机翼防冰控制活门SAS911
一、名称
Wing Anti-Ice Control Valve
机翼防冰控制活门
二、件号
HC1750~HC1758,SAS911-001A,-002A,SAS912-001A,-002A
三、章节号
30-11-51
四、适用机型
A320
五、系统
30 ICE AND RAIN PROTECTION
防冰防雨
六、安装位置
大翼RIB 8和RIB 9之间
wing leading-edge outboard of the engine pylons
发动机吊架的机翼前缘外侧
七、部件原理
The wing anti-ice control valve has these primary components:
– an actuator body assembly
– a butterfly valve
– a controller-housing assembly
– a damper assembly
– a solenoid valve assembly
– two pressure switches
– a valve position microswitch.
机翼防冰控制活门有以下主要部件：
-作动器壳体组件
-蝶板组件
-控制器外壳总成
-阻尼器总成
-电磁阀总成
-两个压力开关
-活门位置微动开关。
When bleed-air pressure is applied upstream of the butterfly valve, and the solenoid valve is energized, the actuator and damper chambers pressurize. This opens the butterfly valve and lets bleed-air pass through the anti-ice control valve. The anti-ice valve controls its outlet pressure to 1.55bar±0.17bar.
当在蝶板上游施加引气压力，且电磁阀通电时，作动器和阻尼腔加压。这将打开蝶板，并使引气通过防冰控制活门。防冰活门将其出口压力控制在1.55bar±0.17bar。
When the bleed-air pressure is more than this, the controller-housing sensor diaphragm opens the sensor valve. This releases the pressure in the actuator chamber to atmosphere and closes the butterfly valve.
当引气压力大于此压力时，控制器壳体传感器膜片打开传感器阀。这将作动器腔中的压力释放到大气中，并关闭蝶板。
When the outlet pressure falls below the controlled value the damper spring closes the sensor valve. The actuator chamber then pressurizes again and opens the butterfly valve. The constant movement of the butterfly valve keeps the valve outlet pressure at the specified value.
当出口压力降至控制值以下时，阻尼弹簧将关闭传感器阀。然后，作动器腔再次加压并打开蝶板。蝶板的不断移动使活门出口压力保持在规定值。
The two pressure switches monitor the pressure downstream of the butterfly valve to sense a valve malfunction.
两个压力开关监测蝶阀下游的压力，以检测活门故障。
If the pressure increases to 2.2 bar (31.9082 psi) the related switch gives a high pressure signal. If the pressure decreases to 0.9 bar (13.0533 psi) the related switch gives a low pressuresignal.
如果压力增加到2.2 bar（31.9082 psi），相关开关会发出高压信号。如果压力降至0.9 bar (13.0533 psi)，相关开关会发出低压信号。
The valve can be manually locked in the open or closed position by the lock pin. The pin is removed from the valve body and used to safety the valve indicator lever. When the lock pin is removed from its storage position, the actuator chamber is open to atmosphere, to prevent pneumatic operation of the valve.
活门可以通过锁销手动锁定在打开或关闭位置。锁销从活门壳体上拆下，用于安全锁定指示杆。当锁销从其储存位置移除时，作动器腔打开，其他流向大气，以防止活门的气动操作。
The anti-ice valve has upstream and downstream ground-test connections. These let a functional test of the valve be done without bleed-air pressure in the ducts.
防冰活门具有上游和下游地面测试连接。这样就可以在管道中没有引气压力的情况下对活门门进行功能测试。
八、工作参数
Operating upstream air pressure (max): 413 kPag (60 psig)
Operating output pressure (max) : 172 kPag (25 psig)
Operating temperature (max): 260 deg C (500 deg F)
Operating voltage :28 V dc Nominal
九、在飞机系统中的工作原理及互联
Two wing anti-ice control-valves are installed on the aircraft, one in each wing leading-edge outboard of the engine pylons. A single ON/OFF switch on the cockpit overhead panel (25VU) operates the two valves.
The wing anti-ice control-valve:
– isolates the anti-ice ducts from the pneumatic system bleed-air supply when anti-icing is not required
– controls the pressure of the wing anti-ice bleed-air, supplied by the pneumatic system.
The valves are selected electrically and actuated pneumatically. If an electrical failure occurs, the valves will automatically go back to the closed position. The valves can be locked in the closed position to let the aircraft operate in non-icing conditions.
NOTE : The RH anti-ice control valve can be locked in the OPEN position, but the correct ECAM procedure must be applied (REF. 30-11-00-04).
When the valve(s) is/are locked in the CLOSED position, the aircraft is not permitted to fly into icing conditions. A microswitch in the anti-ice valve senses when the valve is closed and gives a CLOSED/NOT CLOSED signal to the Environmental Control System Zone Control and Bleed Status
Computer (ECS computer) and the Electronic Centralized Aircraft Monitoring (ECAM) system.A visual/mechanical valve position indication is also given.
飞机上安装有二个机翼防冰控制活门, 每个发动机吊架机翼前缘外侧一个。通过在驾驶舱顶板(25VU)上的一个ON/OFF(接通/断开)电门来操作二个活门。
机翼防冰控制活门:
-当不需要防冰时, 隔绝防冰导管和气源系统引气
-控制机翼防冰引气压力, 通过气压系统压力。
活门电气选择并气动操作。如发生电气故障, 活门将自动回到CLOSED位置。活门可锁在接通位置让飞机操作在非结冰状况。
注: 右防冰控制活门可能锁在OPEN位置, 但必须施加修正ECAM程序(参见 30-11-00-04)。
当活门锁定在关闭位置时, 不允许飞机在结冰气候条件下飞行。当活门关闭并给出一个CLOSED/NOT关闭信号到环境控制系统区控制器和引气状态计算机(ECS计算机)和飞机电子中央监控(ECAM)系统, 一个微电门在防冰活门感应。也提供一个可视/机械活门位置指示。
The wing ice protection system is supplied with hot air from the pneumatic system, downstream of the pre-cooler. The anti-ice control valve (in the wing, outboard of the engine pylon) isolates these two systems. A restrictor downstream of the anti-ice control valve controls the air flow.The hot air goes through a lagged duct that connects the anti-ice control valve to the telescopic duct, inboard of RIB 13. The telescopic duct only attaches to the piccolo ducts in the slat 3. The piccolo ducts 3, 4 and 5 (that connect together with flexible ducts) release the hot air to heat the slats. The piccolo ducts release the air into the slats through holes along their foward length. The air flows around the forward area of the slat then goes through acceleration slots into the rear section. It is then released overboard through the holes in the bottom surface of the slat.
机翼防冰系统从预冷却器顺流的气压系统提供热空气。防冰控制活门(在发动机吊架外侧的大翼内部)隔离了这两个系统。一个防冰控制活门限制器顺流控制气流。热空气流过一个装有隔热套的管道,该管道将防冰控制活门和RIB 13处的内侧伸缩管连接起来。伸缩管道仅连接到3号缝翼小型导管。小型导管 3,4和 5(连接连同挠性导管)释放热空气以加热缝翼。小型导管释放空气经过孔沿着它的前段进入缝翼。空气围绕缝翼前方的区域流动然后通过加速度槽进入后部。然后空气从缝翼底部表面的孔排出机外。
十、系统介绍/拓展知识
The wing ice protection system：
The wing ice protection system prevents ice on the leading edge of the slats 3, 4 and 5. The system, which is the same in the LH and the RH wing, uses hot air from the pneumatic system (Ref. 36-00-00). It is available in all flight conditions. The two engines usually supply the pneumatic system with bleed air. If there is a failure, the cross-bleed valve opens and one engine can supply the two wings.The system is only used during flight, but can be tested on the ground. To prevent heat damage to the slats, the ground test stops automatically after 30 seconds.
大翼防冰系统：
大翼防冰系统用来防止在3,4和 5号缝翼前缘出现结冰。该系统(在左侧和右侧大翼是相同的)使用来自气源系统(Ref. 36-00-00)的热空气。在所有飞行条件下它都是可用的。这两个发动机通常用引气供给气源系统。如果出现故障,交输引气活门打开并可由一台发动机给二个大翼供气。系统只在飞行过程中使用,但可在地面上进行测试。以防止缝翼受到过热损伤,地面测试在30秒后自动停止。
