CN102120491A - Upper-surface circulating jet fixed-wing helicopter - Google Patents
Upper-surface circulating jet fixed-wing helicopter Download PDFInfo
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- CN102120491A CN102120491A CN2011100445726A CN201110044572A CN102120491A CN 102120491 A CN102120491 A CN 102120491A CN 2011100445726 A CN2011100445726 A CN 2011100445726A CN 201110044572 A CN201110044572 A CN 201110044572A CN 102120491 A CN102120491 A CN 102120491A
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Abstract
The invention discloses an upper-surface circulating jet fixed-wing helicopter, and belongs to the field of aircraft machines. An engine drive gear drives blower impellers which are symmetrically arranged on two sides; air is sucked by an air suction pipe on the rear of the upper surface, and is pressurized to pass through an exhaust pipe, is ejected through a nozzle of a leading edge slat, flows through the upper side of the surface and enters the air suction pipe to form circulating jet; when the helicopter is stationary or flies at a low speed, huge lift force and thrust can be generated; when the helicopter flies at a high speed, an arc valve controls a blower to pressurize air, the air is directly ejected for propelling, and the lift force and the lift drag ratio are over 30 percent higher than those of the similar common aircraft; and when the helicopter flies at a low speed, the ratio is improved more greatly, and in-situ large-angle lifting can be realized. The upper-surface circulating jet fixed-wing helicopter combines advantages of the common aircraft and an advantage of short takeoff and landing of a helicopter, overcomes respective defects of the common aircraft and the helicopter, is high in safety and stability, convenient to control, easy and flexible to use and convenient to implement, and can be widely applied to the fields such as industry, agriculture, commerce, individual transportation, tourism, entertainment, sport competition, patrol sightseeing, military and the like.
Description
Technical field:
The invention belongs to the aviation machine field, but be specifically related to a kind of wide-angle lifting subsonic aircraft.
Background technology:
For the restricted area of some aircraft takeoffs and landings, promptly rescue, carry, investigate occasions such as operation, patrol, tourism, sightseeing as mountain region, forest, river valley, sea, battlefield etc. and short distance, but need the autogyro of vertical lift especially.
Autogyro airworthiness, economy etc. are all not as conventional airplane, but use is more flexible, convenient.Therefore for a long time, when autogyro is updated, aeronautical chart also research always how in conjunction with the two characteristics of autogyro and conventional airplane.Propose, test, develop some other can vertical takeoff and landing (VTOL) or the aircraft that rises and falls of short range, in these schemes as rotor, deflectable jet pipe, deflectable screw propeller or driving engine, fan even deflectable wing, or take vector engine, booster rocket or the like.These schemes have only minority to obtain implementing, and also have layout, structure more complicated, reliability, relatively poor, the high problem in various degree of cost of economy separately.Mainly only be used for military affairs and special-purpose.For civilian, can be vertically or the wide-angle lifting, do not change conventional airplane fixed-wing basic structure again, economic and reliable, autogyro does not also have at present simply and easily.
Chinese patent: aerofoil jet fixed-wing autogyro (patent No. ZL200520112432.8) provides a kind of in this respect and formed a kind of up-to-date technology of lift by jet on aerofoil.On fixed wing aircraft, also can realize the vertical lift that is similar to, but its aerodynamic arrangement, mode of jet, structure produce lift size still some deficiency and defective.
Summary of the invention:
The present invention is directed to more existing autogyro scheme technology, different separately problems, shortcoming and defect, innovation a kind of " top airfoil circulation jet fixed wing aircraft ".The fixed wing of this aircraft is from aerodynamic arrangement, principle, structure etc., and propulsion system all is very different with modern conventional airplane.It not only utilizes flows through streaming of aircraft airfoil surface from the place ahead, formation produces lift around the circular rector of wing, and by its wing top airfoil front spray orifice ejection jet, flowing through top airfoil sucks from the rear portion, flow out from blowing engine again after entering the blowing engine supercharging, to front spray orifice ejection jet, so constitute circulation jet again, increase its circular rector and lift greatly along top airfoil.When flying speed equals 0, sizable lift is also arranged, do not need adrm and runway (even not needing highway pavement).Both can be directly with wide-angle lifting (having approached autogyro), also can commonly rise and fall and flying method, its fixed-wing is the same with the conventional airplane fixed-wing simple and reliable, and lift is big, and airworthiness (comprising dynamic property, economy, stability, road-holding property etc.) is better.
