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11. 发明授权

US4904157A Aircraft propeller assembly with blade pitch reset for ground idle 失效
标题翻译：飞机螺旋桨总成，叶片间距重新设置，用于地面怠速
公开(公告)号：US4904157A
公开(公告)日：1990-02-27
申请号：US274466
申请日：1988-11-21
申请人： Loy D. Pace , Donald C. Stackhouse , Earl W. Jones , Dennis S. Zimpfer
发明人： Loy D. Pace , Donald C. Stackhouse , Earl W. Jones , Dennis S. Zimpfer
IPC分类号： B64C11/40
CPC分类号： B64C11/40
摘要： An aircraft propeller has adjustable pitch blades which are reset from a low pitch in-flight idle position to a lower pitch ground idle position by a beta feedback and reset mechanism. The reset mechanism includes a set of cam elements supported for movement in response to rotation of the blades and positioned to engage a follower plate adjustably mounted on the beta feedback control rods.
摘要翻译：飞机螺旋桨具有可调桨距叶片，其通过β反馈和复位机构从低空转空转位置复位到较低桨距地面空闲位置。复位机构包括一组凸轮元件，其被支撑用于响应于叶片的旋转而移动并被定位成接合可调节地安装在β反馈控制棒上的随动板。

12. 发明授权

US4699568A Aircraft propeller with improved spinner assembly 失效
标题翻译：具有改进旋转器总成的飞机螺旋桨
公开(公告)号：US4699568A
公开(公告)日：1987-10-13
申请号：US844348
申请日：1986-03-26
申请人： W. Benjamin Harlamert , Donald C. Stackhouse
发明人： W. Benjamin Harlamert , Donald C. Stackhouse
IPC分类号： B64C11/14 , B64D15/12 , B64C11/44
CPC分类号： B64D15/12 , B64C11/14
摘要： A propeller hub supports a plurality of adjustable pitch propeller blades which are rotated on corresponding radial axes by a hydraulic actuating system supported by the hub. The hub and pitch changing system are enclosed by a spinner assembly including a substantially flat circular bulkhead member having a core molded between skins of resin impregnated high modulus fiber material. The bulkhead member supports a spinner dome of molded resin impregnated high modulus fiber material, and concentric slip rings are supported by a member connected to the rearward face of the bulkhead member. Terminal posts extend from the slip rings through the bulkhead member to receive conductor wires for supplying electrical current to de-icing heating elements mounted on the blades. A fairing is bonded to the spinner dome for each blade to provide for optimum aerodynamic flow around the base portion of each blade, and each fairing is formed by a molded resin skin material covering a rigid foam core.
摘要翻译：螺旋桨轮毂支撑多个可调桨距螺旋桨叶片，它们通过由轮毂支撑的液压致动系统在相应的径向轴线上旋转。轮毂和桨距变化系统由旋转器组件包围，该旋转器组件包括具有在树脂浸渍的高模量纤维材料的表面之间模制的芯的基本上平坦的圆形隔壁构件。隔板构件支撑模制树脂浸渍的高模量纤维材料的旋转圆顶，并且同心滑环由连接到隔板构件的后表面的构件支撑。端子柱从滑环延伸通过隔板构件以接收用于向安装在叶片上的除冰加热元件提供电流的导线。整流罩与每个叶片的旋转圆顶结合，以提供围绕每个叶片的基部的最佳空气动力学流动，并且每个整流罩由覆盖刚性泡沫芯的模制树脂表皮材料形成。

13. 发明授权

US3461966A Unitary fixed pitch aircraft propeller 失效
标题翻译：机组固定式飞机飞机螺旋桨
公开(公告)号：US3461966A
公开(公告)日：1969-08-19
申请号：US3461966D
申请日：1967-10-16
申请人： HARTZELL PROPELLER INC
发明人： BIERMANN DAVID
IPC分类号： B64C11/08 , B64C11/10 , B64C11/22
CPC分类号： B64C11/08

14. 发明授权

US3249159A Propeller control system 失效
公开(公告)号：US3249159A
公开(公告)日：1966-05-03
申请号：US42379465
申请日：1965-01-06
申请人： HARTZELL PROPELLER INC
发明人： DAVID BIERMANN
IPC分类号： B63H3/08 , B64C11/40
CPC分类号： B63H3/082 , B63H2003/088 , B64C11/40

15. 发明授权

US3156301A Variable pitch propeller 失效
公开(公告)号：US3156301A
公开(公告)日：1964-11-10
申请号：US24305762
申请日：1962-12-07
申请人： HARTZELL PROPELLER INC
发明人： DAVID BIERMANN
IPC分类号： B64C11/40
CPC分类号： B64C11/40

16. 发明授权

US3057410A Controllable pitch propeller 失效
公开(公告)号：US3057410A
公开(公告)日：1962-10-09
申请号：US73258858
申请日：1958-05-02
申请人： HARTZELL PROPELLER INC
发明人： DAVID BIERMANN
IPC分类号： B64C11/40
CPC分类号： B64C11/40

17. 发明授权

US4810167A Composite aircraft propeller blade 失效
标题翻译：复合飞机螺旋桨叶片
公开(公告)号：US4810167A
公开(公告)日：1989-03-07
申请号：US939426
申请日：1986-12-08
申请人： Mark W. Spoltman , Richard D. Bowerman , Richard L. Edinger
发明人： Mark W. Spoltman , Richard D. Bowerman , Richard L. Edinger
IPC分类号： B29D99/00 , B32B5/16 , B64C11/26 , F01D5/28
CPC分类号： B29D99/0025 , B32B5/16 , B64C11/26 , F01D5/282 , B29K2105/04 , B29K2105/0809 , B29K2105/108 , B29K2105/20 , B64D2027/026 , Y02T50/66 , Y02T50/672
摘要： A generally flat core of foam material extends outwardly from a wedge-shaped metal base plug, and the core is covered with overlapping plies of resin-bonded plastics materials having unidirectional fibers. The plies are covered by outer layers or skins of resin-bonded woven fabric plastics materials. The fibers of the inner plies are orientated at positive and negative acute angles relative to the longitudinal axis of the blade to provide the blade with predetermined torsional stiffness, and the fibers of the outer plies extend generally parallel to the axis and wrap around the base plug in an interleaving manner to provide high stiffness and strength to bending forces. Some of the plies extending around the base plug receive metal shell elements, and the shell elements engage propeller hub lip portions which cooperate to define an under-cut recess and clamp the plies to the base plug.
摘要翻译：大体上扁平的泡沫材料芯从楔形金属基塞向外延伸，并且核心被具有单向纤维的树脂粘合塑料材料的重叠层覆盖。帘布层由树脂粘合的织物塑料材料的外层或表皮覆盖。内层的纤维相对于叶片的纵向轴线以正的和负的锐角取向，以提供具有预定的扭转刚度的叶片，并且外层的纤维基本上平行于轴延伸并围绕基座以交错方式提供对刚度和强度的弯曲力。围绕基座延伸的一些帘布层接收金属外壳元件，并且壳体元件接合螺旋桨轮毂唇缘部分，其协作以限定下切割凹部并将帘布层夹紧到基座塞上。

18. 发明授权

US4302155A Air craft propeller assembly with composite blades 失效
标题翻译：航空航天螺旋桨组合与复合叶片
公开(公告)号：US4302155A
公开(公告)日：1981-11-24
申请号：US1961
申请日：1979-01-08
申请人： Richard V. Grimes , W. Benjamin Harlamert , David F. Thompson
发明人： Richard V. Grimes , W. Benjamin Harlamert , David F. Thompson
IPC分类号： B64C11/26 , B64C27/473 , B64C11/06
CPC分类号： B64C27/473 , B64C11/26 , B64C2027/4736
摘要： An adjustable pitch aircraft propeller has peripherally spaced composite blades each including an elongated core of expanded rigid foam material extending from a metal base member having a reduced neck portion and an outwardly projecting flange portion. A casing or skin of plastic resin impregnated fabric material surrounds the core of each blade and extends inwardly along the neck portion and also has a flange portion overlying the flange portion of the base member. The skin material overlying the neck portion of the base member is retained by a filament winding impregnated with plastic resin, and the blade is coupled to the propeller hub by an annular lip portion which projects inwardly and overlies the flange portion of the skin material. The foam core of each propeller blade has longitudinally extending slots, and strips of resin impregnated fabric material extend through the slots to form corresponding webs which connect the skin material forming opposite side of the propeller blade.
摘要翻译：可调桨距飞机螺旋桨具有外围间隔的复合叶片，每个复合叶片包括从具有减小的颈部和向外突出的凸缘部分的金属基底构件延伸的膨胀的刚性泡沫材料的细长芯。塑料树脂浸渍的织物材料的外壳或皮肤围绕每个叶片的芯部并且沿着颈部部分向内延伸，并且还具有覆盖在基底部件的凸缘部分上的凸缘部分。覆盖在基底部件的颈部上的表皮材料由浸渍有塑料树脂的细丝缠绕部分保持，并且叶片通过向内突出并覆盖在皮肤材料的凸缘部分上的环形唇形部分联接到螺旋桨毂上。每个螺旋桨叶片的泡沫芯具有纵向延伸的槽，并且树脂浸渍的织物材料条延伸穿过狭槽，以形成连接形成螺旋桨叶片相对侧的表皮材料的相应腹板。

19. 发明授权

US4097189A Aircraft propeller and blade pitch control system 失效
标题翻译：飞机螺旋桨和桨叶桨距控制系统
公开(公告)号：US4097189A
公开(公告)日：1978-06-27
申请号：US725008
申请日：1976-09-20
申请人： W. Benjamin Harlamert
发明人： W. Benjamin Harlamert
IPC分类号： B64C11/38
CPC分类号： B64C11/38
摘要： A propeller hub supports a plurality of angularly disposed propeller blades which are movable by a hydraulic cylinder between a high pitch position and a reverse position through a low pitch position. Hydraulic fluid is supplied to the cylinder from a governor unit driven by the aircraft engine, and a fluid pressure responsive relief valve controls the pressure of the hydraulic fluid. The pressure responsive relief valve is manually adjustable by the aircraft pilot to change the fluid pressure at which the valve responds in order to change the pitch of the propeller blades. The fluid pressure must be increased above a predetermined normal operating limit for actuating the cylinder against the bias of a spring within the propeller to move the blades to their reverse pitch position. In addition, a centrifugally actuated lock unit prevents actuation of the cylinder and movement of the blades to their reverse pitch position until the speed of the propeller is reduced to a slow idle. The pressure responsive relief valve also incorporated hydraulic means to assure that the valve responds immediately to the pilot's command.
摘要翻译：螺旋桨轮毂支撑多个角度布置的螺旋桨叶片，其可以通过液压缸在高俯仰位置和反向位置之间通过低俯仰位置移动。液压流体从由飞机发动机驱动的调速器单元供应到气缸，并且流体压力响应安全阀控制液压流体的压力。压力响应式安全阀可由飞机驾驶员手动调节，以改变阀响应的流体压力，以改变螺旋桨叶片的桨距。必须将流体压力增加到高于预定的正常操作极限，以便克服螺旋桨内的弹簧的偏压来致动气缸，以将叶片移动到其相反的俯仰位置。此外，离心致动的锁定单元防止气缸的致动和叶片的运动到其相反的桨距位置，直到螺旋桨的速度降低到缓慢的空转。压力响应安全阀还包括液压装置，以确保阀门立即响应飞行员的指令。

20. 发明授权

US3861828A Aircraft propeller and vibration damper assembly 失效
标题翻译：飞机螺旋桨和振动阻尼器总成
公开(公告)号：US3861828A
公开(公告)日：1975-01-21
申请号：US35659073
申请日：1973-05-02
申请人： HARTZELL PROPELLER INC
发明人： BIERMANN DAVID , GRIMES RICHARD V , HOWE GILBERT D , CRITCHLOW E FOREST
IPC分类号： B64C11/00 , B64C11/02
CPC分类号： B64C11/008 , Y10S416/50 , Y10T464/50
摘要： An annular weight member is positioned concentrically with an aircraft propeller and is supported by a plurality of circumferentially spaced fasteners which extend axially through corresponding resilient bushings confined within holes formed within the weight member. The fasteners are secured to a support member which is rigidly connected to the aircraft engine shaft, and a friction pad is compressed between the weight member and the support member by a set of compression springs mounted on the fasteners. In one embodiment, the support member consists of an annular plate rigidly secured to the propeller hub, and in another embodiment, the support member consists of the starter ring gear for the engine. A further embodiment shows the weight member supported by an outwardly projecting flange of the starter gear hub and also functioning as the starter ring gear for the engine.
摘要翻译：环形配重构件与飞行器螺旋桨同心地定位，并且被多个周向间隔开的紧固件支撑，该紧固件轴向地延伸通过限定在配重构件内形成的孔内的相应的弹性衬套。紧固件被固定到刚性地连接到飞行器发动机轴的支撑构件，并且摩擦垫通过安装在紧固件上的一组压缩弹簧在配重构件和支撑构件之间被压缩。在一个实施例中，支撑构件由刚性地固定到螺旋桨毂的环形板组成，并且在另一个实施例中，支撑构件由用于发动机的起动器齿圈组成。另一实施例示出了由起动器齿轮毂的向外突出的凸缘支撑并且还用作发动机的起动器齿圈的配重构件。

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