CN1978277A - Combined rotor aircraft - Google Patents
Combined rotor aircraft Download PDFInfo
- Publication number
- CN1978277A CN1978277A CN 200510129377 CN200510129377A CN1978277A CN 1978277 A CN1978277 A CN 1978277A CN 200510129377 CN200510129377 CN 200510129377 CN 200510129377 A CN200510129377 A CN 200510129377A CN 1978277 A CN1978277 A CN 1978277A
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- China
- Prior art keywords
- bevel gear
- occupant
- parachute
- survival capsule
- hatch door
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Abstract
This invention relates to a new design for combined rotorcrafts, which applies a technology of flat airframe, a lift rotor-fan, an axial drive airscrew, an alternate power conversion distribution unit and a split passenger/lifesaving cabin to get fine stability, higher flying speed, sail, safety factor and vertical lifting, sliding running and flying-off in short and super-short distances and landing ability, the design of the combined rotorcrafts breaks away the traditional mode of the current rotor and bias rotor airplanes from outlook to the whole distribution.
Description
Technical field
A kind of combined rotor aircraft belongs to the aeronautical technology field
Background technology
The inclined to one side autogiro of unique in the world production at present and place in operation is through the inclined to one side rotor transport plane of the MV-22 " osprey " of development for many years by the U.S..But through to its use with to the analysis of pertinent data picture, this type aircraft also exists many deficiencies and defective at present, as take off vertically switch transition to flat fly or from flat when flying to be transformed into vertical and landing the ability of balance relatively poor, switching mechanism complexity, a series of problems such as rotor steering shaft moment of torsion is big partially, fixed-wing is less and reach because of rotor diameter is excessive when flat flying that the resistance that causes increases, consumption of fuel height and the serious flight safety coefficient that causes because of no single-shot balance flight performance are low.This combined type autogiro just under this background for solving the design plan of a kind of new ideas distribution form that existing inclined to one side rotor, the existing problem of rotor class aircraft work out.
Summary of the invention
Order of the present invention ground is exactly for addressing the above problem and the not enough a kind of combined rotor aircraft that provides
Realize order of the present invention ground and solution be this autogiro with existing rotor and partially the aircraft of rotor class many fundamentally different are arranged.It has adopted technology such as flat fuselage, lifting rotor fan, shaft type drving sprial oar, alternative expression power conversion distributor gears, split type occupant/survival capsule, thereby makes this machine obtain good stable, higher flying speed, voyage far away, higher aircraft passenger safety factor and multiple load prestowage form and technical performances such as vertical takeoff and landing, short distance or super-short distance rolling start, landing ability and good maneuvering performance.
The combined type autogiro is made up of flat fuselage, lifting rotor fan, shaft type drving sprial slurry, alternative expression power conversion distributor gears, split type occupant/survival capsule five parts:
Flat fuselage 1 front portion is provided with upper and lower aperture that driving compartment 2 fuselage middle front parts and rear portion be respectively equipped with lifting rotor fan mounting hole 3 mounting holes 3 of two tandem layouts and is provided with venetian blind type bucket cover 4 lower blades lid blade and can swings, (as shown in Figure 6) also be provided with in mounting hole 3 and be provided with axis hole in the middle of lifting rotor fan braket 5 supports, it is that machinery space 7 is provided with split type occupant/survival capsule matrix and places slideway 8 and be provided with tailplane 9 and two vertical tails 10 at afterbody on waist that fixed wing 6 waists are equipped with in the waist both sides
Double-deck lifting rotor fan 11 is installed in the rotating shaft 12, and rotating shaft 12 is installed in the axis hole of power rotor fan mounting hole 3 inner supports 5, and bevel gear 13 is housed in the middle of the rotating shaft 12
Shaft type drving sprial oar 14 is installed on the top of the screw propeller rotating shaft 15 on the fuselage both sides fixed wing 6, and bevel gear 16 is installed on the other end of rotating shaft 15
The afterburning h type engine h 17 of alternative expression power conversion distributor gears is installed in the middle machinery space 7 of fuselage, on the output shaft 18 at driving engine two ends, be separately installed with power-transfer clutch 19 power-transfer clutchs 19 and change-speed box 20 UNICOMs, driving bevel gear 22 driving bevel gears 22 and 23 engagements of transmission bevel gear are installed on the top of the take-off (propeller) shaft 21 of change-speed box 20 to be driven rotating shafts 12 and drives double-deck lifting rotor fan 11 and rotate, power distribution bevel gear 24 power distribution bevel gears 24 and 25 engagements of side transmission bevel gear also are housed on the take-off (propeller) shaft before driving engine, power-transfer clutch 26 power-transfer clutchs 26 and change-speed box 27 UNICOMs are installed on the output shaft of side transmission bevel gear 25, on the top of the take-off (propeller) shaft 28 of change-speed box 27 transmission bevel gear 29 transmission bevel gears 29 are installed and drive bevel gear 16 screw propeller rotating shafts 15 and screw propeller 14 rotations