The technical scheme that the present invention solves its technical matters is: the screw propeller that does not have conventional airplane, turbojet, propelling units such as fan, overlap specific centrifugal blower and between the wing of both sides, respectively adorn one, driving engine by the centre passes through driving device, the blower freeing pipe links to each other with top airfoil front end leading edge slat, air inlet pipe links to each other with the aspirate tube at top airfoil rear portion, along rear portion, aerofoil top aspirated air, through the blowing engine air-out, flow out by aerofoil front end leading edge slat top spout again, form jet, a large amount of air flow thereupon near inducing pipe, so new effective lift system is formed in circulation.Produce thrust backward simultaneously, flying speed is bigger, blowing engine also can be separately from the direct injection air backward of its exhaust nozzle, constitute new push system.
The invention has the beneficial effects as follows: fixed-wing is simpler than common helicopter rotor, reliable, does not have common propelling unit and rotor drive.Utilize the engine drive blowing engine to push away, inhale the lift system of the circulation jet that aerofoil top forms and spray the push system of formation backward from exhausr port, effectively simple.The characteristics of comprehensive conventional airplane and autogyro, whole aircraft 1ift-drag ratio is big, and compactness is simple, reliable, gently little, flexible and convenient to use.
Below in conjunction with Fig. 1--Fig. 5 is described further layout of the present invention, structure and principle.
The present invention is shoulder-wing configuration, and there are preceding winglet, elevating rudder in fuselage the place ahead.The aircraft (Fig. 1) that there are vertical tail and a yaw rudder in the rear end (Fig. 2).Driving engine (9) and coupled transmission gearbox (21), two centrifugal exhausting fans (8) all are positioned at fuselage (1), have only the ejector exhaust pipe (7) of blowing engine (8) to expose the outer top of fuselage.Ejector exhaust pipe mouth direction backward, both sides wing (5) is fastenedly connected with fuselage (1), wing (5) front end has leading edge slat (4), there are some gap-shaped fumaroles the upper end of leading edge slat, the wing rear inner part is equipped with aspirate tube (13), aspirate tube connects top airfoil top, has row suction hole (14), aspirate tube (13) up to link to each other with blowing engine air inlet pipe (17).Steerable butterfly valve (23) is housed in the blowing engine air inlet pipe (17).
The leading edge slat (4) in wing (6) the place ahead is specific special-shaped tubular, the outer end sealing, interior end opening links to each other with blowing engine freeing pipe (16), leading edge slat (4), top airfoil, aspirate tube (13) and blowing engine, air inlet-outlet pipe (17,16) are thus formed the stream of open cycle jet by the impeller (18) of rotation.Flow direction shown in arrow among Fig. 1 Fig. 2.
Blowing engine spiral case below connects the catheter nozzle (25) of control cock (26) until the fuselage forward lower part by conduit.The balance in pitch of aircraft when control is risen and fallen.Driving engine (9) drives the blower wheel (18) that bilateral symmetry is arranged by the transmission gearbox middle gear, forms engine installation.
Driving engine (9) radiating gill and peripheral wind scooper (11) are enclosed within the exhaust pipe of engine (10) periphery, form the heat abstractor by exhaust injection, driving engine blow down gas thus, and injection cooled engine air, ejection backward produces certain thrust together.
Preceding winglet (2) and preceding elevating rudder (24) are positioned at the front end of fuselage (1), and vertical tail (19) and yaw rudder (20) are positioned at the rear end of fuselage, control lifting in-flight and course respectively, and vertical and driftage is stable.Fuselage (1) below is to hang wheel (3).
The present invention's first feature is: two centrifugal blowers (8) lay respectively at driving engine (9), transmission gearbox (21) both sides, and blowing engine air inlet pipe (17) links to each other with wing aspirate tube (13), and freeing pipe (16) links to each other with leading edge slat (1).
Second feature is: the leading edge slat of wing front end (1) is specific special-shaped tubular, and there is row's gap-shaped spout the upper end, the spout direction backward, aspirate tube (13) is positioned at the wing rear inner part, there is row's gap-shaped air suctiton inlet (14) top, air suctiton inlet is directed upwardly.
The 3rd feature is: driving engine (9) output shaft links to each other with air vane wheel shaft, the impeller (18) of both sides with the master and slave moving axis of transmission gearbox (21) successively.Blowing engine exhaust nozzle direction backwards.
The 4th feature is: blowing engine (8) spiral case below links to each other with conduit, control cock (26), and catheter nozzle (25) is positioned at fuselage (1) front end, and mouth of pipe direction down.
The 5th feature is: (Fig. 3, Fig. 4, Fig. 5) arc valve (27) is positioned at blowing engine (8) spiral case, and butterfly valve (23) (Fig. 1) is positioned at blowing engine air inlet pipe (17).
