Vertical take-off and landing aircraft
阅读：776发布：2023-12-31
专利汇可以提供Vertical take-off and landing aircraft专利检索，专利查询，专利分析的服务。并且A VTOL aircraft is powered on regular fixed wing flight by a pair of jet engines on the after quarter of the fuselage and achieves vertical take-off and landing under the power of an articulated tail rotor which is retractable into a storage compartment of the fuselage during conversion from rotor flight to fixed wing flight. The take-off and landing rotor derives power for its blade tip jet nozzles through internal ducting which receives jet engine exhaust gas through a diversion system connected in the main jet exhaust nozzle of each engine. By-pass air is also diverted from each engine to the interior of the rotor blades and is further directed to rotor blade jet flap slots for maintaining rotor cyclic and collective pitch control without the customary complex mechanisms. Rotor directional control is maintained by diverting additional by-pass air to certain fixed wing jet flap slots. A mechanical traction device is utilized to retract and extend the rotor.，下面是Vertical take-off and landing aircraft专利的具体信息内容。
1. A vertical take-off and landing aircraft comprising a fixed wing aircraft body portion having a pair of jet propulsion engines and a rear opening longitudinal fuselage rotor stowage compartment, a take-off and landing rotor for the aircraft adapted when deployed outside of said stowage compartment to lift the aircraft tail upwardly with the nose of the craft downwardly, a carriage means for said rotor having tracked engagement with said stowage compartment, power traction means connected with said carriage means to move the carriage means in opposite directions in the stowage compartment for retracting and deploying the rotor, said rotor comprising a mast including rotating and non-rotating parts, means forming a universal type mechanical connection between the carriage means and non-rotating part of the mast, a pair of lifting rotor blades having jet nozzle means at their tips and jet flap slots near longitudinal edges thereof, mechanical linkage means pivotally connecting said blades to the rotating part of said mast in such a manner that the blades may fold upwardly into substantial parallelism to facilitate retraction thereof into said stowage compartment, valved conduit means for diverting exhaust gas from said jet engines and delivering the same through said mast and rotor blades to said tip jet nozzle means to produce rotation of said blades, and additional valved conduit means for diverting by-pass air from said jet engines and delivering it cyclically and variably through said mast and blades to said jet flap slots, said valved conduit means for diverting exhaust gas comprising a duct connected in the exhaust jet nozzle of each engine and leading to and joined with a common center exhaust gas duct in the after portion of the aircraft fuselage, a coacting common exhaust gas duct on the carriage means and movable therewith, and means forming a sliding seal between opposing ends of said common ducts whereby exhaust gas may pass from one into the other without leakage when the common ducts are in registry.
2. The structure of claim 1, and a flexible duct section for exhaust gas interconnecting said non-rotating rotor mast part and said common exhaust gas duct of the carriage means.
3. The structure of claim 1, and said aircraft body portion having a floor partition and rear facing passenger seats in the fuselage above the rotor stowage compartment.
4. The structure of claim 3, and a cockpit in the nose portion of the fuselage including seats and aircraft controls for a first pilot who pilots the aircraft during normal fixed wing flight and for a second pilot who pilots the aircraft during rotor flight while the fuselage is substantially vertical and nose down.
5. The structure of claim 4, and a shock-absorbing nose structure on the fuselage to facilitate landing the aircraft nose downwardly into contact with the ground.
6. The structure of claim 4, and said cockpit having windows for the two pilots on the top and bottom of the aircraft nose, the seat for the rotor flight pilot facing downwardly and rearwardly adjacent the windows on the bottom of the nose.
7. The structure of claim 1, and a door hingedly secured to the rear of the fuselage and serving in one position to cover the rear open end of said rotor stowage compartment and serving in a second position as a ground support for the aft end of the fuselage, and guidance means for folded rotor blades on said door operable in the open position of the door to assist in guiding the rotor into the stowage compartment.
8. The structure of claim 7, and a shock-absorbing means on the rotor stowage door adapted to contact the ground at the completion of landing of the aircraft.
9. The structure of claim 5, and means to guide and lock into place in an uPright position the mast structure of said rotor on landing of the aircraft when the fuselage thereof moves to a substantially horizontal position and the rotor is stopped.
