CN106945823A - Wall-attached jet all-wing aircraft - Google Patents
Wall-attached jet all-wing aircraft Download PDFInfo
- Publication number
- CN106945823A CN106945823A CN201710205798.7A CN201710205798A CN106945823A CN 106945823 A CN106945823 A CN 106945823A CN 201710205798 A CN201710205798 A CN 201710205798A CN 106945823 A CN106945823 A CN 106945823A
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- Prior art keywords
- wing aircraft
- air
- aircraft
- turbine
- wing
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
-
- 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
- B64C39/026—Aircraft not otherwise provided for characterised by special use for use as personal propulsion unit
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Wall-attached jet all-wing aircraft belongs to aviation field；The operation principle of the all-wing aircraft is：Accelerated using high velocity air and sweep away all-wing aircraft upper surface air, the extra lift of acquisition and thrust supply aircraft flight.The all-wing aircraft can fly in low-to-medium altitude, can be using 1) City supervision 2) crop pest control 3) rescue and relief work 4) fire-fighting 5) Hai Lu rescues 6) short distance traffic etc..The all-wing aircraft has short take-off and landing, and big-elevation not stall, low-altitude low-speed is good, manipulates control simply, flight stability and the good advantage of security.The aircraft includes (1) all-wing aircraft, (2) turbine compressed-air system, (3) harness system, (4) steerable system.
Description
(1) technical field
The present invention relates to aviation field, a kind of brand-new flight instruments is specifically provided, according to《International Patent Classification (IPC)》
IPC, which is divided, belongs to operation, Department of Transportation, aircraft major class.
(2) background technology
Presently known of manned vehicle has fixed wing aircraft, helicopter, gyroplane, rocket, fire balloon, dirigible and spray
Gas knapsack etc., concept aircraft has rolling wing machine, fan wing machine etc..But problem and defect is individually present in these aircraft：Fixed-wing
Aircraft needs to slide ability landing over long distances, and huge using the noise of heat engine, fuel oil pollution is serious, is flown using the fixed-wing of electric power
Machine flying distance and flying height are again not enough, and low-latitude flying requires too high to the driving technology of driver, once there is accident appearance
Easily there is fatal crass；Helicopter promotes air-flow to move downward acquisition lift using propeller, but due to propeller efficiency compared with
Low, its oil consumption is huge, and cost is high, it is impossible to popularize；The flight theory of fire balloon and dirigible is to utilize hot-air or hydrogen, helium
The characteristics of isodensity is smaller than air, is wrapped up using huge balloon and produces buoyancy, is characterized in possessing huge balloon, the spy
Levying causes its flying speed slow, by constraint of meteorological condition etc.；What New Zealand Rice Te Cheqi Glenn Martin sold
Jet knapsack, its flight theory is puffed away downwards with motorcycle engine two ducted fans of the driving raw lift of miscarriage, its feature
It is the ducted fan of two up to human ears, people and engine, fuel tank are all at position on the lower side, and making its center of gravity, on the lower side to improve flight steady
It is qualitative, but according to its announcement data from the point of view of, the aircraft oil consumption is huge, does not meet the world theme of low-carbon environment-friendly；Britain
The disclosed fan wing machine of fanwing companies, its flight theory is to install cross flow fan in upper surface of the airfoil, when being rotated using fan
Lift and thrust the supply aircraft flight of generation, the aircraft is characterized in that huge cross flow fan, machine are installed above wing
Head process goes out, and wing tip is provided with aileron, and these features cause flying speed slow, the momentum problems that cross flow fan rotating band comes, although it
Design empennage can cause head to drop to keep balance in the case of unexpected accelerate, and cross flow fan maximization meeting
Serious structure problem is brought, the technology for causing the aircraft to maximize is harsh, is limited by composite technology level；West
Pacify the disclosed rolling wing machine technology of polytechnical university, its flight theory is to stir air downwards when rotating with cycloid propeller to obtain anti-make
Firmly, with reaction force as lift, the device is characterized in that aircraft both sides respectively have a huge cycloid propeller, the device
This feature causes vehicle flight speeds low, big to landing environmental requirement, and cycloid propeller movable part is easily because vibrations and folding
Generation mechanical fatigue is scratched, once being broken, aircraft loses lift immediately and fallen.Fan wing machine and rolling wing machine because technology not
Maturation, will reach that manned purpose also has very long distance to walk.
(3) content of the invention
Present invention aim to address the deficiency of existing aircraft, spy is safe there is provided a kind of environmentally friendly, easily,
Cheap trip mode, can be obviously improved traffic jam issue, and the life of energy people is enriched again.
The invention provides a kind of brand-new flight equipment, it is characterised in that：Utilize the powerful Entraining Effect of wall-attached jet
Lift is provided.In R＆D process, it is found that fan wing machine has similar flight theory to the present invention：It is artificial to accelerate upper surface of the airfoil gas
Stream.But, the shortcomings of cross flow fan has bulky, fragile structure, inefficiency.The utilization wall-attached jet of the invention
Instead of replacing cross flow fan, but substitution is not simple replacement, and the change of aircraft body, research will step into new neck
Domain, creates new things, in new field, and inventor needs to tackle the major problem to have：1 jet spray angle and spout half
Traditional winged control ability of empennage declines caused by width, 2 jet jet velocities, the shape and installation site of 3 nozzles, 4 low flight speed, and 5 fly
Wing stability, 6 turbine installation forms, fuselage caused by 7 turbine rotations is rotated backward, 8 aircraft weight problems,
Solve 1 jet spray angle problem of problem when, by simulated experiment draw spray angle should parallel aerofoil
It can make full use of the energy of engine, improve efficiency, calculated through empirical equation, half-breadth is in 0.5mm to optimal between 5mm.In solution
Certainly during 2 jet jet velocity of problem, although flow velocity is to be the bigger the better, it is contemplated that the air compressor machine that big flow velocity is brought is overweight, it is pressurized
Structure thickeies, and manufacturing cost rises, the problems such as turbine is to energy requirement, with reference to all kinds of air compressor machines on the market on flow and
The parameter of pressure, comparative analysis show that the operating pressure of the present invention is low intermediate pressure section, and working flow rate is gone out 40 according to calculation of pressure
~200m/s.When solving the shape and installation site of the nozzle of problem 3, selectable scheme has round nozzle and rectangular nozzle,
In theoretical validation is carried out, discovery takes the rectangular nozzle more to have advantage：The technique merged with all-wing aircraft is simple, the energy utilization of jet
Rate is high, lightweight, it is easy to which that the advantages of cleaning, installation site is close to aerofoil, can increase jet energy utilization, and enhancing structure is strong
Degree, it is succinct and attractive in appearance.When traditional empennage flies the problem of control ability declines caused by solving 4 low flight speed, it is found that moved using center of gravity
The dynamic wing surface angle that changes can reach manipulation all-wing aircraft ability, so casting out traditional empennage, its advantage has, and simplifies flying wing structure, drop
Low flight control difficulty, mitigates all-wing aircraft weight.5 all-wing aircraft stability problems can be caused due to casting out empennage, the present invention refers to fire balloon weight
The heart is far below lift application point, reaches the purpose of very balance and stability, also as shown in Figure 1 using the method.The method
Though flight resistance can be caused to increase, because being low-speed operations device, influence is little, the present invention using people's lives and properties as
Weight, so design.When solving 6 turbine installation form of problem, drawn by the contrast of a variety of designs：Using all-wing aircraft covering as pressure
Force container shell can save the installation of turbine casing, and the vertical aerofoil in turbine suction inlet direction can make full use of air entry
Low-pressure area, and ensure that the air-flow streamline being centrifuged out is straight, reduce energy loss；The air that engine is inhaled is the pressure in all-wing aircraft
Contracting air can improve engine efficiency.When the fuselage caused by solve the problems, such as 7 turbine rotations is rotated backward, we with reference to directly
Rising aircraft and being balanced using tail undercarriage inside the momentum problems that king bolt oar is brought, creative utilization all-wing aircraft has pressure air
Sprayed in the steering spout of all-wing aircraft wing tip, using thrust-balancing all-wing aircraft inner turbine rotational band come momentum problems, and control
Air-flow size can realize the purpose of left and right turn.When solving 8 aircraft weight problem of problem, the present invention is empty with all-wing aircraft inside
Between be designed to Transfer pipe, remove blower casing and with all-wing aircraft covering replace, remove traditional empennage fly control and to change center of gravity
Substitution, makes full use of the body weight of people, and optimization design, it is ensured that while aircraft intensity and toughness and toughness, and it is unnecessary to reduce
Annex.