The principle of the flight that the present invention rises and falls is: (Fig. 3, Fig. 4, Fig. 5), before the engine starting, close the butterfly valve (23) in the blowing engine air inlet pipe (17), to reduce starting load.After the starting, butterfly valve standard-sized sheet, driving engine (9) drive main driven gear axle and both sides blower wheel (18) rotation in the transmission gearbox (21), and air suctiton inlet (14) sucks air on the aerofoil, blowing engine spiral case arc valve this moment (27) is positioned at the OA position, and (Fig. 3) wing flap (15) deflects down.After entering the supercharging air of blowing engine thus, be communicated with freeing pipe through arc valve (27).By leading edge slat (4), gap-shaped spout (5) ejection from its upper end, form aerofoil top jet, induce and entrainment near a large amount of air, flow backward thereupon, air-flow is inhaled into aspirate tube (13) once more by air suctiton inlet (14) near the top airfoil boundary-layer, sprays jet more again through air inlet pipe, blowing engine, freeing pipe, leading edge slat spout, so constantly circulates.(Fig. 3 flow streamline arrow)
Press the bernoulli's theorem of fluid energy conservation, wing top air quickens to flow, and relevant pressure must reduce, and this moment, wing below air was almost static, and pressure is higher relatively.Though aircraft is motionless, the upper and lower difference of pressure of wing also constitutes sizable lift L
1(Fig. 3).
The wing aspirate tube sucks the top air, also produces corresponding lift.And, form thrust T forward again through the jet that leading edge slat sprays backward
0(Fig. 3), promoting aircraft advances.
Aircraft advances, and for reducing resistance, handles wing flap (15) and upward deflects (Fig. 4).The blowing engine accelerated service keeps the corresponding acceleration of top airfoil circulation jet to flow, and superposes with the place ahead incoming flow, and (flow field shown in the arrow among Fig. 4) makes thrust T
1Lift L
1, L
2Corresponding increase overcomes aircraft gravity and takes off, and handles air jet duct road inner control valve (26) in case of necessity, helps to keep the aircraft balance in pitch.Driving engine and blower speed are higher, and take off distance is shorter, and take-off angle is bigger.
When big speed is flown, handle droope snoot and wing and be integrally combined.Simultaneously blowing engine arc valve (27) is turned to the OB position, close freeing pipe (16) passage, and spiral case internal channel standard-sized sheet, in the blowing engine behind spiral case passage diffusion air, directly from ejector exhaust pipe (7) ejection, thrust T (Fig. 5) is bigger, this moment state of flight and manipulation, and the control of balance and stability and conventional airplane flying method are basic identical.But because wing rear air suctiton inlet sucks air-flow, to the control of friction layer, make the aerofoil top not have burbling, not only thrust, lift increase, and resistance also reduces, thereby has improved the aerodynamic force quality of 1ift-drag ratio and complete machine.
During low-speed operations or when descending, handle and push leading edge slat (4) open, make and the wing front end between a fixed gap is arranged, arc valve (27) rotates and is back to the OA position simultaneously, and the blowing engine freeing pipe is communicated with, (Fig. 4), wing cocycle jet superposes with the place ahead incoming flow again, has bigger lift equally.As continue to descend, put down rear portion wing flap (15) (Fig. 3), speed is very little of equaling 0, sizable lift is still arranged, so its stalling speed is far below similar conventional airplane, not only safety is good, also the wide-angle safe falling be can realize, airport and runway generally do not needed.(also can on runway, rise and fall in addition) by the conventional airplane flying method
Wing flap among the present invention not only is used for aircraft takeoffs and landings, when turning to, also can be used as the attached wing and handles.
Description of drawings:
Fig. 1 is the structure birds-eye view of the present invention's " top airfoil circulation jet fixed-wing autogyro ", and arrow represents that air is expelled to leading edge slat circulation jet stack direction from leading edge slat through aerofoil top air suctiton inlet, aspirate tube, blowing engine.
Fig. 3, Fig. 4, Fig. 5 are respectively blowing engine of the present invention and thrust that wing constitutes and lift system, when different flight state, stream flow field, the sketch of the diverse location of (Fig. 3-Fig. 5 solid arrow) and associated components (droope snoot, arc valve, wing rear portion wing flap).