10. The structure of claim 7, and a power actuator for said door mounted in said fuselage.
11. The structure of claim 1, and means to automatically rotate the rotor on its axis with the rotor blades folded so as to properly align the folded blades for proper entry lengthwise into said stowage compartment.
12. The structure of claim 1, and a center located fixed target thrust spoiler near the aft portion of the fuselage, and a coacting power-operated thrust reverser door adjacent the thrust spoiler, whereby the exhaust gas from both aircraft engines may be directed to the thrust spoiler.
13. The structure of claim 12, and said thrust spoiler being tiltable to assist in maneuvering the aircraft out of a dive at low speed for rapid conversion from rotor flight to fixed wing flight.
14. The structure of claim 1, and linkage means interconnecting the rotating part of said mast and said blades to stabilize the blades and to control and limit flapping thereof, said linkage means including a pair of fluid pressure activated cylinder units which control and dampen the flapping action of said blades.
15. The structure of claim 1, and each lifting rotor blade having an internal exhaust gas distribution system directing exhaust gas to said blade tip jet nozzle means, and each blade having an internal chamber and guidance means directing by-pass air to said blade jet flap slots.
16. A vertical take-off and landing aircraft comprising a fixed wing aircraft body portion having a pair of jet propulsion engines and a rear opening longitudinal fuselage rotor stowage compartment, a take-off and landing rotor for the aircraft adapted when deployed outside of said stowage compartment to lift the aircraft tail upwardly with its nose downwardly, a carriage means for said rotor having tracked engagement with said stowage compartment, power traction means connected with said carriage means to move the carriage means in opposite directions in the stowage compartment for retracting and deploying the rotor, said rotor comprising a mast including rotating and non-rotating parts, means forming a universal type mechanical connection between the carriage means and non-rotating part of the mast, a pair of lifting rotor blades having jet nozzle means at their tips and jet flap slots near longitudinal edges thereof, mechanical linkage means pivotally connecting said blades to the rotating part of said mast in such a manner that the blades may fold upwardly into substantial parallelism to facilitate retraction thereof into said stowage compartment, valved conduit means for diverting exhaust gas from said jet engines and delivering the same through said mast and rotor blades to said tip jet nozzle means to produce rotation of said blades, additional valved conduit means for diverting by-pass air from said jet engines and delivering it cyclically and variably through said mast and blades to said jet flap slots, said additional valved conduit means diverting by-pass air from said jet engines comprising a by-pass air duct connected in the by-pass air channel of each jet engine and leading to and connected in a common by-pass air duct in the after portion of the fuselage and near the center thereof, said common by-pass air duct being divided into two valved branches and said two branches being sub-divided into four duct branches, a like number of by-pass air duct branches on the carriage means and movable therewith, and means forming a sliding seal between the opposed mouths of said four duct branches on the fuselage and coacting branches on the carriage means.
17. The structure of claim 16, and plural flexible duct sections for by-pass air interconnecting said duct branches on the carriage means with variable by-pass air passages of the rotor mast.
18. The structure of claim 17, and additional flexible duct sections cOnnected with the rotating part of the mast and the interior of said rotor blades and placing the jet flap slots of the rotor blades in communication with said variable passages of the rotor mast.
19. The structure of claim 18, and said variable by-pass air passages of the rotor mast including relatively stationary quadrant passages in the non-rotating part of said mast,and a pair of divided by-pass air passages in the rotating part of the mast and being circumferentially coextensive with the non-rotating quadrant passages and movable relative thereto circumferentially to cylically vary the movement of by-pass air to said rotor blade jet flap slots.
20. A vertical take-off and landing aircraft comprising a fixed wing aircraft body portion having a pair of jet propulsion engines on opposite sides of the aircraft fuselage, said fuselage having a longitudinal rear opening rotor stowage compartment, a lifting rotor for the aircraft adapted to be deployed through the rear of the stowage compartment and raising and lowering the aircraft in a nose down vertical attitude for take-off and landing, mechanical power means connected with the rotor to retract the same into the stowage compartment and to move the rotor rearwardly therefrom, said rotor including a pair of hinged foldable airfoil blades having jet nozzles thereon to produce rotation of the rotor and having jet flap slots by means of which the pitch of the blades and the directional attitude of the rotor may be regulated, fixed conduit means on the aircraft body portion connected with said jet propulsion engines for diverting exhaust gas and by-pass air therefrom for delivery to the rotor, coacting conduit means movable with the rotor into selaed registration with the fixed conduit means when the rotor is deployed, and passage means on the rotor and within the blades thereof for delivering engine exhaust gas to said blade jet nozzles and for cyclically and variably delivering by-pass air from the engines to said blade jet flap slots.