Advantages of the present invention：Very-short-reach landing (in theory can VTOL), big-elevation not stall, low-altitude low-speed performance
Good, simple in construction, it is easy to manipulate, good stability, simple training, women and children can all be manipulated, low manufacture cost, and ordinary people can also be purchased
Buy.Compared to helicopter, it wins simple in construction, it is easy to manipulate, good stability, low cost gives people the sense of security.Compared to solid
Determine wing aircraft, it is won in very-short-reach landing, and big-elevation not stall, low-altitude low-speed performance is good, it is easy to manipulate, good stability.Phase
Than in gyroplane, it has wind loading rating strong, without large-scale rotatable parts, can make the short-distance traffic work of effective use in city
Tool.Compared to fan wing machine, the turbofan that the present invention takes is more more efficient than cross flow fan, and centre of gravity, which is designed, causes low-speed stability
More preferably.In addition, the present invention is less demanding to landing condition, available for agricultural, transport, fire-fighting, rescue, it can also be used to unmanned plane
Deng cost of the present invention is relatively low in addition, it is easy to popularize, the every aspect of the lives of the people can be entered.
(4) illustrate
Below in conjunction with the accompanying drawings and embodiment the present invention is further detailed explanation：
Fig. 1：For all-wing aircraft overall construction drawing；
Fig. 2：For turbine compressed-air system figure；
Fig. 3：Position all-wing aircraft detail view；
Explanation is marked in schematic diagram：
1：All-wing aircraft 2：Turbine compressed-air system 3：Harness system 4：Steerable system 5：Dynamical system 6：Charging turbine 7：
Pressure vessel enclosure 8：Internal cavities 9：Nozzle 10：Turn to spout
(5) embodiment
Embodiment 1：
The present invention includes (1) all-wing aircraft, (2) turbine compressed-air system, (3) harness system, (4) steerable system.Described (1) flies
The wing is hollow, upper surface be provided with nozzle, inside be provided with (6) charging turbine, bottom be provided with (5) dynamical system, (3) harness system and
(4) steerable system.Described all-wing aircraft, (9) nozzle opening is close to aerofoil surface, and the flowpiston of injection is parallel with aerofoil, described
(2) turbine compressed-air system, (7) pressure vessel enclosure is all-wing aircraft covering, and the vertical aerofoil in (6) turbine Suction gas inlet direction starts
Machine institute suck is the compressed air in all-wing aircraft.Described (3) harness system, (3) harness system is hung on below all-wing aircraft, is used
Flexible cable is constrained or spherical hinge connection.Described (4) steerable system, promotes cross bar to change all-wing aircraft position of centre of gravity, hand by legs and feet
Regulation (10) turns to the flow of spout to adjust flight attitude.
Embodiment 2：
After the engine started, (6) charging turbine rotates compressed air, and compressed air flows in wing inner space
Dynamic, in the excretion of upper surface of the airfoil (9) nozzle, it is drained the plane jet formed and entrains all air with jet hit and will
It drives to the back lower place, forms low-pressure area, all-wing aircraft now has possessed part lift, after opening the throttle, and engine is from compression
Air-breathing in air, burning is more fully there is provided powerful power drive (6) charging turbine, and (6) charging turbine faster rotational speed is thrown away greatly
Gas is measured, gas is pressurized in wing space and discharged strongly in (9) nozzle, trigger powerful volume suction and form low-pressure area, its
Low-pressure area pressure and all-wing aircraft lower surface pressure formation pressure differential, pressure differential is exactly the lift source of all-wing aircraft, and its size is pressure differential
Value is multiplied by active area.
