positions of the rear wing, the vertical fin is arranged right above the tail of the airplane body, and the rudder is arranged at the rear edge of the vertical fin.
(5) Two elevators are mounted at the left and right rear edges of the front wing in an articulated manner and used for taking off and landing of the unmanned transport plane and controlling the pitching direction in flight.
(6) The two flaperons are arranged at the rear edge positions of the left and right outer sides of the rear wing in a hinged mode and are used for controlling the rolling direction of the unmanned transport plane in flight.
(7) Two flaps are mounted at the rear edge positions of the left inner side and the right inner side of the rear wing in a hinged mode and used for controlling the pitching direction of the unmanned transport plane during taking off and landing and flying.
(8) And the rudder is arranged at the rear edge of the vertical tail in a hinged mode and is used for controlling the yaw direction of the unmanned transport plane in flight.
The rotation of the elevator at-35 to +35 degrees, the rotation of the flaperon and the flap at-30 to +30 degrees and the rotation of the rudder at-25 to +25 degrees are realized by a driving mechanism in the wing.
Compared with the prior art, the utility model discloses an adopt unmanned transport plane of short take-off and landing of wing distributing type high lift screw and wingtip cruise screw combines boundary layer swallowing technique (BLI), thereby works through the high lift screw of front wing and back wing, thereby makes the air current that flows through front wing and back wing surface improve the aerodynamic efficiency of wing with higher speed, promotes the maximum lift coefficient to shorten unmanned aerial vehicle take-off and landing roll-off distance. In addition, the design of wingtip cruise screw propeller makes the screw do work with the help of the energy rotation of wingtip vortex, can also the energy can be saved when reducing wingtip vortex resistance, promotes unmanned aerial vehicle range and time of navigating. When the unmanned aerial vehicle is cruising and flying flat, only the wingtip cruise propeller works, the distributed high-lift propellers of the front wing and the rear wing stop working, and the blades are folded backwards to reduce the resistance of the flat flight, and meanwhile, the energy of the whole unmanned aerial vehicle is reasonably utilized.
Drawings
FIG. 1 is a schematic structural appearance diagram of an unmanned aerial vehicle in a take-off and landing state;
FIG. 2 is a schematic structural shape diagram of the unmanned aerial vehicle in the efficient cruise state;
in the figure: 1-fuselage, 2-front wing, 3-front wing right elevator, 4-front wing left elevator, 5-front wing right distributed high lift propeller and motor, 6-front wing left distributed high lift propeller and motor, 7-rear wing, 8-rear wing right outboard aileron, 9-rear wing right inboard flap, 10-rear wing left outboard aileron, 11-rear wing left inboard flap, 12-rear wing left propulsion propeller and motor, 13-rear wing right propulsion propeller and motor, 14-rear wing left distributed high lift propeller and motor, 15-rear wing right distributed high lift propeller and motor, 16-vertical tail, 17-rudder, 18-front wing right distributed motor (propeller folded up), 19-front wing left distributed motor (propeller folded up), 20-rear wing right distributed motor (propeller folded and retracted), 21-rear wing left distributed motor (propeller folded and retracted).
Detailed Description
The utility model provides a novel unmanned cargo airplane of short distance take-off and landing, tandem wing duck formula overall arrangement around the cargo airplane adopts, as shown in figure 1: the airplane comprises an airplane body 1, a front wing 2, a rear wing 7, a front wing right elevator 3, a front wing left elevator 4, a rear wing right inner side flap 9, a rear wing left inner side flap 11, a rear wing right outer side aileron 8, a rear wing left outer side aileron 10, a vertical tail 16, a rudder 17, a front wing right distributed high-lift propeller and motor 5, a front wing left distributed high-lift propeller and motor 6, a rear wing left distributed high-lift propeller and motor 14, a rear wing right distributed high-lift propeller and motor 15, a rear wing left propulsion propeller and motor 12, a rear wing right propulsion propeller and motor 13 and the like. The fuselage is in streamline layout with a lower front end and a higher rear end, the front wings cross the front end of the fuselage, the rear wings cross the rear end of the fuselage, and the vertical tails are arranged right above the tail part of the fuselage. The front wing and the rear wing are arranged in a height difference mode to reduce interference of airflow of the front wing on the rear wing, the rear wing is higher in ground clearance, a rear cabin door is conveniently designed, and goods and personnel can be far away from the propeller when entering and exiting from the rear cabin door.
The left and right elevators are arranged at the left and right rear edge positions of the front wing, the left and right flaperons are arranged at the left and right outer rear edge positions of the rear wing, the left and right flaperons are arranged at the left and right inner rear edge positions of the rear wing, the rudders are arranged at the rear edge of the vertical tail, 7 control surfaces are arranged at the rear edge positions of the wings in a hinged mode, the rotation of the elevators at-35 degrees to +35 degrees, the rotation of the flaperons and the flaperons at-30 degrees to +30 degrees and the rotation of the rudders at-25 degrees to +25 degrees are realized through a driving mechanism inside the wings.