Each parts among Fig. 1-Fig. 5:
The 1-fuselage; Winglet before the 2-; 3-hangs wheel; The 4-leading edge slat; 5-gap-shaped spout; The 6-wing; The 7-ejector exhaust pipe; The 8-centrifugal blower; The 9-driving engine; The 10-exhaust pipe of engine; 11-leads cover; The 12-winglet; The 13-aspirate tube; 14---air suctiton inlet; The 15-wing flap; 16-blowing engine freeing pipe; 17-blowing engine air inlet pipe; The 18-impeller; The 19-vertical tail; The 20-yaw rudder; The 21-transmission gearbox; The 22-paddle shaft; The 23-butterfly valve; 24---preceding wing flap; The 25-catheter nozzle; The 26-control cock; The 27-arc valve (Fig. 3-Fig. 5).
Among Fig. 3-Fig. 5: each solid arrow represents to stream flow field, grain direction; ω-blower wheel spin velocity; T-thrust; L
1-airfoil lift; L
2-air-breathing additional the lift that causes; OA, OB-are respectively the arc valves that is in diverse location; V-the place ahead incoming flow
The specific embodiment:
Below in conjunction with accompanying drawing of the present invention, describe one of the present invention embodiment preferably in detail:
Title: top airfoil circulation jet fixed-wing autogyro
Form: ultra light aircraft
Oad: 3.85 meters of total lengths, 8.5 meters of overall withs, 1.75 meters of overall heights
Wing: the span: 8.4 meters, blade area: 10.08 sq ms
Preceding winglet: 3.6 meters of the spanes, blade area: 2.6 sq ms
Engine type: air-cooled, twin-tub, electric starting up gasoline engine, band gear reduction box
Maximum power: 40 kilowatts
Maximum speed: 6500 rev/mins
Weight: empty weight: 170 kilograms of maximum fuel weight: 30 liters of maximum take-off weights: 380 kilograms, can carry 2 people
Performance: max level speed: 150 kilometers/hour
Maximum cruise: 110 kilometers/hour
Stalling speed: 25 kilometers/hour
MAX CLB: 5.5 meter per seconds
Take off distance (wide-angle lifting): 30 meters
Practical ceiling: 3500 meters
Voyage; 300 kilometers, maximum range: single 800 kilometers of the additional fuel tanks that add
Maximum operating overload :+3.8g-1.9g
Advantage of the present invention is:
1, top airfoil circulating jet lift system of the present invention, bigger more than 30% than similar big or small conventional airplane airfoil lift and lift-drag ratio when big speed flight, low-speed operations lift, that lift-drag ratio improves ratio is bigger. Even air speed equals at 0 o'clock, sizable lift is arranged also. Can realize original place wide-angle lifting, comprehensive helicopter, short take-off and landing plane and conventional airplane advantage separately, and overcome its deficiency separately.
2, the two centrifugal blower jet thrust systems of the present invention, be arranged symmetrically with, balance is good, compact (being positioned at fuselage interior) resistance is little, there are not common similar properller and spiral wake flow thereof to the impact of other parts, when blower wheel rotates in addition, the gyro of generation (gyroscopic inertia) stabilization. So good stability of the present invention, reliability also is better than similar helicopter and other VTOL aircrafts.
3, the present invention not only wing produce lift, air entry produces different lift separately with front winglet in it, even aircraft is static or low-speed operations, rising and falling all has sizable lift, thereby greatly reduces the danger such as common flight stall or forced landing whereabouts, security is better.
4, wide-angle lifting of the present invention can smooth-goingly transit to climb, glide, flatly fly, other flight attitudes such as glide. Control, easy operation use flexiblely, are convenient to practice and extension.
The present invention can be widely used in the every field such as each public institution, enterprise, individual, civil aviaton, public affair, transportation, contact, military affairs, physical culture, contest, amusement, tourism, sightseeing, rescue and relief work, patrol and commerce.
Claims (5)
1. top airfoil circulation jet fixed-wing autogyro, comprise aspirate tube, centrifugal exhausting fan, air inlet-outlet pipe, arc valve, transmission gearbox, driving engine in fuselage, leading edge slat, wing, the wing, two centrifugal blowers that it is characterized in that symmetric arrangement lay respectively at driving engine, transmission gearbox both sides, the blowing engine air inlet pipe links to each other with aspirate tube, and freeing pipe links to each other with leading edge of a wing slat.
2. according to claims 1 described top airfoil circulation jet fixed-wing autogyro, it is characterized in that leading edge slat is specific special-shaped tubular, there is row's gap-shaped spout the upper end, and the spout direction backwards, aspirate tube is positioned at wing inside, and there is row's gap-shaped air suctiton inlet the top.
