CN206511120U - Dalta wing is coaxial to turning duct aircraft - Google Patents
Dalta wing is coaxial to turning duct aircraft Download PDFInfo
- Publication number
- CN206511120U CN206511120U CN201621046687.3U CN201621046687U CN206511120U CN 206511120 U CN206511120 U CN 206511120U CN 201621046687 U CN201621046687 U CN 201621046687U CN 206511120 U CN206511120 U CN 206511120U
- Authority
- CN
- China
- Prior art keywords
- turning
- wing
- aircraft
- coaxial
- coaxially
- 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
Abstract
A kind of dalta wing is coaxial to turning duct aircraft, mainly by coaxially to turning duct aircraft, dalta wing, accelerating propulsive wing to constitute；Wherein coaxially engine, speed pulley, driving belt, console are arranged in flight capsule to turning duct aircraft, downside outside flight capsule is equipped with undercarriage, buffer unit is disposed between undercarriage and flight capsule, it is coaxial concentric equipped with circular control slat to turning the lower section of ducted fan propeller system, coaxially to turning ducted fan propeller system and control slat respectively up and down together by the fixedly sleeved shell middle and upper part periphery in flight capsule of support, the axial line of three is overlapped in the vertical；Dalta wing is socketed in the coaxial coaxial periphery to turning ducted fan propeller system and control slat to turning duct aircraft, makes coaxially to be built in dalta wing to turning duct aircraft；The dead astern of the dalta wing relative with aircraft direction of advance is provided with acceleration propulsive wing.
Description
Technical field
The utility model is related to Aircraft structural design and applied technical field, and particularly a kind of dalta wing is coaxial to turning to contain
Road aircraft.
Background technology
At present, Fixed Wing AirVehicle needs runway to carry out landing, can not be parked in battlefield surveillance and stare region of war ring in the air
Border.Relative and Fixed Wing AirVehicle, helicopter has VTOL and an advantage that can be hovered, but helicopter pneumatic efficiency
Low, noise is very big during flight, is easy to be found by enemy in battlefield surveillance, and wing tip easily knocks tree in forest is searched
Branch causes body to damage, while the propeller of rotation can be damaged to personnel at a high speed.The Kinematic Decomposition of propeller is transported for level
Dynamic and rotary motion.The resistance being primarily present during propeller motion has air frictional resistance, pressure drag, induced drag and interference
Resistance etc..Blade makes speed highest at blade tip because of high speed circular motion, and induced drag is than larger, and air-flow produces impact and made to external world
Big into noise, this is the low main cause of free spiral rotation oar dynamic efficiency.Free spiral rotation oar due to being cantilever beam structure rod member,
Being easily deformed under pneumatic action at blade tip causes efficiency further to deteriorate, and this is to limit one of bottleneck of propeller high-speed motion,
It is also the key of propeller aeroplane and helicopter rate limitation.Meanwhile, it is the side for adjusting main rotor power that the advance of helicopter, which is fallen back,
Adjusted to, power in horizontal forward or power backward, that is, make lift out of plumb and the horizon of main wing, so to helicopter
Driver behavior and rotor axle construction increase complexity, the response of operational order has certain delayed.As aircraft is in peace
Protect, the disaster relief can not meet requirement with acting on increasing, traditional Fixed Wing AirVehicle and helicopter in terms of anti-terrorism.
The isolated fan of the more same diameter of ducted fan can produce bigger lift, and fan ring is included in duct, both may be used
Stop that the pneumatic sound of fan is outwards propagated, but it is compact conformation, safe.Therefore, the advantage of ducted fan propeller：At blade tip by
Duct is protected, and impact noise reduces, and induced drag is reduced, and efficiency is higher.Under same power consumption, ducted fan is more same
The isolated propeller of diameter, can produce bigger thrust.Simultaneously because the ring of duct includes effect, its compact conformation, pneumatic make an uproar
Sound is low, safety in utilization is good, therefore as a kind of thrust or lift unit, is applied among Flight Vehicle Design.
Have many duct aircraft at present, but they are mainly to be widely applied and make ducted tail rotor, also have
In duct aircraft, ducted fan is as lift fan, and thrust then needs separately to add fan, so current duct aircraft body
Product all compares huge and complexity, and lift and thrust are all to be respectively derived from different fan systems.Ducted fan diameter is bigger, its
Power is bigger, still, because of its design feature, ducted fan restricted diameter, so aircraft will when needing high-power lift
Load onto more than two ducted fans, the aircraft of these pair of duct or many ducts there is the balance sex chromosome mosaicism of flight.
The content of the invention
The purpose of this utility model is to overcome the deficiencies in the prior art there is provided one kind is reasonable in design, and compact conformation is simple, behaviour
Make flexible instruction and respond the dalta wing of fast flight fast and stable coaxially to turning duct aircraft.
Triangle Ji described in the utility model is coaxial to turning duct aircraft, mainly by coaxially to turning duct aircraft, triangle
The wing, acceleration propulsive wing composition；It is wherein coaxial to turn duct aircraft by flight capsule, it is coaxial to turn ducted fan propeller system,
Control slat, engine, speed pulley, driving belt, console, complete machine parachute, undercarriage, buffer unit, seat
Constitute, engine, speed pulley, driving belt, console are arranged in flight capsule, the downside outside flight capsule is equipped with
Fall frame, buffer unit is disposed between undercarriage and flight capsule, it is coaxially concentric to turning the lower section of ducted fan propeller system
Equipped with circular control slat, coaxially pass through together up and down respectively to turning ducted fan propeller system and control slat
The fixedly sleeved shell middle and upper part periphery in flight capsule of support, the axial line of three is overlapped in the vertical；Dalta wing is socketed in together
Axle to turn duct aircraft it is coaxial to turn ducted fan propeller system and control slat periphery, make coaxially to turn contain
Road aircraft is built in dalta wing；Acceleration is provided with the dead astern of the dalta wing relative with aircraft direction of advance to promote
The wing.
It is described in the utility model coaxial to turning bottom of the engine device of duct aircraft in flight capsule, engine
Power transmission shaft on speed pulley is housed, be provided with seat above engine, console, flight be set in the front of seat
The downside outside complete machine parachute, flight capsule is provided with the top of cabin undercarriage is housed, be provided between undercarriage and flight capsule
Buffer unit, it is coaxially concentric equipped with circular control slat to turning the lower section of ducted fan propeller system, it is coaxial right
Turn ducted fan propeller system and control slat is mounted in the periphery of flight capsule middle and upper part, i.e. flight capsule by support casing together
It is looped around the coaxial center to turning ducted fan propeller system and the common axial line of control slat, the axle of three
Heart line is overlapped in the vertical.
It is described in the utility model coaxial to turning ducted fan propeller system by driving gear shaft, driven gear shaft, just
Turn gear ring, reversion gear ring, positive switch rotor, reversion rotor, duct ring, driven pulley, support composition and into annular shape；Control hundred
Page disk is annular shape, is made up of advance louver and direction louver.
Described in the utility model coaxial to turning in ducted fan propeller system, positive switch rotor is distributed on outside rotating forward gear ring
Zhou Shang, reversion rotor is distributed on reversion gear ring periphery, the equal rotating forward gear ring of diameter and concentric pairing above and below reversion gear ring,
Driving gear shaft and driven gear shaft, which are distributed on, rotates forward gear ring with inverting above and below gear ring in the annular slot of pairing, driving gear shaft
With the tooth on the axle body of driven gear shaft and the gear teeth for rotating forward gear ring, inverting gear ring, four be intermeshing, while positive switch rotor
The spacing of plane-parallel is maintained between reversion rotor, when driving gear shaft rotation, the upper and lower engaged with its axle body
Gear ring and reversion gear ring are rotated forward under the auxiliary of driven gear shaft, it is synchronous to carry out concentric both forward and reverse directions to rotating, simultaneously
Also the positive switch rotor being connected respectively with them and reversion rotor is driven to carry out coaxial to rotating；In positive switch rotor coaxially to turning
Periphery with reversion rotor group, provided with a duct ring, is coaxially one to turning ducted fan propeller system from the appearance
It is great circle ring-type of the inner ring using duct ring as outer shroud using the rotating forward gear ring to being combined and reversion gear ring；Driving gear shaft is connected
One end of flight capsule is equipped with driven pulley, and driven pulley is connected by driving belt with the speed pulley on engine
It is dynamic, constitute the power drive mechanism of aircraft.
In control slat described in the utility model, what the vertical left and right sides with aircraft direction of advance was installed is
Louver in advance louver, the front and back installation direction louver in the same direction with aircraft direction of advance, advance louver and direction louver
Group is all that can adjust the vertically downward or diagonally downward flow deflector group of angle.