Split type occupant/survival capsule 30 is placed in the matrix of fuselage middle and upper part and places on the slideway 8, the centre that the end draw runner 31 of occupant/survival capsule 30 and matrix are placed slideway 8, connect by quick-fried disconnected Luo bolt 32, occupant/survival capsule 30 bottoms are provided with the top that automatic inflatable pneumatic bag 34 occupants/survival capsule 30 is housed in 33 cabins, the open air bag of matrix cabin and are provided with in emergent articles for use cabin 35 and parachute compartment 36 parachute compartments parachute 37 is housed, the top of parachute compartment 36 is provided with and is provided with hinge device 39 between parachute hatch door 38 parachute hatch doors 38 and the occupant's survival capsule and makes to realize rotating between hatch door 39 and the occupant/survival capsule 30 and connect, the quick-fried disconnected Luo bolt 40 that is located at hatch door 38 front portions makes occupant/survival capsule and 38 realizations of hatch door fixed, the hauling rope 43 that extraction parachute 42 extraction parachute lower ends are housed in hatch door 38 tops also are provided with extraction parachute cludy 41 cludies by the hatch door front along on open-type half slot 44 connects with the top of parachute, on hauling rope 42, also be provided with confession and draw back 38 of the yi word pattern intermediate rod 45 extraction parachute cludies 41 of hatch door 38 usefulness and hatch doors by quick-fried Broken bolt 46 connections
Transport pipe 47 bunkers 48 wheels 49
Description of drawings
Accompanying drawing 1 is the combined rotor aircraft front elevation
Accompanying drawing 2 is combined rotor aircraft elevational cross-sectional view
Accompanying drawing 4 is that combined rotor aircraft is overlooked the A-A cutaway view
Accompanying drawing 5 is combined rotor aircraft lateral plans
Accompanying drawing 6 is occupant/survival capsule B-B explosion views
Accompanying drawing 7 is the local amplification views of occupant/survival capsule
Accompanying drawing 8 is occupant/survival capsule working process scheme drawings
Specific embodiments
The invention will be further described below in conjunction with view:
When aircraft takes off vertically, before opening venetian blind type bucket cover 4 earlier and starting afterburning h type engine h 17 closed power-transfer clutch 19 change-speed boxs 20 then and drive, back take-off (propeller) shaft 21 driving bevel gears 22 drive transmission bevel gear 23 and drive 11 commentaries on classics of rotating shaft 12 lifting rotor fans, at this moment aircraft just can be realized the vertical takeoff and landing of aircraft and hover under the lift effect that lifting rotor fan 11 provides, when aircraft need fly forward, with regard to the start the engine augmenter, power-transfer clutch 26 change-speed boxs 27 of closed both sides make take-off (propeller) shaft 28 transmission bevel gears 29 driving bevel gears 16 screw propeller rotating shafts 15 rotation screw propellers 14 make aircraft obtain to promote to realize flying forward simultaneously.After aircraft reaches certain speed, fixed wing 6 and has produced enough lift, be that holdback clutch 19 makes 11 stalls of lifting rotor fan, and the augmenter and close upper and lower venetian blind type bucket cover 4 and make aircraft enter normal level flight of killing engine, when aircraft arrival destination needed vertical landing or hovers, the inverse process that can repeat the aforesaid operations program got final product.When hang, also blade of louver window lid blade (as shown in Figure 6) makes aircraft obtain the transverse displacement kinetic force under the adjustable swing
When balance was adjusted various rotating speed between lifting rotor fan 11 and the screw propeller 14, aircraft just can obtain different landing effects: reach the various variable loads that adapt with it as short distance, ultrashort distance
Use as the crew module when split type occupant/survival capsule 30 is flat, but when in a single day aircraft aloft has an accident, just can be used as survival capsule uses, in use, earlier quick-fried disconnected quick-fried Broken bolt 32,40,46 is opened extraction parachute 42 simultaneously under the effect of extraction parachute 42 hauling ropes 43 and yi word pattern intermediate rod 45 pulling force, parachute hatch door 38 is opened backward, and parachute 37 is drawn back, and the pulling force that parachute 37 produces is pulled away from aircraft with occupant/survival capsule 30 along matrix placement slideway 8.In after occupant/survival capsule breaks away from aircraft, automatically open automatic inflatable pneumatic bag 34 rapidly and reduce to minimum and safe falling to make the vibrations of split type occupant/survival capsule when landing as far as possible, for being rescued, occupant safety provide safe rescuing to ensure simultaneously, the aviator also can be rescued by ejection bailout, under the situation that this external condition is allowed, aircraft occupant/survival capsule disembark reduced weight and hazard level after, also can win the condition and the time of the trouble-shooting of lot of valuable for chaufeur.When this type machine uses as military secret, can weapon is under the wings of an airplane plug-in, and crew module's part no longer is set.