Embodiment 3：
After aircraft takeoff, because the frictional force without ground goes the momentum for overcoming (6) charging turbine rotating band to ask
Topic, because the conservation of momentum understands that aircraft can rotate in the horizontal direction.And the present invention turns to spray in all-wing aircraft end provided with (10)
Mouthful, the steering on air-flow size controlled level direction sprayed using spout, the momentum for not only overcoming (6) charging turbine to bring is asked
Topic, moreover it is possible to make full use of the momentum of (6) charging turbine to reach the purpose of flipper turn when turning.
Claims (9)
1. a kind of flight instruments, including (1) all-wing aircraft, (2) turbine compressed-air system, (3) harness system, (4) steerable system.Its feature
It is：Described (1) all-wing aircraft is hollow, and upper surface is provided with (9) nozzle, and inside is provided with (6) charging turbine, and bottom is provided with (5) power
System, (3) harness system and (4) steerable system.
2. according to (1) all-wing aircraft described in claim 1, it is characterised in that：(9) nozzle opening is close to aerofoil surface.
3. according to (1) all-wing aircraft described in claim 2, it is characterised in that：The flowpiston of injection is parallel with wingpiston.
4. according to (2) turbine compressed-air system described in claim 1, it is characterised in that：(7) pressure vessel enclosure is covered for all-wing aircraft
Skin.
5. according to (2) turbine compressed-air system described in claim 1 and 4, it is characterised in that：(6) turbine suction inlet direction is vertical
Aerofoil.
6. according to (2) turbine compressed-air system described in claim 1,4 and 5, it is characterised in that：(5) air that engine is inhaled
For the compressed air in all-wing aircraft.
7. according to (3) harness system described in claim 1, it is characterised in that：(3) harness system suspension is with below all-wing aircraft, adopting
Constrained with flexible cable.
8. according to (3) harness system described in claim 1, it is characterised in that：Harness system is hung on below all-wing aircraft, using ball
Chain connection.
9. according to (4) steerable system described in claim 1, it is characterised in that：Cross bar is promoted to change all-wing aircraft center of gravity by legs and feet
Position, hand adjustment section (10) turns to the flow of spout to adjust flight attitude.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710205798.7A CN106945823A (en) | 2017-03-28 | 2017-03-28 | Wall-attached jet all-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710205798.7A CN106945823A (en) | 2017-03-28 | 2017-03-28 | Wall-attached jet all-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106945823A true CN106945823A (en) | 2017-07-14 |
Family
ID=59475574
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710205798.7A Withdrawn CN106945823A (en) | 2017-03-28 | 2017-03-28 | Wall-attached jet all-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106945823A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI705028B (en) * | 2019-07-03 | 2020-09-21 | 國立雲林科技大學 | Wing efficiency enhancement device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050151002A1 (en) * | 2003-04-02 | 2005-07-14 | Toyota Jidosha Kabushiki Kaisha. | Vertical takeoff and landing apparatus |
| CN102120491A (en) * | 2011-02-24 | 2011-07-13 | 雷良榆 | Upper-surface circulating jet fixed-wing helicopter |
| CN103419923A (en) * | 2013-07-24 | 2013-12-04 | 南京航空航天大学 | Thrust gain device with high-speed wall attached air flow |
| CN105460216A (en) * | 2014-09-11 | 2016-04-06 | 周承岗 | Sucker type aircraft |
-
2017
- 2017-03-28 CN CN201710205798.7A patent/CN106945823A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050151002A1 (en) * | 2003-04-02 | 2005-07-14 | Toyota Jidosha Kabushiki Kaisha. | Vertical takeoff and landing apparatus |
| CN102120491A (en) * | 2011-02-24 | 2011-07-13 | 雷良榆 | Upper-surface circulating jet fixed-wing helicopter |
| CN103419923A (en) * | 2013-07-24 | 2013-12-04 | 南京航空航天大学 | Thrust gain device with high-speed wall attached air flow |
| CN105460216A (en) * | 2014-09-11 | 2016-04-06 | 周承岗 | Sucker type aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI705028B (en) * | 2019-07-03 | 2020-09-21 | 國立雲林科技大學 | Wing efficiency enhancement device |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170714 |
|
| WW01 | Invention patent application withdrawn after publication |