Dalta wing described in the utility model, is socketed in coaxial to turning the coaxial to turning ducted fan spiral of duct aircraft
The periphery of oar system and control slat, makes coaxially to be built in dalta wing to turning duct aircraft；Dalta wing one of them
The direction of advance of aircraft is pointed to and as advancing angle in angle forever, when aircraft flight, it is possible to substantially reduce aircraft
Air drag, makes the flight of aircraft more smooth steady；The wing body thickness of dalta wing, is at least not less than coaxial to turning ducted fan
The thickness of propeller system；The side view cutting plane of the advancing angle of dalta wing can also be able to be taper angle shape with rectangle.
Acceleration propulsive wing described in the utility model, be arranged on the dalta wing relative with aircraft direction of advance just after
Side, the advance for being used to help aircraft accelerates；The minimum number for accelerating propulsive wing is one.
Dalta wing described in the utility model is coaxial to turning during the work of duct aircraft, by console to start start first
Machine, the power of engine starts coaxial to turning ducted fan propeller set by drive pulley, the driving belt of transmission mechanism
The driven pulley rotation work of system, is that aircraft is carried so as to drive coaxially to turning ducted fan propeller system rotary work
For rising and flying power, meanwhile, by controlling the advance louver and the louver group water conservancy diversion angle of direction louver of slat,
To control the heading of aircraft；When aircraft needs rapidly to advance, while the work of Acceleration of starting propulsive wing makes flight
Device increases the power fast forwarded through on the basis of original flying speed；When aircraft run out of steam during flying or power not
During foot forced landing, then complete machine parachute is ejected, allow aircraft general safety to land.
In summary, dalta wing described in the utility model is coaxial to turning duct aircraft than existing duct aircraft more
With distinguishing feature：The design of gear ring is primarily due to, coaxially to turning ducted fan propeller system for great circle ring-type, diameter
Can be bigger, lift and flying power are more sufficient；Second flight capsule is arranged on the coaxial axle to turning ducted fan propeller system
The position of heart line longitudinal direction, takes full advantage of the motorless idle axial space in propeller system center, makes the structure of aircraft
More compact, power distribution is more balanced, and machine gravity distribution is more reasonable, it is ensured that the flight stability of aircraft；3rd control louver
Disk is directly installed on the coaxial lower section to turning ducted fan propeller system, and the dynamic air-flow of rising, thrust and adjustment direction comes
Source is shared, make the rising of aircraft, hovering, flight and the operation that turns to it is more flexible it is simple with response instruction in time；4th contains
The coaxial design to turning of road fan, makes the flight of aircraft more stable, and the balance matching for having prevented double ducts or many ducts is asked
Topic, simplifies flight control；The air drag when design of 5th dalta wing can allow the aircraft to advance greatly drops
It is low, lift the flying speed and flight stability of aircraft；6th accelerates the design of propulsive wing, allows the pace of aircraft can
Raised speed and rapidly advanced with quick response；The 7th overall drop umbrella set, more aircraft provides overall flight safety and protected
Barrier.So, the utility model has huge economic value and social value.
Brief description of the drawings
Fig. 1 is front view of the present utility model, is included coaxial to turning duct aircraft 00, dalta wing 12, accelerating
Propulsive wing 13.
Fig. 2 is of the present utility model coaxial to turning duct aircraft front view, includes flight capsule 01, coaxially to turning
Ducted fan propeller system 02, control slat 03, engine 04, speed pulley 05, driving belt 06,
Console 07, complete machine parachute 08, undercarriage 09, buffer unit 10, seat 11, driving gear shaft 021, from
Movable gear shaft 022, rotating forward gear ring 023, reversion gear ring 024, positive switch rotor 025, reversion rotor 026, duct ring
027th, driven pulley 028, support 029.
Fig. 3 is of the present utility model coaxial to turning ducted fan propeller system with loading onto dalta wing and accelerate propulsive wing
Top view, include driving gear shaft 021, driven gear shaft 022, rotate forward gear ring 023, positive switch rotor 025,
Invert rotor 026, duct ring 027, dalta wing 12, acceleration propulsive wing 13.
Fig. 4 is the top view of control slat of the present utility model, includes console 07, seat 11, advance hundred
Page 031, direction louver 032.
Embodiment
The utility model is further illustrated with reference to the accompanying drawings and examples.
As shown in Fig. 1 and Fig. 3, dalta wing described in the utility model is coaxial to turning duct aircraft, mainly by same
Axle is to turning duct aircraft 00, dalta wing 12, accelerating propulsive wing 13 to constitute.