The design of combined rotor aircraft has broken away from existing rotor, the inclined to one side traditional Design Mode of rotor class aircraft fully from the outward appearance to the integral layout, thereby make this machine obtain the Combination property advantage of above-mentioned polytype aircraft, and the multinomial technology that this machine adopts in design also can provide some important reference approach for the innovative design of existing helicopter, rotor class aircraft.
Claims (6)
1, a kind of combined rotor aircraft is made up of flat fuselage, lifting rotor fan, shaft type drving sprial oar, alternative expression power conversion distributor gears, split type occupant/survival capsule five parts the combined type autogiro, it is characterized in that: be equipped with in the flat fuselage (1) to be equipped with in shaft type drving sprial oar (14) fuselage in lifting rotor (11) wing (6) that series type installs alternative expression power conversion distributor gears is housed, back is provided with split type occupant/survival capsule (30).
2, according to the described combined rotor aircraft of claim (1), it is characterized in that: flat fuselage (1) front portion be provided with driving compartment (2) fuselage middle front part and rear portion be respectively equipped with two tandem layouts lifting rotor fan mounting hole (3) mounting hole (3) on, following aperture is provided with venetian blind type bucket cover (4) lower blade lid blade and can swings, and (as shown in Figure 6) also is provided with the middle axis hole that is provided with of lifting rotor fan braket 5 supports in mounting hole (3), it is that machinery space (7) is provided with split type occupant/survival capsule matrix and places slideway (8) and be provided with tailplane (9) and pair vertical tail (10) at afterbody on waist that fixed wing (6) waist is equipped with in the waist both sides.
3, according to the described combined rotor aircraft of claim (1), it is characterized in that: double-deck lifting rotor fan (11) is installed in the rotating shaft (12), rotating shaft (12) is installed in the axis hole of power rotor fan mounting hole (3) inner support (5), and bevel gear (13) is housed in the middle of the rotating shaft (12).
4, according to the described combined rotor aircraft of claim (1), it is characterized in that: shaft type drving sprial oar (14) is installed on the top of the screw propeller rotating shaft (15) on the fuselage both sides fixed wings (6), and bevel gear (16) is installed on the other end of rotating shaft (15).
5, according to the described combined rotor aircraft of claim (1), it is characterized in that: the afterburning h type engine h (17) of alternative expression power conversion distributor gears is installed in the middle machinery space (7) of fuselage, on the output shaft (18) at driving engine two ends, be separately installed with power-transfer clutch (19) power-transfer clutch (19) and change-speed box (20) UNICOM, driving bevel gear (22) driving bevel gear (22) and transmission bevel gear (23) engagement are installed on the top of the take-off (propeller) shaft (21) of change-speed box (20) to be driven rotating shaft (12) and drives double-deck lifting rotor fan (11) and rotate, power distribution bevel gear (24) power distribution bevel gear (24) and side transmission bevel gear (25) engagement also are housed on the take-off (propeller) shaft before driving engine, power-transfer clutch (26) power-transfer clutch (26) and change-speed box (27) UNICOM are installed on the output shaft of side transmission bevel gear (25), are equipped with on the top of the take-off (propeller) shaft (28) of change-speed box (27) that transmission bevel gear (29) transmission bevel gear (29) drives bevel gear (16) screw propeller rotating shaft (15) and screw propeller (14) rotates.