The front wing distributed high-lift propellers and the motors are arranged on the front wing front edge in a bilateral symmetry mode, the left and right groups of the front wing distributed high-lift propellers and the motors are arranged on the left and right sides at equal intervals, the left and right groups of the rear wing distributed high-lift propellers and the motors are arranged on the rear wing front edge in a bilateral symmetry mode, the left and right groups of the rear wing distributed high-lift propellers and the motors are arranged at equal intervals, all the high-lift propellers are driven.
The left and right cruise propellers and the fuel oil engines are respectively arranged at the left and right wingtips of the rear wing, the cruise propellers are driven by the fuel oil engines, each fuel oil engine is provided with a set of generator, and the electric energy output by the generators provides a power source for the motor of the high-lift propeller.
The utility model discloses a wing distributing type high lift screw and wingtip cruise screw short-distance take-off and landing unmanned transport plane divide into short-distance take-off stage, high-efficient cruise stage and short-distance landing stage, and the flight process as follows:
as shown in fig. 1: in the short take-off stage, four groups of high-lift propeller blades on the left and right of the front edge of the front wing are unfolded, six groups of high-lift propeller blades on the left and right of the front edge of the rear wing are unfolded, engines at the tips of the left and right wingtips of the rear wing are started, power is supplied to all the high-lift propellers of the front wing and the rear wing after power generation and network throwing of a generator, flaperon and flaps of the rear wing are deflected to the maximum position, an engine accelerator is increased, the unmanned aerial vehicle starts to roll off, at the moment, airflow flows over the upper surfaces of the front wing and the rear wing at high speed due to the action of the high-lift propellers, and the front wing and the rear wing can reach higher lift force under the condition of low rolling speed, so that the.
As shown in fig. 2: in the efficient cruise stage, when the unmanned aerial vehicle finishes taking off and climbing to enter the cruise stage, the motors of the high-lift propellers at the front edges of the front wing and the rear wing are completely turned off, only the wingtip cruise propeller and the engine are allowed to work, necessary thrust is provided for the unmanned aerial vehicle to fly flatly, and the energy of the whole aircraft is reasonably distributed. And all the high-lift propellers can be folded backwards after stopping working, so that the flat flight resistance is reduced.
In the short-distance landing stage, when the unmanned aerial vehicle needs to land, all the high-lift propellers on the front edges of the front wings and the rear wings are unfolded and the propeller motors are started, so that all the high-lift propellers rotate at a high speed, the flow velocity of the upper wing surfaces of the front wings and the rear wings is accelerated, the lift coefficient is improved, the landing grounding speed of the unmanned aerial vehicle can be reduced, and the sliding distance on the ground is reduced.
Claims (10)
1. A short take-off and landing unmanned aerial vehicle comprising: fuselage, preceding wing, rear wing, its characterized in that, short distance take-off and landing unmanned transport aircraft still includes: the aircraft comprises a plurality of high-lift propellers arranged at the front edge of a front wing, a plurality of high-lift propellers arranged at the front edge of a rear wing, and two cruise propellers correspondingly arranged at the left wingtip and the right wingtip of the rear wing, wherein each high-lift propeller is a foldable propeller.
2. The short take-off and landing unmanned aerial vehicle of claim 1,
the high-lift propellers are arranged on the front edge of the front wing and are used for accelerating the airflow velocity on the surface of the front wing when the unmanned transport plane takes off and lands;
the high-lift propellers are arranged on the front edge of the rear wing and are used for accelerating the airflow velocity on the surface of the rear wing when the unmanned transport plane takes off and lands;
two cruise propellers arranged at the left wingtip and the right wingtip of the rear wing are used for providing pulling force or pushing force when the unmanned aerial vehicle flies flatly.
3. The short take-off and landing unmanned aerial vehicle of claim 1, wherein: the front wing traverses the front end of the fuselage, the rear wing traverses the rear end of the fuselage, the front wing and the rear wing are arranged in a height difference manner, and the fuselage is in a streamline layout with a lower front end and a higher rear end.
4. The unmanned aerial vehicle of claim 1, wherein each cruise propeller is driven by a respective fuel-powered engine, and each fuel-powered engine drives a set of generators;
each high-lift propeller is driven by a corresponding motor;
the electric energy output by the set of generators provides a power source for half of the motors corresponding to all the high-lift propellers.
5. The short take-off and landing unmanned aerial vehicle of claim 1,
four high-lift propellers are arranged at the front edge of the front wing and are arranged at equal intervals from left to right;
six high-lift propellers are arranged at the front edge of the rear wing and are arranged at equal intervals from left to right.
6. The unmanned aerial vehicle for short take-off and landing according to claim 1, wherein the fuselage is in a streamline layout with a lower front end and a higher rear end, the front wings traverse the front end of the fuselage, and the rear wings traverse the rear end of the fuselage;
the short take-off and landing unmanned aerial vehicle further comprises: two elevators, two flaperons, two flaps, vertical tails and rudders;
the two elevators are respectively arranged at the left and right rear edge positions of the front wing, the two flaperons are respectively arranged at the rear edge positions of the left and right outer sides of the rear wing, the two flaps are respectively arranged at the rear edge positions of the left and right inner sides of the rear wing, the vertical fin is arranged right above the tail part of the airplane body, and the rudder is arranged at the rear edge of the vertical fin.