21. The structure of claim 20, and adjustable valving means in the fixed conduit means for regulating the volumetric flow of exhaust gas and by-pass air diverted from said engines to the rotor.
22. The structure of claim 20, and a mast structure for said lifting rotor including rotating and non-rotating interfitting components, said components having divided exhaust gas passage means and divided relatively movable variable passage means for by-pass air, and said last-named exhaust gas and by-pass air passage means of the mast structure communicating with said coacting movable conduit means.
23. A vertical take-off and landing aircraft comprising a fixed wing aircraft body portion having a pair of jet propulsion engines and a rear opening longitudinal fuselage rotor stowage compartment, a take-off and landing rotor for the aircraft adapted when deployed outside of said stowage compartment to lift the aircraft tail upwardly with the nose of the craft downwardly, a carriage means for said rotor having tracked engagement with said stowage compartment, power traction means connected with said carriage means to move the carriage means in opposite directions in the stowage compartment for retracting and deploying the rotor, said rotor comprising a mast including rotating and non-rotating parts, means forming a universal type mechanical connection between the carriage means and non-rotating part of the mast, a pair of lifting rotor blades having jet nozzle means at their tips and jet flap slots near longitudinal edges thereof, mechanical linkage means pivotally connecting said blades to the rotating part of said mast in such a manner that the blades may fold upwardly into substantial parallelism to facilitate retraction thereof into said stowage compartment, valved conduit means for diverting exhaust gas from said jet engines and delivering the same through said mast and rotor blades to said tip jet nozzle means to produce rotation of said blades, additional valved conduit means for diverTing by-pass air from said jet engines and delivering it cyclically and variably through said mast and blades to said jet flap slots, and additional by-pass air duct means for delivering by-pass air to fixed wing jet flaps and elevator jet flaps on the aircraft.
24. A vertical take-off and landing aircraft comprising a fixed wing aircraft body portion having a pair of jet propulsion engines and a rear opening longitudinal fuselage rotor stowage compartment, a take-off and landing rotor for the aircraft adapted when deployed outside of said stowage compartment to lift the aircraft tail upwardly with the nose of the craft downwardly, a carriage means for said rotor having tracked engagement with said stowage compartment, power traction means connected with said carriage means to move the carriage means in opposite directions in the stowage compartment for retracting and deploying the rotor, said rotor comprising a mast including rotating and non-rotating parts, means forming a universal type mechanical connection between the carriage means and non-rotating part of the mast, a pair of lifting rotor blades having jet nozzle means at their tips and jet flap slots near longitudinal edges thereof, mechanical linkage means pivotally connecting said blades to the rotating part of said mast in such a manner that the blades may fold upwardly into substantial parallelism to facilitate retraction thereof into said stowage compartment, valved conduit means for diverting exhaust gas from said jet engines and delivering the same through said mast and rotor blades to said tip jet nozzle means to produce rotation of said blades, additional valved conduit means for diverting by-pass air from said jet engines and delivering it cyclically and variably through said mast and blades to said jet flap slots, and automatic valve means in said valved conduit means for diverting exhaust gas and in said additional valved conduit means for diverting by-pass air and being automatically operable in response to failure of either aircraft engine to assure a continued adequate flow of exhaust gas and by-pass air to said rotor.
25. The structure of claim 24, and said automatic valve means consisting of a pair of independently pivoted flip-flop valve plate elements in said conduit means and additional conduit means and being automatically self-centering in the presence of exhaust gas and by-pass air streams from both of said engines.