3. top airfoil circulation jet fixed-wing autogyro according to claim 1 is characterized in that engine output shaft connects the master and slave moving axis of transmission gearbox, paddle shaft, impeller successively, and blowing engine exhaust nozzle direction backwards.
4. top airfoil circulation jet fixed-wing autogyro according to claim 1 is characterized in that blowing engine spiral case below links to each other with conduit, control cock, and catheter nozzle is positioned at front fuselage, and mouth of pipe direction down.
5. top airfoil circulation jet fixed-wing autogyro according to claim 1 is characterized in that arc valve is positioned at the blowing engine spiral case, and butterfly valve is positioned at the blowing engine air inlet pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100445726A CN102120491A (en) | 2011-02-24 | 2011-02-24 | Upper-surface circulating jet fixed-wing helicopter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100445726A CN102120491A (en) | 2011-02-24 | 2011-02-24 | Upper-surface circulating jet fixed-wing helicopter |
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| CN102120491A true CN102120491A (en) | 2011-07-13 |
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| CN2011100445726A Pending CN102120491A (en) | 2011-02-24 | 2011-02-24 | Upper-surface circulating jet fixed-wing helicopter |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102506062A (en) * | 2011-09-30 | 2012-06-20 | 中国航空动力机械研究所 | Bearing and turboshaft engine with same |
| CN106945823A (en) * | 2017-03-28 | 2017-07-14 | 罗方越 | Wall-attached jet all-wing aircraft |
| RU2630270C2 (en) * | 2016-02-09 | 2017-09-06 | Степан Валентинович Суворов | Vertical takeoff and landing aircraft |
| CN110282128A (en) * | 2019-08-07 | 2019-09-27 | 西华师范大学 | A kind of vertically taking off and landing flyer |
| RU2712708C1 (en) * | 2019-05-13 | 2020-01-30 | Борис Никифорович Сушенцев | Aircraft with short or vertical take-off and landing |
| WO2021242463A3 (en) * | 2020-04-27 | 2022-03-03 | Jetoptera, Inc. | Vertical take off and landing aircraft with fluidic propulsion system |
| US11718403B2 (en) | 2015-04-15 | 2023-08-08 | Northrop Grumman Systems Corporation | Extremely quiet short take-off and landing (STOL) aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3592416A (en) * | 1968-06-05 | 1971-07-13 | Entwicklungsring Sued Gmbh | Vertical takeoff and landing aircraft |
| CN2334674Y (en) * | 1997-12-11 | 1999-08-25 | 崔建新 | Air jet power increasing wing |
| CN1803533A (en) * | 2006-01-09 | 2006-07-19 | 李志文 | Air current circulation aircraft and method for making the same |
| CN2827873Y (en) * | 2005-07-06 | 2006-10-18 | 雷良榆 | Helicopter with airfoil fluidic fixing wing |
-
2011
- 2011-02-24 CN CN2011100445726A patent/CN102120491A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3592416A (en) * | 1968-06-05 | 1971-07-13 | Entwicklungsring Sued Gmbh | Vertical takeoff and landing aircraft |
| CN2334674Y (en) * | 1997-12-11 | 1999-08-25 | 崔建新 | Air jet power increasing wing |
| CN2827873Y (en) * | 2005-07-06 | 2006-10-18 | 雷良榆 | Helicopter with airfoil fluidic fixing wing |
| CN1803533A (en) * | 2006-01-09 | 2006-07-19 | 李志文 | Air current circulation aircraft and method for making the same |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102506062A (en) * | 2011-09-30 | 2012-06-20 | 中国航空动力机械研究所 | Bearing and turboshaft engine with same |
| US11718403B2 (en) | 2015-04-15 | 2023-08-08 | Northrop Grumman Systems Corporation | Extremely quiet short take-off and landing (STOL) aircraft |
| RU2630270C2 (en) * | 2016-02-09 | 2017-09-06 | Степан Валентинович Суворов | Vertical takeoff and landing aircraft |
| CN106945823A (en) * | 2017-03-28 | 2017-07-14 | 罗方越 | Wall-attached jet all-wing aircraft |
| RU2712708C1 (en) * | 2019-05-13 | 2020-01-30 | Борис Никифорович Сушенцев | Aircraft with short or vertical take-off and landing |
| CN110282128A (en) * | 2019-08-07 | 2019-09-27 | 西华师范大学 | A kind of vertically taking off and landing flyer |
| WO2021242463A3 (en) * | 2020-04-27 | 2022-03-03 | Jetoptera, Inc. | Vertical take off and landing aircraft with fluidic propulsion system |
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Application publication date: 20110713 |