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15. minimize [ 'minimaiz ] vt. 把…減到最小
16. airflow [ 'flou ] n. 氣流
17. effect [ i'fekt ] n. 效應(yīng);作用;效果
18. baseplate [ 'beispleit ] n. 底板;基座
19. locator [ lou'keit ] n. 定位器
20. insure [ in'u ] v. 保證;為…提供保證
21. flange [ 'flænd ] n. 凸邊;法蘭盤;突緣
22. caution [ 'k :n ] n. 注意;警告
23. note [ nout ] n. 注意;提示;符號;注示
24. kept [ kept ] 是keep 的過去式及過去分詞(意為保持)
25. clean [ kli:n ] a. 清潔的
26. smooth [ smu:ð ] a. ; ad. 平滑的;光滑的
27. deform [ di'f :m ] v. 變形
28. plug [ plg ] v. 堵塞
29. interconnect [ 'intk'nekt ] v. ; n. 相互連接
30. average [ 'ævrid ] a. ; n. 平均的;平均值
31. turn [ t:n ] v. ; n. 轉(zhuǎn)彎
32. turbulence [ 't:bjulns ] n. 湍流;擾動;顛簸
33. standby airspeed indicator 備用空速指示器
34. over a range of … 在…范圍的
35. capsule [ 'kæpsju:l ] 盒子;封殼;容器
36. interior [ in'tiri ] a; n. 內(nèi)部的;內(nèi)部
37. diaphragm [ 'daifræm ] n. 膜盒
38. response to … [ ris'p ns ] 對…的響應(yīng)
39. substantially [ sb'stænli ] ad. 大體上
40. is linear with … [ 'lini ] 與…成線性關(guān)系
41. rocking [ 'r ki ] shaft 搖臂軸; 擺動軸
42. pinion [ 'pinjn ] n. 小齒輪; 傳動齒輪
43. protrude [ pr 'tru:d ] v. 伸出; 突出
44. dial [ 'dail ] n. 刻度盤;儀表盤
45. serve as 用作;充當(dāng);起…的作用
TEXT
[1] The pitot/static system provides dynamic (pitot) and ambient (static ) air
pressure to airplane systems. The interfacing systems and components convert
the pressure inputs into altitude and airspeed signals. The pitot/static system
consists of probes, static ports, valves, hoses, tubings , manifolds and various
fittings, including drain fittings. The air probes sense dynamic and ambient
pressures and supply the pressures through lines to using components.The probe
are heated to prevent ice accumulation. The alternate static ports provides
ambient pressure for the standby altimeter /airspeed indicator.
Fig. 30-1 pitot/static system
[2] Figure 30-2 illustrates the pitot/static system component locations. The
pitot/static probes are installed outside the airplane, two on each side, bellow
control cabin window No. 3 at station 247.6. The alternate static ports are
located at station 406, one at either side of the airplane. Window and pitot/static
heat module is installed on the P5 panel. The pneumatic altitude/airspeed
indicator is located on the captain's instrument panel (P1) .
Fig. 30-2 pitot/static system compenent locations
[3] The pitot/static probe has three ports: one directed forward for pitot pressure
sensing and two located around the outside of the pitot/static probe for static
pressure sensing. A strut projects the probe
several inches from the airplane skin to
minimize airflow turbulence effects. A
baseplate contains the electrical and
pressure fittings. Locator pins, in the
baseplate, insure proper installation
orientation. The probe design and port
location minimize errors caused by mach
number and alpha angle (angle of attack). An
anti-icing heater in the probe prevents ice
accumulation. The heater is connected to two
shielded pins in the baseplate. A gasket
provides cabin pressure seal. The gasket is
installed between the probe mounting flange
and the airplane structure.
Fig. 30-3 pitot/static probe
[4] The alternate static ports sense static (ambient) air pressures and provide the
static pressure input to the alternate static system. The static port is
flush-mounted on the fuselage skin. A circle is painted around the port with a
caution note. The area within the circle must be kept clean and smooth and the
port holes must not be deformed or plugged. The left and right alternate static
ports are interconnected to provide an average ambient pressure to the standby
altimeter /airspeed indicator.
[5] Figure 30-5 shows the interface
among components of the pitot/static
system and between the pitot/static
system and other airplane system. The
Fig. 30-4 alternate static port
main sensors of the pitot/static system
are four probes. The four probes are
identified as the captain's probe on the
upper left, the first officer's probe on the
upper right, the first auxiliary probe
(number 1 aux) on the lower right, and
the second auxiliary probe (number 2
aux ) on the lower left. Each of the
probes has one pitot pressure line and
　
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