7. The short take-off and landing unmanned aerial vehicle of claim 6, wherein the two elevators are mounted in an articulated manner at the left and right trailing edges of the front wing for unmanned aerial vehicle take-off and landing and pitch-in-flight steering.
8. The transport plane of claim 6, wherein said two flaperons are hingedly mounted at the rear edge positions on the left and right outer sides of the rear wing for roll direction control during flight of the transport plane.
9. The unmanned aerial vehicle of claim 6, wherein the two flaps are hingedly mounted at the trailing edge positions on the left and right inner sides of the rear wing for unmanned aerial vehicle takeoff and landing and pitch direction control during flight.
10. The unmanned aerial vehicle of claim 6, wherein the rudder is mounted at the trailing edge of the vertical tail in an articulated manner for controlling the yaw direction of the unmanned aerial vehicle in flight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922167148.5U CN211468780U (en) | 2019-12-05 | 2019-12-05 | Short-distance take-off and landing unmanned conveyor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922167148.5U CN211468780U (en) | 2019-12-05 | 2019-12-05 | Short-distance take-off and landing unmanned conveyor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211468780U true CN211468780U (en) | 2020-09-11 |
Family
ID=72367744
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922167148.5U Active CN211468780U (en) | 2019-12-05 | 2019-12-05 | Short-distance take-off and landing unmanned conveyor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211468780U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112455696A (en) * | 2020-12-03 | 2021-03-09 | 中国商用飞机有限责任公司 | Hybrid power airplane |
| CN112572785A (en) * | 2020-12-09 | 2021-03-30 | 中国空气动力研究与发展中心 | High-efficiency front edge distributed propeller aircraft power layout |
| CN112644684A (en) * | 2020-12-23 | 2021-04-13 | 河北利翔航空科技有限公司 | Unmanned conveyer with duck wing and forward swept wing |
| EP3868661A1 (en) * | 2020-02-24 | 2021-08-25 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Fixed-wing short-takeoff-and-landing aircraft and related methods |
| CN115571327A (en) * | 2022-12-07 | 2023-01-06 | 北京启时智航科技有限公司 | Distributed electric propulsion ultra-short take-off and landing fixed-wing aircraft platform |
-
2019
- 2019-12-05 CN CN201922167148.5U patent/CN211468780U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3868661A1 (en) * | 2020-02-24 | 2021-08-25 | Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company | Fixed-wing short-takeoff-and-landing aircraft and related methods |
| CN112455696A (en) * | 2020-12-03 | 2021-03-09 | 中国商用飞机有限责任公司 | Hybrid power airplane |
| CN112572785A (en) * | 2020-12-09 | 2021-03-30 | 中国空气动力研究与发展中心 | High-efficiency front edge distributed propeller aircraft power layout |
| CN112644684A (en) * | 2020-12-23 | 2021-04-13 | 河北利翔航空科技有限公司 | Unmanned conveyer with duck wing and forward swept wing |
| CN115571327A (en) * | 2022-12-07 | 2023-01-06 | 北京启时智航科技有限公司 | Distributed electric propulsion ultra-short take-off and landing fixed-wing aircraft platform |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN211468780U (en) | Short-distance take-off and landing unmanned conveyor | |
| CN108569399B (en) | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power | |
| US20210206487A1 (en) | Aircraft and Modular Propulsion Unit | |
| CN114126966A (en) | Novel aircraft design using tandem wings and distributed propulsion system | |
| CN111268120B (en) | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN106586001A (en) | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration | |
| US11407507B2 (en) | Lift rotor system | |
| CN110217391B (en) | Oil-electricity hybrid power vertical take-off and landing forward-swept fixed wing unmanned aerial vehicle | |
| CN105564633A (en) | Wing flap lift enhancement type joined-wing airplane with approximately horizontal rotation propellers | |
| US11873086B2 (en) | Variable-sweep wing aerial vehicle with VTOL capabilites | |
| CN115489716B (en) | Wing and electric aircraft integrated with distributed ducted fans | |
| CN104973234A (en) | Aircraft using distributed electric ducted fan flap lift-rising system | |
| CN103192981A (en) | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft | |
| CN112896499A (en) | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller | |
| CN205203366U (en) | Approximate level is rotated propeller wing flap lift -rising and is connected wing aircraft | |
| CN213323678U (en) | Power distribution type unmanned aerial vehicle capable of taking off and landing vertically | |
| CN112622548A (en) | Flying automobile | |
| CN218617171U (en) | Multi-rotor aircraft | |
| CN217515371U (en) | Ducted thrust electric vertical take-off and landing composite wing aircraft | |
| CN111532426A (en) | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout | |
| CN113086184B (en) | Tandem distributed electric propulsion coaxial duct vertical take-off and landing aircraft | |
| CN217049016U (en) | Wing interval adjusting module and aircraft comprising same | |
| CN114701640A (en) | Jet wing type full-speed global vertical take-off and landing fixed wing aircraft and control method | |
| CN114852325A (en) | Ducted thrust electric vertical take-off and landing composite wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |