摘要：【中文】本发明属于飞机部装装配技术领域，涉及一种AGV转运部件的精准定位方法及装置，所述的精准定位方法先通过导向装置对AGV设备的转运部件进行预定位，后利用零点定位器对AGV设备的转运部件进行精确定位的方法；所述精准定位装置包含：AGV设备、零点定位器组、定位支座、模块化定位工装、安装平台、定位磁条以及将安装平台与模块化定位工装连接定位的导向装置；并通过零点定位器组将安装平台与模块化定位工装连接定位；本发明设计方法稳定可行，有效解决了AGV作为物流转运设备定位精度低带来的问题，且能解决一次精确定位导致的零点定位器磕碰损坏的问题，大幅提升AGV设备的利用效率，为实现飞机装配生产线实现自动化物流运转提供技术保障。 【EN】The invention belongs to the technical field of aircraft assembly and relates to an accurate positioning method and device for an AGV transferring part, wherein the accurate positioning method comprises the steps of pre-positioning the transferring part of AGV equipment through a guide device, and then accurately positioning the transferring part of the AGV equipment by using a zero positioner; the accurate positioning device includes: the system comprises AGV equipment, a zero point positioner group, a positioning support, a modular positioning tool, an installation platform, a positioning magnetic stripe and a guiding device for connecting and positioning the installation platform and the modular positioning tool; connecting and positioning the mounting platform and the modular positioning tool through a zero positioner group; the design method is stable and feasible, effectively solves the problem caused by low positioning precision of the AGV as the logistics transfer equipment, can solve the problem of collision and damage of the zero point positioner caused by one-time accurate positioning, greatly improves the utilization efficiency of the AGV equipment, and provides technical support for realizing automatic logistics operation of an aircraft assembly production line.

摘要：【中文】本发明属于飞机氧气系统设计技术领域，涉及一种电控式集中氧气系统，包含：充氧面板(1)、泄压阀(2)、氧气瓶组件(3)、氧气控制箱(4)；所述充氧面板(1)与氧气瓶组件(3)通过充氧管路连接，用于与地面充氧设备对接，为飞机氧气系统充氧；所述泄压阀(2)与氧气瓶组件(3)通过泄压管路连接；所述氧气瓶组件(3)通过输氧管路上连接的氧气控制箱(4)为机组和乘客输送氧气；解决了现有氧气瓶组件在机下不能充氧问题，解决了传统氧气系统压力表使用的毛细管加工困难，易变形、折断、堵塞的问题，并解决了夜间飞行时氧气控制箱上标识看不清问题。本发明在满足机上乘员用氧需求的同时，也提高了飞机设计品质。 【EN】The invention belongs to the technical field of airplane oxygen system design, and relates to an electric control type centralized oxygen system, which comprises: the oxygen charging device comprises an oxygen charging panel (1), a pressure release valve (2), an oxygen cylinder assembly (3) and an oxygen control box (4); the oxygenation panel (1) is connected with the oxygen bottle assembly (3) through an oxygenation pipeline and is used for being butted with ground oxygenation equipment to oxygenate an airplane oxygen system; the pressure release valve (2) is connected with the oxygen cylinder assembly (3) through a pressure release pipeline; the oxygen cylinder assembly (3) is used for conveying oxygen to the unit and passengers through an oxygen control box (4) connected to the oxygen conveying pipeline; the problem of current oxygen cylinder subassembly can not oxygenate under quick-witted is solved, the capillary processing difficulty that traditional oxygen system manometer used has been solved, yielding, rupture, the problem of jam to sign is seen unclear on the oxygen control box when having solved the flight night. The invention can meet the oxygen demand of the passengers on the airplane and simultaneously improve the design quality of the airplane.

摘要：【中文】本发明实施例公开了一种自动驾驶仪的舵机安装装置，包括：舵机、舵机支架、两个导向滑轮、两套钢索组件和被驱动装置；舵机安装在舵机支架的上部，两个导向滑轮安装在舵机支架的下部；舵机上配置有圆盘形鼓轮，钢索组件的缠绕在所述鼓轮上，且钢索组件中由鼓轮输出的钢索部分通过相应位置的导向滑轮连接到被驱动装置一侧的固定端；导向滑轮，用于承接由鼓轮输出的钢索部分，并通过导向滑轮的导向调整输出钢索部分的输出方向。本发明实施例解决了现有自动驾驶仪中的舵机安装结构，占用空间大，且不利于后续维护的问题。 【EN】The embodiment of the invention discloses a steering engine mounting device of an autopilot, which comprises: the steering engine, the steering engine bracket, the two guide pulleys, the two sets of steel cable assemblies and the driven device; the steering engine is arranged on the upper part of the steering engine bracket, and the two guide pulleys are arranged on the lower part of the steering engine bracket; a disc-shaped drum wheel is arranged on the steering engine, a steel cable component is wound on the drum wheel, and the steel cable part output by the drum wheel in the steel cable component is connected to the fixed end of one side of the driven device through a guide pulley at the corresponding position; and a guide pulley for receiving the wire portion outputted from the drum and adjusting the output direction of the outputted wire portion by the guide of the guide pulley. The embodiment of the invention solves the problems that the steering engine mounting structure in the existing autopilot occupies large space and is not beneficial to subsequent maintenance.