26. A vertical take-off and landing aircraft having a tail lifting take-off and landing rotor and fixed wing means for normal flight, a pair of laterally spaced jet engines on the aircraft including exhaust gas and by-pass air passage means, said rotor having a pair of airfoil blades containing jet flap slots for regulating blade pitch and also having blade tip jet nozzles for producing rotation of the rotor, and a jet flap cyclic control system for the rotor which includes a bifurcated duct for by-pass air diverted from the by-pass air passage means of said engines, a valve immediately upstream from said bifurcated duct enabling by-pass air to be directed into either branch of the bifurcated duct, another valve arranged in each branch of the bifurcated duct and having common control means, an additional pair of sub-branch ducts leading from each said branch of the bifurcated duct, said sub-branches being downstream from said valves in said branches having the common control means, whereby the volume of by-pass air to any of the sub-branch ducts can be varied, a rotor mast structure intervened between said sub-branch ducts and blade jet flap slots and containing a circumferential passage for by-pass air divided into four quadrants which are non-rotating, said mast structure having a mating interfitting circumferential passage for by-pass air which is divided into a pair of semi-circular segments and which rotates, said quadrants and semi-circular segments communicating to achieve cyclic variation in the volume of by-pass air being delivered to the blade jet flap slots, anotHer pair of ducts interconnecting said semi-circular segments with an interior chamber of each rotor blade leading to the jet flap slot of the blade, and valved conduit means between the aircraft engines and interior passage means of said blades for delivering engine exhaust gas to said blade tip jet nozzles.
27. The structure of claim 26, and said valved conduit means for delivering said exhaust gas including a passage for exhaust gas in the rotating part of the mast structure and inwardly of said quadrants, said passage being internally divided into two sections each delivering exhaust gas to the tip jet nozzle of one rotor blade.
28. The structure of claim 26, and a blade root arm for each rotor blade, a pair of hinge supports for said root arms to allow upward folding of the blades and varying of the blade coning angle, said hinge supports carried by the rotating part of the rotor mast structure, means forming a single teetering hinge above said hinge supports, blade fold-up slide pole means extending above the teetering hinge, slide units movably mounted on the slide pole means, and a pair of widely spaced blade support arms connected to each blade near the leading and trailing edges thereof, said arms also connected with said slide units.
29. The structure of claim 26, and each of said airfoil blades of the rotor comprising a hollow blade body, an insulated unitary exhaust gas duct system slidable as a unit into the blade body, a bolt-on blade tip cascade nozzle structure for the blade body communicating with said duct system, and a bolt-on blade root end plate for the blade body serving to anchor said duct system and adding structural integrity and rigidity to the blade.
30. The structure of claim 29, and a slip-type expansion joint between said dut system and blade tip cascade nozzle structure.
31. The structure of claim 26, and said first and second named valves comprising butterfly-type valves having off-center pivots and being self-centering in the slipstream in which they are disposed in the absence of a positive controlling force thereon.
| 标题 | 发布/更新时间 | 阅读量 |
|---|---|---|
| 无人机起落架电动伸缩机构 | 2020-05-08 | 214 |
| 一种起落架试验载荷加载装置 | 2020-05-08 | 641 |
| 自带发电机的用电产品 | 2020-05-08 | 117 |
| 一种功能可扩展的房屋结构 | 2020-05-08 | 269 |
| 一种快速起落无人机以及无人机的起落控制方法 | 2020-05-11 | 709 |
| 一种智能城市监控无人机 | 2020-05-08 | 284 |
| 一种野生动物自然保护区监测用无人机 | 2020-05-11 | 89 |
| 一种无人机仿生起落架 | 2020-05-08 | 354 |
| 一种一次成型的方形管材切割装置 | 2020-05-08 | 599 |
| 碟形五轴多旋翼机 | 2020-05-08 | 871 |
高效检索全球专利专利汇是专利免费检索,专利查询,专利分析-国家发明专利查询检索分析平台，是提供专利分析，专利查询，专利检索等数据服务功能的知识产权数据服务商。
我们的产品包含105个国家的1.26亿组数据，免费查、免费专利分析。
分析报告
专利汇分析报告产品可以对行业情报数据进行梳理分析，涉及维度包括行业专利基本状况分析、地域分析、技术分析、发明人分析、申请人分析、专利权人分析、失效分析、核心专利分析、法律分析、研发重点分析、企业专利处境分析、技术处境分析、专利寿命分析、企业定位分析、引证分析等超过60个分析角度，系统通过AI智能系统对图表进行解读，只需1分钟，一键生成行业专利分析报告。
起落架热门专利
QQ群二维码
意见反馈
意见反馈