It is described in the utility model coaxial to turning duct aircraft by flight capsule 01, coaxially to turning to contain as shown in Fig. 2
Road fan propeller system 02, control slat 03, engine 04, speed pulley 05, driving belt 06, control
Platform 07 processed, complete machine parachute 08, undercarriage 09, buffer unit 10, seat 11 are constituted；It is wherein coaxial to turning duct
Fan propeller system 02 by driving gear shaft 021, driven gear shaft 022, rotates forward gear ring 023 as shown in Fig. 3
, reversion gear ring 024, positive switch rotor 025, reversion rotor 026, duct ring 027, driven pulley 028 constitute and
Into annular shape；Control such as Fig. 4 of slat 03 show annular shape, is made up of advance louver 031 and direction louver 032.
Coaxial bottom of the device of engine 04 in flight capsule 01 to turning duct aircraft that the utility model is stated,
It is equipped with the power transmission shaft of engine 04 above speed pulley 05, engine 04 and is provided with seat 11, seat 11
It can select to install according to the purposes of aircraft or cancel；The front of seat 11 sets console 07, and console 07 can
Its installation site is selected according to the purposes and mode of operation of aircraft, but needs not influence the reality of aircraft miscellaneous equipment function
Apply；The top of flight capsule 01 is provided with complete machine parachute 08；Downside outside flight capsule 01 is equipped with undercarriage 09, rises
Fall and buffer unit 10 is disposed between frame 09 and flight capsule 01；Coaxially to turning under ducted fan propeller system 02
Side is concentric equipped with circular control slat 03, coaxially to turning ducted fan propeller system 02 and control slat
03 is fixedly set in the periphery of flight capsule middle and upper part, i.e. flight capsule 01 by support together is looped around coaxially to turning duct wind
In the center for fanning propeller system 02 and the common axial line of control slat 03, the axial line of three is in the vertical
Overlap.
Described in the utility model coaxial to turning in ducted fan propeller system 02, positive switch rotor 025 is distributed on just
Turn on the periphery of gear ring 023, rotor minimum number is not less than 3；Reversion rotor 026 is distributed on outside reversion gear ring 024
Zhou Shang, rotor minimum number is not less than 3；The equal rotating forward gear ring 023 of diameter with reversion gear ring about 024 it is concentric
Pairing, driving gear shaft 021 and driven gear shaft 022 be distributed on rotating forward gear ring 023 with invert gear ring about 024 it is right
In the annular slot of conjunction, tooth on the axle body of driving gear shaft 021 and driven gear shaft 022 with rotating forward gear ring 023, it is anti-
Turn the tooth of gear ring 024, four be intermeshing, and the minimum number of driving gear shaft 021 is one, driven gear shaft 022
Minimum number be two, driving gear shaft 021 and driven gear shaft 022 are cylindricality gear or angular wheel；Just simultaneously
The spacing of plane-parallel is maintained between switch rotor 025 and reversion rotor 026, when driving gear shaft 021 is rotated, with
The rotating forward gear ring 023 and reversion gear ring 024 of the upper and lower of its axle body engagement are under the auxiliary of driven gear shaft 022, together
Step carries out concentric both forward and reverse directions to rotating, while also driving the positive switch rotor 025 being connected respectively with them and reversion
Rotor 026 is carried out coaxially to rotating, and coaxially the positive switch rotor 025 turned and the periphery of reversion rotor 026 are being provided with
One duct ring 027, the main duct of duct ring 027 is shared by positive switch rotor 025 and reversion rotor 026, Huo Zhe
It is respectively that positive switch rotor 025 and reversion rotor 026 set independent duct in duct ring 27, from the appearance, coaxially
To turn ducted fan propeller system 02 be one with to the rotating forward gear ring 023 being combined and reversion gear ring 024 be
Inner ring is with great circle ring-type of the duct ring 027 for outer shroud, and one end of the connection flight capsule 01 of driving gear shaft 021 is equipped with driven
Belt pulley 028, driven pulley logical 028 is crossed driving belt 06 and is connected with the speed pulley 05 on engine 04
It is dynamic, constitute the power drive mechanism of aircraft.
Claims (4)
1. a kind of dalta wing is coaxial to turning duct aircraft, mainly by coaxially to turning duct aircraft, dalta wing, accelerating propulsive wing
Composition, coaxially to turning duct aircraft then by flight capsule, coaxially to turning ducted fan propeller system, control slat, starting
Machine, speed pulley, driving belt, console, complete machine parachute, undercarriage, buffer unit, seat composition, wherein engine,
Speed pulley, driving belt, console are arranged in flight capsule, the downside outside flight capsule be equipped with undercarriage, undercarriage with
Buffer unit is disposed between flight capsule, it is coaxially concentric equipped with circular control to turning the lower section of ducted fan propeller system
Slat processed, coaxially to turn ducted fan propeller system and control slat respectively up and down together by support it is fixedly sleeved
The shell middle and upper part periphery of flight capsule, the axial line of three is overlapped in the vertical, it is characterised in that be socketed in dalta wing coaxially
Periphery to turning ducted fan propeller system and control slat, makes coaxially to be built in dalta wing to turning duct aircraft
It is interior；The direction of advance of aircraft is pointed to forever and as advancing angle in the one of angle of dalta wing；With aircraft direction of advance phase
To dalta wing dead astern be provided with acceleration propulsive wing.
2. a kind of dalta wing as claimed in claim 1 is coaxial to turning duct aircraft, it is characterised in that the wing body of dalta wing is thick
Degree, is at least not less than the coaxial thickness to turning ducted fan propeller system.
3. a kind of dalta wing as claimed in claim 1 is coaxial to turning duct aircraft, it is characterised in that the advancing angle of dalta wing
Side view cutting plane be rectangle or taper angle shape.
4. a kind of dalta wing as claimed in claim 1 is coaxial to turning duct aircraft, it is characterised in that accelerate propulsive wing quantity
It is at least one.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621046687.3U CN206511120U (en) | 2016-09-11 | 2016-09-11 | Dalta wing is coaxial to turning duct aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621046687.3U CN206511120U (en) | 2016-09-11 | 2016-09-11 | Dalta wing is coaxial to turning duct aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206511120U true CN206511120U (en) | 2017-09-22 |
Family
ID=59860964
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621046687.3U Active CN206511120U (en) | 2016-09-11 | 2016-09-11 | Dalta wing is coaxial to turning duct aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206511120U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107813927A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Dalta wing is coaxially to turning duct aircraft |
-
2016
- 2016-09-11 CN CN201621046687.3U patent/CN206511120U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107813927A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Dalta wing is coaxially to turning duct aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105620743B (en) | One kind is verted three rotor craft inclining rotary mechanisms | |
| US20180244367A1 (en) | Thrust producing unit with at least two rotor assemblies and a shrouding | |
| CN107672802B (en) | Slotted duct type rotor wing aircraft with rolling flow | |
| CN103935517B (en) | Aircraft | |
| CN204660020U (en) | One is distributed independently controls multi-rotor aerocraft | |
| CN103395492B (en) | A kind of unpowered short take-off and landing (STOL) unmanned plane turning rotor | |
| KR20150023061A (en) | Personal aircraft | |
| CN201419624Y (en) | Double-bypass propeller aerocar capable of vertical taking off and landing | |
| RU2507121C1 (en) | High-speed rotary-wing aircraft | |
| RU2673933C1 (en) | Gyroplane | |
| CN102490897A (en) | Multi-driving embedded rotor manned helicopter | |
| CN205602100U (en) | Gyroplane is lift vertically to short -tail crust | |
| CN111003166A (en) | Tandem electric double-rotor helicopter and control system thereof | |
| CN104590535A (en) | Propelling device for airship power device | |
| CN107303948A (en) | A kind of short tail goes straight up to gyroplane | |
| KR101772223B1 (en) | Rotor Concealing Hybrid VTOL UAV | |
| CN205022860U (en) | Coaxial pair changes duct aircraft | |
| CN106379534A (en) | Spin control system and aircraft | |
| CN206511120U (en) | Dalta wing is coaxial to turning duct aircraft | |
| CN108569396A (en) | Combined type blended wing-body high-speed helicopter | |
| CN206087305U (en) | Spin control system and aircraft | |
| CN106364665A (en) | Flight power system and flight vehicle | |
| CN109353176B (en) | Tricycle is experienced in flight | |
| CN106542094A (en) | Coaxially to turning duct aircraft | |
| CN105799927A (en) | Ducted ring fixed wing helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190214 Address after: 528000 Unit 1, Unit 102, 6 Blocks, Area A, Phase I, Liandong Youguyuan, No. 3, Dongsan District, Danzao Jiansha Road, Nanhai District, Foshan City, Guangdong Province Patentee after: Foshan Guoneng Aerospace Aircraft Manufacturing Co., Ltd. Address before: 528200 Xingyayuan E13-402, Xingye New Village, Guicheng, Nanhai District, Foshan City, Guangdong Province Patentee before: Lang Feng |