摘要：【中文】本发明属于直升机系统检测领域，具体涉及一种用于直升机电气系统的自动检测试验平台。目前为检测电气系统各项功能是否能正常工作，主要依靠测试仪表或简单的测试工装配合仪表来完成通电检测，测试设备无法通用、集成度低，不便于存放和搬运，效率极低。本发明提供了一种用于直升机电气系统的自动通电检测试验平台，包括相互连接的测试模块和信号适配模块。在PXI机箱内安装有PXI控制器和多种发送测试信号的资源板卡以及多种采集反馈信号的资源板卡，PXI控制器控制资源板卡通过信号适配模块向被测系统发送所需测试信号，并在通电的情况下进行持续的自动检测。能够满足全机电气各系统的通电检测、极大提高测试效率、降低人工劳动强度。 【EN】The invention belongs to the field of helicopter system detection, and particularly relates to an automatic detection test platform for a helicopter electrical system. At present, whether each function of an electric system can work normally or not is detected, the power-on detection is mainly completed by a test instrument or a simple test tool matched instrument, the test equipment cannot be universal, the integration level is low, the storage and the carrying are inconvenient, and the efficiency is extremely low. The invention provides an automatic power-on detection test platform for an electric system of a helicopter. A PXI controller, a plurality of resource board cards for sending test signals and a plurality of resource board cards for collecting feedback signals are installed in a PXI case, the PXI controller controls the resource board cards to send required test signals to a tested system through a signal adapting module, and continuous automatic detection is carried out under the condition of power-on. The power-on detection of all electrical systems of the whole machine can be met, the testing efficiency is greatly improved, and the labor intensity of workers is reduced.

摘要：【中文】本发明属于舱门锁机构设计技术，涉及一种用于直升机的舱门碰锁机构。本发明直升机舱门碰锁机构包括外把手组件(1)、内把手组件(2)、拉杆组件(3)、锁盒组件(4)、锁座组件(5)。所述锁座组件(5)安装在门框上，锁盒组件(4)安装在舱门结构上，二者相互配合，控制舱门开闭，所述外把手组件(1)、内把手组件(2)通过拉杆组件(3)连接锁盒组件(4)，通过拉杆组件(3)控制锁盒组件(4)与锁座组件(5)之间的配合关系，实现舱门开闭。本发明的直升机舱门碰锁机构，传力路径直接，可大幅降低舱门开启操纵力；集成锁盒，可靠性高，重量轻，故障率低，安装及维护便捷，可快速实现在各类直升机舱门上的改装需求。 【EN】The invention belongs to the design technology of a cabin door lock mechanism, and relates to a cabin door latch mechanism for a helicopter. The invention discloses a helicopter cabin door latch mechanism which comprises an outer handle assembly (1), an inner handle assembly (2), a pull rod assembly (3), a lock box assembly (4) and a lock seat assembly (5). The door is characterized in that the lock seat assembly (5) is installed on a door frame, the lock box assembly (4) is installed on a door structure, the lock seat assembly and the door structure are matched with each other to control the opening and closing of the door, the outer handle assembly (1) and the inner handle assembly (2) are connected with the lock box assembly (4) through the pull rod assembly (3), and the lock box assembly (4) and the lock seat assembly (5) are controlled to be matched with each other through the pull rod assembly (3) to realize the opening and closing of the door. The helicopter cabin door latch mechanism has a direct force transmission path, and can greatly reduce the opening operating force of the cabin door; the integrated lock box has the advantages of high reliability, light weight, low failure rate, convenience in installation and maintenance and capability of quickly meeting the refitting requirements on various helicopter cabin doors.

摘要：【中文】本发明涉及一种多功能直升机尾桨试验系统，包括：试验台体、三相异步电机、电机转速控制系统、桨距控制系统、变速箱、涵道尾桨传动轴、涵道尾桨、常规结构尾桨传动轴、常规结构尾桨、测力杆系、测力天平、第一扭矩传感器、第二扭矩传感器、声级计、风速风温测量仪和数据采集系统。本发明可满足常规结构尾桨和涵道尾桨等多种结构形式尾桨的试验要求，可进行性能试验、动力学试验、噪声研究、地面载荷测量等多种试验项目，完全模拟真机进行试验，边界条件与尾桨工况一致性高。 【EN】The invention relates to a multifunctional helicopter tail rotor test system, which comprises: the test bench comprises a test bench body, a three-phase asynchronous motor, a motor rotating speed control system, a propeller pitch control system, a gearbox, a ducted tail rotor transmission shaft, a ducted tail rotor, a conventional structure tail rotor transmission shaft, a conventional structure tail rotor, a force measuring rod system, a force measuring balance, a first torque sensor, a second torque sensor, a sound level meter, a wind speed and wind temperature measuring instrument and a data acquisition system. The invention can meet the test requirements of tail rotors with various structural forms such as tail rotors with conventional structures, duct tail rotors and the like, can carry out various test items such as performance tests, dynamic tests, noise researches, ground load measurement and the like, completely simulates a real machine to carry out tests, and has high consistency of boundary conditions and tail rotor working conditions.