CN208746231U - A kind of distribution shrouded propeller power vertical take-off and landing drone - Google Patents
A kind of distribution shrouded propeller power vertical take-off and landing drone Download PDFInfo
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- CN208746231U CN208746231U CN201821438002.9U CN201821438002U CN208746231U CN 208746231 U CN208746231 U CN 208746231U CN 201821438002 U CN201821438002 U CN 201821438002U CN 208746231 U CN208746231 U CN 208746231U
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Abstract
The utility model discloses a kind of distributed shrouded propeller power vertical take-off and landing drone, belong to unmanned aerial vehicle scope, using tail sitting posture tandem wing layout designs, cooperate distributed-power bypass system, so that the standby high cruise lift resistance ratio of flying instrument.Distributed-power bypass system is distributed in front wing and rear wing, and front wing moves entirely, so that VTOL and level-flight attitude conversion are safer.Distributed-power vertical take-off and landing drone has the characteristics that low energy consumption, noise is small, wind loading rating is strong, control and safe margin are high, maneuverability is good, cruise duration is long, easy maintenance.
Description
Technical field
The utility model belongs to unmanned plane field, and in particular to a kind of distribution shrouded propeller power is vertical take-off and landing unmanned
Machine.
Background technique
Common unmanned plane is broadly divided into fixed-wing unmanned plane and rotor wing unmanned aerial vehicle.Wherein fixed-wing unmanned plane has flight
The advantages that speed is fast, flying height is high, the cruise time is long, but runway is generally required in takeoff and landing, or pass through auxiliary dress
Transmitting and landing are set, thus its application range has certain limitations.The maximum advantage of rotor wing unmanned aerial vehicle is can VTOL and sky
Middle hovering, and there is good low-speed maneuver performance, but its disadvantage is it is also obvious that mainly low efficiency, flying speed slowly with
And the cruise time is short.It can be seen that the unmanned plane of two kinds of forms respectively has its advantage and disadvantage.With the quick universal of unmanned plane and extensively
Requirement using, people to performances such as the landing of unmanned plane, speed and endurances is continuously improved, can VTOL fixed-wing nobody
Machine comes into being.
Can VTOL fixed-wing unmanned plane both had fixed-wing unmanned plane during flying speed is fast, flying height is high, cruise when
Between it is long the advantages that, and with VTOL and hovering ability, can VTOL fixed-wing unmanned plane generally closed
Note and extensively research.Currently can VTOL fixed-wing unmanned plane mainly have more rotor combination fixed-wing formulas, tilting rotor formula and
Three kinds of forms of tail sitting posture.More rotor combination fixed-wing formulas are the simplest, install rotor system additional directly on fixed-wing unmanned plane and are
Unmanned plane provides Vertical Dynamic, and the VTOL and hovering ability of fixed-wing unmanned plane are realized with this, and maximum defect is,
Fly once unmanned plane switchs to put down, rotor system will stop working, and become the weight that unmanned plane is additionally born；Tilting rotor formula is logical
The rotor that crossing can vert is providing Vertical Dynamic or horizontal power in different positions for unmanned plane, the biggest problems are that, incline
Turn that process control difficulties are big, reliability is low；Tail sitting posture unmanned plane is a kind of tail seat ground head-up unmanned plane of machine, when taking off,
It takes off vertically under the effect of dynamical system lift, turns unmanned plane by constantly dragging down head when reaching certain altitude and speed
Fly to be flat, when landing, make head upward by drawing high head and climbing, then controlling dynamical system and reducing lift keeps unmanned plane vertical
Landing.
In conclusion the advantages of tail sitting posture unmanned plane combines fixed-wing unmanned plane and rotor wing unmanned aerial vehicle, while not depositing again
The problem of bearing additional weight, without complicated process control of verting is done, still, and in the prior art, tail sitting posture unmanned plane
Its unique form also brings specific problem to it, mainly under vertical flight and transition flight mode, flying speed
Relatively slow, low so as to cause rudder face driving efficiency, the problem of wind resistance difference, additionally there are be all gyroplane problem: noise is big, effect
Rate is lower, and safety is poor.
Utility model content
In view of the above-mentioned problems, being used the utility model proposes a kind of distributed shrouded propeller power vertical take-off and landing drone
In solving, tail sitting posture unmanned plane rudder face driving efficiency under vertical flight and transition flight mode is low, wind resistance is poor and gyroplane is made an uproar
Sound is big, rotor low efficiency, the problem of safety difference.
In order to solve the above technical problems, the technical solution of the utility model are as follows:
A kind of distribution shrouded propeller power vertical take-off and landing drone, including fuselage, front wing, rear wing, vertical fin and rise and fall
Frame；
The front fuselage upper surface is equipped with air intake duct, and the fuselage afterbody upper surface is equipped with exhaust outlet；The front wing is
All-moving wing, the front wing are made of the left front wing and right front wing, and the left front wing includes the first shell, rotation axis and front wing rudder
Face；First upper shell is the first upper limb, and first shell lower end is the first bottom wing, first shell left and right side
For first baffle, described rotation axis one end is fixed on the first bottom wing right end, and the other end is fixed on back docking；Described first
Upper limb is fixed with the front wing rudder face, and the front wing rudder face is fixed at first bottom wing relative position；The right front wing with
It is symmetrical set between the left front wing；
The rear wing is made of the left back wing and right rear wing, and the left back wing is fixed on the downside of fuselage afterbody, the left back wing
Including second housing and rear wing rudder face；The second housing upper end is the second upper limb, and the second housing lower end is the second bottom wing,
The second housing left and right side is second baffle, and second upper limb is fixed with the rear wing rudder face, the second bottom wing phase
To being fixed with the rear wing rudder face at position；It is symmetrical set between the right rear wing and the left back wing；First shell and
Duct dynamical system is equipped in two shells；
The vertical fin includes left side vertical fin and right side vertical fin, and the left side vertical fin and right side vertical fin are symmetrically arranged sweepback
The wing, the left side vertical fin are fixed on rear wing upper end left part, and the right side vertical fin is fixed on rear wing upper end right part, the left side vertical fin
And right side vertical fin is along the setting symmetrical above and below of rear wing center line；Vertical fin end taper is fixed with undercarriage.
As the further improvement of this programme, the mounting height of the front wing is greater than the mounting height of rear wing.
As the further improvement of this programme, the undercarriage is wheel undercarriage.
As the further improvement of this programme, the streamlined shape of fuselage.
As the further improvement of this programme, the rear wing aerofoil profile is thick wing type.
As the further improvement of this programme, the duct dynamical system is by propeller, radome fairing, motor fixing frame and electricity
Mechanism at；The motor fixing frame both ends are installed on first baffle and second baffle, and the motor is fixed on motor and fixes
On front side of frame, the motor shaft of the motor is fixed with the propeller, and the radome fairing is fixed on front side of propeller.
By adopting the above technical scheme, the utility model has the following beneficial effects: front wing be all-moving wing, cooperate dynamical system and
It is low, anti-that flight control system can effectively solve tail sitting posture unmanned plane rudder face driving efficiency under vertical flight and transition flight mode
The problem of wind difference, and improve the mobility of unmanned plane；Simultaneously because using the design of duct package and the landing of tail sitting posture, this
Aircraft does not have the movable device of any exposed propeller or danger, because the exhaust stream of turboshaft engine expands by rear wing air-flow
Substantially cool down after exhibition, is discharged without high temperature hot gas body, accidental wound will not be caused to personnel, antenna on ground or warship etc.
Evil has good safety；In addition distributed power system, lift efficiency can be effectively improved by being distributed in front wing and rear wing, be increased
Add cruise duration, and control is more flexible, there is higher safe margin；The distribution of multiple duct power and control rudder face is set
Meter, so that the demand to vertical fin weakens, not needing rudder can be realized course maneuvering.
Detailed description of the invention
Fig. 1 is distributed shrouded propeller power vertical take-off and landing drone stereoscopic schematic diagram in the present embodiment；
Fig. 2 is distributed shrouded propeller power vertical take-off and landing drone front-view schematic diagram in the present embodiment；
Fig. 3 is distributed shrouded propeller power vertical take-off and landing drone schematic top plan view in the present embodiment；
Fig. 4 is the first duct dynamical system and the second duct power system architecture schematic diagram in the present embodiment.
In figure, 1- fuselage, 2- air intake duct, 3- front wing, 4- vertical fin, 5- undercarriage, 6- rear wing, 7- exhaust outlet, 8- duct is dynamic
Force system, the first upper limb of 3-1-, the first bottom wing of 3-2-, 3-3- front wing rudder face, 3-4- rotation axis, the second upper limb of 6-1-, 6-2-
Two bottom wings, 6-3- rear wing rudder face, 8-1- propeller, 8-2- radome fairing, 8-3- motor fixing frame, 8-4- motor.
Specific embodiment
Specific embodiment of the present utility model is described further with reference to the accompanying drawing.It should be noted that
The explanation of these embodiments is used to help to understand the utility model, but does not constitute the restriction to the utility model.This
Outside, technical characteristic involved in the various embodiments of the present invention described below is as long as they do not conflict with each other
It can be combined with each other.
As shown in Figures 1 to 4, a kind of distributed shrouded propeller power vertical take-off and landing drone, including fuselage 1, front wing
3, rear wing 6, vertical fin 4 and undercarriage 5；
The 1 front end upper surface of fuselage is equipped with air intake duct 2, and 1 rear upper surface of fuselage is equipped with exhaust outlet 7；Before described
The wing 3 is all-moving wing, and the front wing 3 is made of the left front wing and right front wing, and the left front wing includes the first shell, rotation axis 3-4
And front wing rudder face 3-3；First upper shell is the first upper limb 3-1, and first shell lower end is the first bottom wing 3-2, institute
Stating the first shell left and right side is first baffle, and the one end the rotation axis 3-4 is fixed on the first bottom wing 3-2 right end, and the other end is solid
It is scheduled on the docking of 1 top of fuselage；The first upper limb 3-1 is fixed with the front wing rudder face 3-3, and the first bottom wing 3-2 is with respect to position
The place of setting is fixed with the front wing rudder face 3-3；It is symmetrical set between the right front wing and the left front wing；
The rear wing 6 is made of the left back wing and right rear wing, and the left back wing is fixed on the downside of 1 rear portion of fuselage, described left back
The wing includes second housing and rear wing rudder face 6-3；The second housing upper end is the second upper limb 6-1, and the second housing lower end is
Second bottom wing 6-2, the second housing left and right side are second baffle, and the second upper limb 6-1 is fixed with the rear wing rudder face
6-3 is fixed with the rear wing rudder face 6-3 at the relative position the second bottom wing 6-2；It is in pair between the right rear wing and the left back wing
Claim setting；Duct dynamical system 8 is equipped in first shell and second housing；
The vertical fin 4 includes left side vertical fin and right side vertical fin, after the left side vertical fin and right side vertical fin are symmetrically arranged
The wing is plunderred, the left side vertical fin is fixed on 6 upper end left part of rear wing, and the right side vertical fin is fixed on 6 upper end right part of rear wing, the left side
Vertical fin and right side vertical fin are along the setting symmetrical above and below of 6 center line of rear wing；The 4 end taper of vertical fin is fixed with undercarriage 5.
The utility model is reequiped using the dynamic engine of oil by taking oil electric mixed dynamic as an example, drives 3 generators, match
Lithium battery is closed, realizes that serial mixed power promotes.
Fuselage 1 is mounted in body using streamline fuselage from low to high, the dynamic engine of oil, and air intake duct 2 is located at fuselage 1
The upper surface of front end, exhaust outlet 7 are arranged in 1 rear upper surface of fuselage, extend between the second upper limb 6-1 and the second bottom wing 6-2,
After engine gas discharge, temperature can be extended by 6 air-flow of rear wing, to be greatly lowered.
Front wing 3 is all-moving wing, is docked by rotary shaft 3-4 with fuselage 1, can cope with prominent wind by force, can also increase vertical rise
It dropping to flat fly over and crosses mode safety, aerofoil profile selects NACA2412,6 small-sized shrouded propeller dynamical systems are disposed in front wing 3,
Front wing rudder face 3-3 is had behind each shrouded propeller.
6 aerofoil profile of rear wing is selected compared with thick wing type NACA2418, can be used as oil storage fuel tank, disposes 20 small-sized ducts in rear wing 6
Propeller dynamical system, has rear wing rudder face 6-3 behind each shrouded propeller, and rear wing 6 is opened up to installing tail sitting posture at ratio 0.5
Vertical fin 4,4 taper of vertical fin have 4 wheel undercarriages for having buffer capacity 5, and support body and reduction impact carry when being used for landing
Lotus.
Front wing rudder face 3-3 realize elevator function, rear wing rudder face 6-3 can independent control realize wing flap and aileron function.
Vertical fin 4 is tail sitting posture vertical fin, and single vertical fin 4 is divided to two sections of wings, 25 ° of inner segment leading edge sweep, outer segment leading edge sweep
21 °, the four-point take-off and landing device that the wheel undercarriage 5 of 4 taper of vertical fin is formed should ensure that anti-rollover angle within 50 °.
