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1. 发明申请

WO1992003337A1 FUEL LINE INSTALLATION IN HELICOPTERS 审中-公开
标题翻译：直升机燃油管线安装
公开(公告)号：WO1992003337A1
公开(公告)日：1992-03-05
申请号：PCT/CH1991000153
申请日：1991-07-23
申请人： LITECO AG , PODGURSKI, Daniel, M.
发明人： LITECO AG
IPC分类号： B64C27/18
CPC分类号： F16L27/087 , B64C27/18
摘要： The fuel line installation in helicopters whose main rotor blades are driven by jet engines fitted at their tips has a swash plate (1) with an adjustable stationary bearing flange (11) and a swash plate ring (2) fitted to rotate thereon and driven by the main rotor blades. The bearing flange (11) has at least one aperture (13, 14) for the fuel opening into at least one passage (35, 36) in the swash plate ring (2). In helicopters whose jet engines are powered by two-components fuels, this circumvents the difficulty of feeding these components to the engines separately.
摘要翻译：直升机中的燃油管路安装在其主要转子叶片由安装在其顶端的喷气发动机驱动的旋转斜盘（1）上，具有可调节的固定轴承凸缘（11）和斜盘环（2），该旋转斜盘安装在其上旋转并由主转子叶片。轴承法兰（11）具有至少一个孔（13,14），用于燃料开口进入斜盘环（2）中的至少一个通道（35,36）。在直升机中，其喷气发动机由双组分燃料提供动力，这避免了将这些部件分别供给发动机的困难。

2. 发明申请

WO1992010661A1 THRUST NOZZLE FOR A ROTATING BODY 审中-公开
标题翻译：旋转喷嘴用于旋转体
公开(公告)号：WO1992010661A1
公开(公告)日：1992-06-25
申请号：PCT/CH1991000254
申请日：1991-12-10
申请人： LITECO AG , WEISS, Hardy, P. , HANNOSCHOECK, Niklaus
发明人： LITECO AG
IPC分类号： F02K07/00
CPC分类号： F02K9/68 , F02K7/005
摘要： In a thrust nozzle for a rotating body, especially a helicopter rotor tip drive system, liquid fuel can be supplied through a radial line. In the thrust nozzle, this fuel undergoes a substantially right-angled deflection in the tangential direction. There are guides for distributing the liquid fuel in the thrust nozzle. The guides comprise a pin (13) arranged axially in the thrust nozzle having at least one helical circumferential groove (12) forming a flow channel for the liquid fuel. The pin (13) is inserted in an inner housing (8) in the thrust nozzle. In this design, the fuel is no longer thrown against the outer internal wall of the propulsion unit by the field of force of the centrifugal forces but is fed uniformly into the decomposition chamber.

3. 发明申请

WO1992014647A1 CONTROL SYSTEM OF THE ROTOR SPEED OF ROTATION FOR HELICOPTER DRIVE ASSEMBLIES 审中-公开
标题翻译：旋转驱动装置的转子转速控制系统
公开(公告)号：WO1992014647A1
公开(公告)日：1992-09-03
申请号：PCT/CH1992000029
申请日：1992-02-13
申请人： LITECO AG , THOMAS, Michel
发明人： LITECO AG
IPC分类号： B64C27/18
CPC分类号： B64C27/18
摘要： A control system of the rotor speed of rotation for helicopter drive assemblies, useful in particular for tip drives, is disclosed. In order to relieve the pilot and ensure optimal regulation of the rotor speed of rotation, the control elements (8, 29; 78, 114), that are subjected to the centrifugal force, control the fuel supply to the drive assemblies.

4. 发明申请

WO1992012897A1 CONTROL SYSTEM FOR ROTARY-WING AIRCRAFT 审中-公开
标题翻译：旋转飞机控制系统
公开(公告)号：WO1992012897A1
公开(公告)日：1992-08-06
申请号：PCT/CH1991000273
申请日：1991-12-18
申请人： LITECO AG , ROCK, Gene
发明人： LITECO AG
IPC分类号： B64C27/59
CPC分类号： B64C27/59
摘要： The control system for rotary-wing aircraft (1) has a rod connection between the main rotor blades (14, 15) and a swash plate (63) which is operationally connected to a pilot's control handle (28) on the one hand and on the other is connected to the main rotor blades (14, 15) via levers (62, 66) with their axes of rotation lying substantially in one plane. When the pilot's control handle (28) is pushed forward, the swash plate (63) is inclined forwards and downwards with no lost motion so that the forward main rotor blade (14 or 15) assumes its smallest angle of attack. This control system has no lost motion. The pilot therefore experiences it as a rigid system of rods when performing control movements. The system thus responds rapidly and accurately.
摘要翻译：旋转翼飞机（1）的控制系统在主转子叶片（14,15）和斜盘（63）之间具有杆连接，斜盘（63）一方面操作地连接到飞行员的控制手柄（28）另一个通过杠杆（62,66）连接到主转子叶片（14,15），其旋转轴基本上位于一个平面中。当飞行员的控制手柄（28）被向前推时，斜盘（63）向前和向下倾斜，没有运动，使得前主转子叶片（14或15）呈现最小的迎角。该控制系统没有运动。因此，飞行员在进行控制动作时，将其作为一个刚性的杆系统来实现。因此系统响应迅速而准确。

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