• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Apparatus for indicating rate of ice accretion particularly for use in an aircraft, the apparatus including test surface on which ice forms in use. First and second gas conduits are supplied with gas from a common pressure regulator the inlet of which communicates with a gas supply. A control port of the regulator is supplied with a reference pressure signal and the regulator operates to maintain its outlet pressure at a predetermined amount in excess of the reference pressure. Each of the first and second conduits includes a restrictor and each conduit terminates at its end remote from the regulator in an orifice. The first orifice is adjacent the test surface and a pressure difference sensor is associated with the first and second conduits to produce a signal dependent on the pressure difference at points between the orifice and restrictor of the two conduits. The pressure difference signal is applied to an indicator. A control conduit at a point which is intermediate the orifice and the restrictor of the second conduit so that the reference pressure for the regulator is derived from the second conduit between the restrictor and the orifice thereof. The test surface is moved relative to the first orifice at a predetermined speed and thus the first orifice will be restricted to an amount dependent upon the thickness of ice forming on the test surface. The difference in pressure sensed by the sensor is directly related to the thickness of the ice layer on the test surface, and since the test surface is moving at a predetermined speed then the indicator indicates the rate of ice accretion on the test surface.
    公开号:SU747407A3
    申请号:SU762366752
    申请日:1976-06-04
    公开日:1980-07-23
    发明作者:Эдгингтон Джоффри
    申请人:Лукас Индастриз Лимитед (Фирма)；
    IPC主号:
    专利说明:

    wires 6 and 13 are interconnected in front of the nozzles by a pressure sensor 15 (sensing element). The control hole 11 is connected to the second pipe between the throttle 12 and the nozzle 14 by the channel 16. The pressure sensor 15 is connected by an electrical connection 17 with an indicator 18. The surface of the cylinder 1 is in contact with the scraper blade 19.
    The device works as follows.
    Clean, dry, passed through the filter, pressurized air is supplied to the regulator 9. The pressure supplied to the inlet 10 of the regulator exceeds the maximum pressure required at its outlet 8, and the regulator acts to ensure that the pressure on outlet 8 will continuously exceed the pressure; in the pipe 13 between the nozzle 14 and choke restrictor 12, regardless of the pressure in the pipe 13.
    When there is no ice on the test surface, the gap between the nozzle 15 and the test surface on cylinder 1 is such that nozzle 5 is not blocked. When the nozzles 5 and 14 form equal pressure drops, provided that the setting of the restrictor chokes 7, 12 is equal, the pressure in the pipe 6 is equal to the pressure in the pipe 13 and the indicator shows zero.
    The other extreme state is when the thickness of the ice layer on the test surface of the cylinder 1 completely closes the gap and reduces POT9K in the pipe b to zero. In this state, there is no pressure drop across choke restrictor 7. Thus, sensor 15 experiences a complete pressure drop through limiter 12, which is kept constant, regardless of the ambient pressure, regulator 9, and the sensor generates a signal corresponding to the full deviation of the scale on the indicator 18.
    The indicator is graded by the intensity of icing on the test surface of cylinder 1. The rising ice is removed with a scrambling paddle 19.
    权利要求:
    Claims (2)
    [1]
    Synthesis Formula
    1 A device for indicating the intensity of icing containing a measured surface, a gas pressure regulator having a test opening for supplying a reference pressure, the output of which is connected to the first and second gas pipelines with limiters installed in them, the first and three times the nozzles located at the ends of the first and second gas pipelines, respectively, sensational element, perceiving the pressure drop in gas pipelines, and the indicator, about the l and cha that due to the increase of accuracy of indications, it has a counter a solder gas pipeline connecting the control opening of the gas pressure regulator with the second gas pipeline between the second nozzle and the stopper and the means for moving the measured surface with a predetermined velocity relative to the first nozzle.
    [2]
    2. A device according to claim 1, characterized in that the dimensional surface is a cylinder mounted rotatably adjacent to the first nozzle.
    Sources of information taken into account in the examination
    1. Trunov O.K. Aircraft icing and means of dealing with it. Mechanical Engineering, 1965, from 185-186, FIG. 3.72.
    2. Great Britain. Patent
    No. 820591, cl. 4, 1965 (prototype).
    w
    类似技术:
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    同族专利:
    公开号 | 公开日
    GB1541422A|1979-02-28|
    US4095456A|1978-06-20|
    FR2313264B1|1979-05-04|
    FR2313264A1|1976-12-31|
    JPS51147900A|1976-12-18|
    DE2624939A1|1976-12-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    CN112407297A|2020-11-19|2021-02-26|四川探索者航空科技有限公司|Aircraft icing detection method, system and device|US2171450A|1937-07-22|1939-08-29|Tecalemit Ltd|Means for detecting ice forming conditions, particularly when encountered by aircraft|
    FR873246A|1941-02-10|1942-07-02|Centre Nat Rech Scient|Icing speed indicator|
    US2427778A|1942-10-30|1947-09-23|Bendix Aviat Corp|Ice detecting mechanism|
    FR940659A|1946-11-14|1948-12-20|Onera |Wire mesh icing detector|
    US2585604A|1950-08-17|1952-02-12|Us Air Force|Rotating disk icing rate meter|
    US2953917A|1956-07-10|1960-09-27|Moore Products Co|Pneumatic dimension gages|
    US3252470A|1962-02-19|1966-05-24|Scott Aviation Corp|Altitude-compensating, constant-flow, oxygen regulator|
    US3220244A|1963-09-06|1965-11-30|Cooper Bessemer Corp|Thrust bearing wear sensing device|
    GB1094833A|1965-09-24|1967-12-13|Burchell James Gladwyn|Improvements in or relating to gauges|
    US3385076A|1965-10-23|1968-05-28|Robertshaw Controls Co|Defrost system and parts therefor or the like|
    US3754433A|1971-09-17|1973-08-28|Bendix Corp|Fluidic proximity sensor|
    AU8358975A|1974-08-05|1977-02-03|Commw Of Australia|Accretion|GB1562488A|1975-11-19|1980-03-12|Lucas Industries Ltd|Apparatus for indicating rate of ice eccretion|
    US4470123A|1982-01-05|1984-09-04|Miami R & D Limited Partnership|Microwave ice accretion meter|
    US4688185A|1982-01-05|1987-08-18|University Research Foundation|Microwave ice accretion measuring instrument|
    US4745804A|1986-12-08|1988-05-24|Dataproducts New England, Inc.|Accretion type ice detector|
    DE19609278C2|1996-03-02|2003-01-30|Stiftung A Wegener Inst Polar|Measuring method for long-term determination of the change in thickness of an ice floe and device for carrying it out|
    US6010095A|1997-08-20|2000-01-04|New Avionics Corporation|Icing detector for aircraft|
    EP2066565B1|2006-09-25|2010-11-24|Rosemount Aerospace Inc.|Detecting ice particles|
    US7439877B1|2007-05-18|2008-10-21|Philip Onni Jarvinen|Total impedance and complex dielectric property ice detection system|
    US8779945B2|2010-03-17|2014-07-15|Sikorsky Aircraft Corporation|Virtual ice accretion meter display|
    CN104648676B|2013-11-22|2017-02-22|中国航空工业集团公司西安飞机设计研究所|Icing signal sensor|
    US11021259B1|2021-01-07|2021-06-01|Philip Onni Jarvinen|Aircraft exhaust mitigation system and process|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    GB2406875A|GB1541422A|1975-06-04|1975-06-04|Apparatus for indicating rate of ice accretion|
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