Heading control by adjusting rear wing 6 ducted fan thrust profiles or adjustment duct between rudder realize, and
All ducted fans can be adjusted to provide different thrust by control system, cooperate the rudder face of distributed AC servo system, have
A variety of special maneuverabilities adapt to various complex working condition requirements.
Under transition flight mode, is rotated by control front wing 3, formed and become vector power, cooperate the control of rear wing rudder face 6-3
System, the sports safety transition of leaning forward and swing back of Lai Shixian unmanned plane.Detailed process are as follows: it puts down for vertical turn and flies over journey, it is certain reaching
Unmanned plane is set to switch to flat fly by constantly dragging down head when height and speed；It is flat to fly to turn vertical process to make by drawing high head and climbing
Head upward, then makes unmanned plane switch to vertical flight.
Multiple shells can be passed sequentially through after screw is fixed and be added when needing multiple dynamical systems by the dynamical system
Add duct dynamical system 8, using oil electric mixed dynamic, by the dynamic driven by engine electrical power generators of oil, cooperation battery system is more
The shrouded propeller of a miniaturization provides electric energy, and pure electric vehicle power can also be used, directly provide electric energy with high-energy battery.Due to current
Battery is generally relatively low compared to the energy density of oil, so selecting oil electric mixed dynamic herein, but is not limited to hybrid power；It is multiple small
The motor power to weight ratio of type is significantly greater than single high capacity motor, and Power System of Flight Vehicle weight is mitigated, and
And the air-flow of wing can be accelerated, so that the lift efficiency of entire wing greatly improves, thus the airfoil for needing aircraft
Product reduces 50% compared to conventional design, reduces frictional resistance and wing weight；Due to being risen using the design of duct package and tail sitting posture
Drop, this aircraft do not have the movable device of any exposed propeller or danger, discharge (turboshaft engine without high temperature hot gas body
Exhaust stream by rear wing air-flow extension after substantially cool down), accident will not be caused to personnel, antenna on ground or warship etc.
Injury has good safety, and wherein shrouded propeller quantity can determine according to demand.Multiple duct power and control rudder face
Distributed Design so that the demand to vertical fin weakens, not needing rudder can be realized course maneuvering；Duct motor according to
It needs to can be designed as generator/motor, when aircraft declines and slows down, power generation mode can be switched to；Aircraft rises
When drop, electric system provides energy and puts into high gear the power demand for meeting propeller.Even if engine under special circumstances
Parking suddenly, battery system have enough energy reserves to continue powered operation, engine can be waited to restart；Or it is meeting
Still a period of time can be continued to run when cannot starting to fuel engines catastrophe failure.
The Heading control of unmanned plane is real by adjusting the rudder between the ducted fan thrust profiles or adjustment duct of rear wing
It is existing, and all ducted fans can be adjusted to provide different thrust by control system, cooperate the rudder of distributed AC servo system
Face has a variety of special maneuverabilities, adapts to various complex working condition requirements.
The embodiments of the present invention is explained in detail in conjunction with attached drawing above, but the utility model is not limited to be retouched
The embodiment stated.For a person skilled in the art, right in the case where not departing from the utility model principle and spirit
These embodiments carry out a variety of change, modification, replacement and modification, still fall in the protection scope of the utility model.
Claims (6)
1. a kind of distribution shrouded propeller power vertical take-off and landing drone, it is characterised in that: including fuselage (1), front wing (3),
Rear wing (6), vertical fin (4) and undercarriage (5)；
Fuselage (1) the front end upper surface is equipped with air intake duct (2), and fuselage (1) rear upper surface is equipped with exhaust outlet (7)；Institute
Stating front wing (3) is all-moving wing, and the front wing (3) is made of the left front wing and right front wing, and the left front wing includes the first shell, turns
Moving axis (3-4) and front wing rudder face (3-3)；First upper shell is the first upper limb (3-1), and first shell lower end is the
One bottom wing (3-2), first shell left and right side are first baffle, and described rotation axis (3-4) one end is fixed on the first bottom wing
(3-2) right end, the other end are fixed on the docking of fuselage (1) top；First upper limb (3-1) is fixed with the front wing rudder face (3-
3), the front wing rudder face (3-3) is fixed at the first bottom wing (3-2) relative position；Between the right front wing and the left front wing
It is symmetrical set；
The rear wing (6) is made of the left back wing and right rear wing, and the left back wing is fixed on the downside of fuselage (1) rear portion, described left back
The wing includes second housing and rear wing rudder face (6-3)；The second housing upper end is the second upper limb (6-1), under the second housing
End is the second bottom wing (6-2), and the second housing left and right side is second baffle, and second upper limb (6-1) is fixed with described
Rear wing rudder face (6-3) is fixed with the rear wing rudder face (6-3) at the second bottom wing (6-2) relative position；The right rear wing with
It is symmetrical set between the left back wing；Duct dynamical system (8) are equipped in first shell and second housing；
The vertical fin (4) includes left side vertical fin and right side vertical fin, and the left side vertical fin and right side vertical fin are symmetrically arranged sweepback
The wing, the left side vertical fin are fixed on rear wing (6) upper end left part, and the right side vertical fin is fixed on rear wing (6) upper end right part, the left side
Side vertical fin and right side vertical fin are along the setting symmetrical above and below of rear wing (6) center line；Vertical fin (4) end taper is fixed with undercarriage
(5)。
2. a kind of distributed shrouded propeller power vertical take-off and landing drone according to claim 1, it is characterised in that: institute
The mounting height for stating front wing (3) is greater than the mounting height of rear wing (6).
3. a kind of distributed shrouded propeller power vertical take-off and landing drone according to claim 1, it is characterised in that: institute
Stating undercarriage (5) is wheel undercarriage.
4. a kind of distributed shrouded propeller power vertical take-off and landing drone according to claim 1, it is characterised in that: institute
State fuselage (1) streamlined shape.
5. a kind of distributed shrouded propeller power vertical take-off and landing drone according to claim 1, it is characterised in that: institute
Stating rear wing (6) aerofoil profile is thick wing type.
6. a kind of distributed shrouded propeller power vertical take-off and landing drone according to claim 1, it is characterised in that: institute
Duct dynamical system (8) is stated to be made of propeller (8-1), radome fairing (8-2), motor fixing frame (8-3) and motor (8-4)；Institute
It states the both ends motor fixing frame (8-3) to be installed on first baffle and second baffle, the motor (8-4) is fixed on motor and fixes
On front side of frame (8-3), the motor shaft and the propeller (8-1) of the motor (8-4) are fixed, and the radome fairing (8-2) is fixed on
On front side of propeller (8-1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821438002.9U CN208746231U (en) | 2018-09-03 | 2018-09-03 | A kind of distribution shrouded propeller power vertical take-off and landing drone |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821438002.9U CN208746231U (en) | 2018-09-03 | 2018-09-03 | A kind of distribution shrouded propeller power vertical take-off and landing drone |
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| CN201821438002.9U Expired - Fee Related CN208746231U (en) | 2018-09-03 | 2018-09-03 | A kind of distribution shrouded propeller power vertical take-off and landing drone |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112103612A (en) * | 2020-11-02 | 2020-12-18 | 成都天锐星通科技有限公司 | Antenna for communication in motion |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| CN112678167A (en) * | 2020-12-28 | 2021-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical take-off and landing control method for tail-seated airplane |
| CN112722263A (en) * | 2021-01-19 | 2021-04-30 | 西北工业大学 | Vertical/short-distance take-off and landing aircraft with distributed power coupling lift-increasing wing surfaces |
| 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 |
| CN113086184A (en) * | 2021-04-23 | 2021-07-09 | 北京航空航天大学 | Tandem distributed electric propulsion coaxial duct vertical take-off and landing aircraft |
| CN113291459A (en) * | 2021-07-27 | 2021-08-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
-
2018
- 2018-09-03 CN CN201821438002.9U patent/CN208746231U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112103612A (en) * | 2020-11-02 | 2020-12-18 | 成都天锐星通科技有限公司 | Antenna for communication in motion |
| CN112644686A (en) * | 2020-12-25 | 2021-04-13 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
| CN112678167A (en) * | 2020-12-28 | 2021-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical take-off and landing control method for tail-seated airplane |
| CN112678167B (en) * | 2020-12-28 | 2024-01-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical take-off and landing control method for tail-seated aircraft |
| CN112722263A (en) * | 2021-01-19 | 2021-04-30 | 西北工业大学 | Vertical/short-distance take-off and landing aircraft with distributed power coupling lift-increasing wing surfaces |
| 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 |
| CN113086184A (en) * | 2021-04-23 | 2021-07-09 | 北京航空航天大学 | Tandem distributed electric propulsion coaxial duct vertical take-off and landing aircraft |
| CN113291459A (en) * | 2021-07-27 | 2021-08-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
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| CF01 | Termination of patent right due to non-payment of annual fee |