6, according to the described combined rotor aircraft of claim (1), it is characterized in that: split type occupant/survival capsule (30) is placed in the matrix of fuselage middle and upper part and places on the slideway (8), the end draw runner (31) of occupant/survival capsule (30) and matrix are placed the centre of slideway 8, connect by quick-fried disconnected Luo bolt (32), occupant/survival capsule (30) bottom is provided with the top that automatic inflatable pneumatic bag (34) occupant/survival capsule (30) is housed in the cabin, the open air bag of matrix cabin (33) and is provided with the top that parachute (37) parachute compartment (36) is housed in emergent articles for use cabin (35) and parachute compartment (36) parachute compartment and is provided with and is provided with hinge device (39) between parachute hatch door (38) parachute hatch door (38) and the occupant's survival capsule and makes that the realization rotation connects between hatch door (39) and the occupant/survival capsule (36), being located at the anterior quick-fried disconnected Luo bolt (40) of hatch door (38) makes between occupant/survival capsule and hatch door (38) realization fixed, the hauling rope (43) that extraction parachute (42) extraction parachute lower end is housed in hatch door (38) top also is provided with extraction parachute cludy (41) cludy connects with the top of parachute along last open-type half slot (44) by the hatch door front, is connect by quick-fried Broken bolt (46) between also being provided with for yi word pattern intermediate rod (45) extraction parachute cludy (41) that draws back hatch door (38) usefulness and hatch door (38) on the hauling rope (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200510129377 CN1978277A (en) | 2005-12-09 | 2005-12-09 | Combined rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200510129377 CN1978277A (en) | 2005-12-09 | 2005-12-09 | Combined rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1978277A true CN1978277A (en) | 2007-06-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200510129377 Pending CN1978277A (en) | 2005-12-09 | 2005-12-09 | Combined rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1978277A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8070089B2 (en) | 2008-03-25 | 2011-12-06 | Eurocopter | Hybrid helicopter that is fast and has long range |
| CN102963531A (en) * | 2012-10-31 | 2013-03-13 | 西安韦德沃德航空科技有限公司 | Non-coaxial multi-rotor-wing VTOL (Vertical Take-Off and Landing) flying machine capable of getting back safely |
| CN103079955A (en) * | 2010-07-19 | 2013-05-01 | 吉·埃罗公司 | Personal aircraft |
| CN103796917A (en) * | 2011-07-19 | 2014-05-14 | 吉.埃罗公司 | Personal aircraft |
| CN103832583A (en) * | 2012-11-26 | 2014-06-04 | 罗傲 | Airplane with lift force balance fans and tiltable rotor wings |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN105691588A (en) * | 2016-04-05 | 2016-06-22 | 浙江大学 | Device and method for linkage opening of airbag hatch cover |
| CN106005394A (en) * | 2016-07-22 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Rescue aircraft |
| CN112660370A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Modal-variable technology verification machine |
-
2005
- 2005-12-09 CN CN 200510129377 patent/CN1978277A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101559832B (en) * | 2008-03-25 | 2012-05-23 | 尤洛考普特公司 | Fast hybrid helicopter with large range |
| US8070089B2 (en) | 2008-03-25 | 2011-12-06 | Eurocopter | Hybrid helicopter that is fast and has long range |
| CN103079955B (en) * | 2010-07-19 | 2016-03-30 | 吉·埃罗公司 | Personal aircraft |
| US9845150B2 (en) | 2010-07-19 | 2017-12-19 | Kitty Hawk Corporation | Personal aircraft |
| CN103079955A (en) * | 2010-07-19 | 2013-05-01 | 吉·埃罗公司 | Personal aircraft |
| CN103796917A (en) * | 2011-07-19 | 2014-05-14 | 吉.埃罗公司 | Personal aircraft |
| US9242738B2 (en) | 2011-07-19 | 2016-01-26 | Zee.Aero Inc. | Personal aircraft |
| US10974838B2 (en) | 2011-07-19 | 2021-04-13 | Wisk Aero Llc | Personal aircraft |
| US11939071B2 (en) | 2011-07-19 | 2024-03-26 | Wisk Aero Llc | Personal aircraft |
| CN102963531A (en) * | 2012-10-31 | 2013-03-13 | 西安韦德沃德航空科技有限公司 | Non-coaxial multi-rotor-wing VTOL (Vertical Take-Off and Landing) flying machine capable of getting back safely |
| CN103832583A (en) * | 2012-11-26 | 2014-06-04 | 罗傲 | Airplane with lift force balance fans and tiltable rotor wings |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN105173070B (en) * | 2015-07-30 | 2018-08-14 | 北京航空航天大学 | A kind of combined type unmanned helicopter |
| CN105691588A (en) * | 2016-04-05 | 2016-06-22 | 浙江大学 | Device and method for linkage opening of airbag hatch cover |
| CN106005394A (en) * | 2016-07-22 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Rescue aircraft |
| CN112660370A (en) * | 2020-12-29 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Modal-variable technology verification machine |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |