• 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:
    The problem to be solved is to provide rapid, efficient and safe de-icing and cleaning of primarily aircrafts. The problem is solved by a de-icing and cleaning system comprising one or more devices for spraying the object in question, preferably aircrafts, with a liquid or gas or irradiating the object, and means for sensing the position of the object in relation to said devices, which means are disposed to control said devices to automatically start and stop the spraying and irradiation in response to the position of the aircraft in relation to the devices.
    公开号:SU1297718A3
    申请号:SU843699109
    申请日:1984-01-27
    公开日:1987-03-15
    发明作者:Магнуссон Улла；Магнуссон Кьелл-Эрик
    申请人:Magnusson Ulla；Kell Erik Magnusson；
    IPC主号:
    专利说明:

    This invention relates to anti-icing anti-icing control systems.
    The purpose of the invention is to provide faster, more efficient and safe ice removal at a more reasonable cost and without risk to the operating personnel.
    FIG. 1 shows an anti-icing and cleaning device control system for an airplane, front view; figure 2 - diagram of the program block of the system; in fig.Z-- block diagram of a part of the program block of the system; 4 shows the principle of a wind compensator.
    The control system of the anti-icing and cleaning device of the aircraft is made as follows.
    The plane, from which the ice must be removed, passes through one or several stationary portals 1 (figure 1). On each portal there is a pipeline, equipped with a set of nozzles 3, facing towards the aircraft 4.
    Portals 1 are located above road 5, which is equipped with a drainage pipe system 6 and 7 for each portal. A liquid is collected in the drainage pipes that does not fall on the aircraft when it is sprayed on or drains from it. Processing liquor is diverted to a collection tank 8, and then to a 9 dp purification unit and, possibly, heating or distillation before being pumped to the storage tank 10. From this tank, the liquid is re-supplied by pump 11 to line 2 to operate the next aircraft.
    Along the road, there are a number of position sensors AP of the aircraft (Fig. 2). They are intended to record the path traveled by the aircraft on the road, and to give a signal to open those actuating valves to which the plane reached the ground, and to close those actuating valves that the airplane has already passed. The position sensors can serve as pressure-sensitive elements mounted on the road; photocells triggered when the plane crosses a beam of light passing across the road, or metal detectors mounted on the road and, for example, containing ka: tu1tsku,
    five
    0
    five
    0
    five
    0
    which is supplied by persm1, mi thats .. well. what frequency. You can also use the number located on the continuation of the road in front or behind, Each, as the ifo.To- phone. The range finder controls the current supplied to the relays, which open and close the execution valves 12-30 of the nozzles 6 to the pipeline. When the nose part of the aircraft 4 enters the portal, the first position sensor is triggered, which transmits current to the relay, opening the actuating valves directed to the nose of the aircraft, causing the treatment fluid to spray on this part of the aircraft. As the aircraft passes under the portal, the position sensors alternately trigger, and the flow of liquid through the nozzles begins and stops as the aircraft surfaces pass by the nozzles.
    Which actuator valves should be open or closed when the corresponding sensor is triggered
    Positions are determined, for example, by a program block (FIG. 2),
     made in the form of a printed circuit board, which is designed for this type of aircraft) to be processed, the printed circuit boards are made to be replaced, therefore it is possible to handle airplanes of various types,
    FIG. 3, showing a portion of the block diagram of the program block, shows how the position sensors g, h and i actuate the actuation valves 12,13,14 and 15 through the relay g 12,
    9 h and i
    13, g 14, U, h 15, 15.
    g 15, h 12, h 13,
    i 12
    i 13
    k
    From the front wheel of the aircraft, the position sensor h is triggered, as a result of which the control circuit closes and the drive current passes from the current source 31 through the relay h 15, h 14 and h 13, the thin line indicates the drive current path current. Then the relays H13, L14 and H15 pass the operating current. From the source 32 of the working current to the actuating valves 13, .14 and 15, which open, as a result of which the treatment liquid is sprayed through the nozzles,
    The next moment the plane leaves the position sensor h, as a result of which the control circuit 1 is shown.
    312
    relays h 13, h 14 and h 15 de-energize and the supply of operating current to the actuating valves 13, 14 and 15 is stopped. As a result, liquid spraying through the appropriate nozzles is completed. When the aircraft leaves the position sensor h, it triggers the position sensor 1, which, in accordance with the block diagram, opens valves 2 and 13 via relays i 12 and i 13.
    The drive current conductors are printed on the printed circuit board and connected to position position i, h, g, current source 31 and relay I 12 -i 15, h 15, g 15 with the help of contact pads for this type of aircraft or aircraft. to be processed.
    . The wind compensator contains a wind direction indicator 33, a wind power indicator 34 (anemometer) and a selection unit corresponding to the determined parameters of the wind of printed circuit boards of the program block 35. On the left in FIG. 4 two printing plates are shown from a total number ( 13) printed circuit boards required in this example, and a board with relays h 12, h 13, h 14, h 15, g 13, g 14 id 15. On the left there are position sensors g, h and i, below shows actuating valves 12 13 , 14 and 15.
    The wind direction indicator 33 comprises a rotary contact lever 36 and a blade or the like, which rotates the contact lever by a convenient number of contact plates 37,38,39 and 40, one for each wind direction. Figure 4. Pokazano application of the four wind directions N, E, S, W, but you can take into account more or fewer directions. Through the contact lever, the drive current (thin dashed lines) is fed to one of the four contact pdastin, and from there to the selection unit of the printed circuit boards of the program block 35 corresponding to certain wind parameters,
    The anemometer contains a movable contact lever 41, a centrifugal regulator) or other device that shifts the contact lever from one extreme position corresponding to the absence of wind, to another extreme position corresponding to the maximum wind force, and a convenient number of intermediate contact plates, one for each interval of wind power. In the shown version, four wind strength intervals are applied: O for no wind, PG for maximum wind strength with intermediate positions I and 11, but more or less intervals can be used. Through the i-contact lever 41, the drive current (thin, solid lines) is supplied to one of the contact plates, and from there to the selection unit of the printed circuit boards of the software block 35 corresponding to certain wind parameters, in which the two control currents from the wind direction indicator 33 and the anemometer 34 are combined in a number of connection points. If it is necessary to combine all wind directions with all wind forces, 4-4 16 connection points will be required, but since the wind direction does not matter when the wind strength is 0, then only 13 connection points are required in this example:
    W PG, Snij F. Ill, Nin, W ir, S ir, E ir Nil
    w I, SI, El, N1 and 0..
    Two serially connected relays 42 and 43 are provided at each connection point. The control current from the wind direction indicator 33 only triggers the relay 42,: and from the anemometer 34 only the relay 43, so that the operating current (bold dashed lines) from the source 44 operating current could pass through the connection point in question, it is necessary that both relays be closed. In Figure 4, point II is shown in the position when the control current from the wind direction indicator sector N closes one relay 42, and the second relay 43 doesn't miss p The operating current, since the anemometer is not in position II, but in position O,
    f
    Each Connection or Contact Point (T, e, Wiri, Sm, NUr, ESh, ..., N I and o) on block 35 is connected to one specific printed circuit board. Thus, there are 13 printed circuit boards in the kit, but are shown.
    5 1
    only two. The remaining eleven boards removed for greater clarity. Figure 4 shows in small arrows how the system works.
    The direction indicator 33 indicates N and the control current flows to the connection points N 1P, N P, N I. However, the anemometer indicates O, so the effect of the wind indicator indicator is not important. Through the connection point O a PCB is connected. Since the position sensor is triggered, the control current will flow through the relays h 15, h 14, and h 13, which will open valves 15, 14 and 13. I
    If the contact arm 41 of the anemometer displaces the I position in the gust of the wind, two successively connected relays 42 and 43 at the connection point N1 are closed, as a result of which the printed circuit board M G, In accordance with the printed circuit board N1, valves 12 and 13 when the position sensor is in position h. The two outermost nozzles 12 and 30 in the portal (see, Fig. 2) will spray the liquid as a result, despite the fact that the wing tips are not yet on: they move under the nozzles. However, a gust of wind displaces the jet of fluid in the S direction (it is assumed that the aircraft is moving in the N direction), resulting in the fluid falling on the wing closing before it enters portal 1.
    The movement of the aircraft 4 relative to the portal 1 can also cause the beginning and end of the spraying, with the help of a variety of sensors, which directly drive the nozzle valves without programming. A system operating in this way may have a number of light sources located in the direction of the jet coming from the center, preferably on the ground, but possibly also in other places. The light sources are formed and directed so that they create a narrow light beam towards the photocell located near each nozzle. The photocell controls the electrically actuable valve of this nozzle. As long as the light beam between the light source and the photocell is not interrupted, the valve remains closed under the action of the photocell. When
    8-6
    An object crosses a beam of light, the photocell triggers and opens the nozzle valve, causing the de-icing fluid to spray onto the object. When the object leaves the light source and the nozzle, the light beam will again begin to illuminate the photocell, which will cause the valve to close and stop spraying. Such a photoelectric system may have a light source and a photocell located adjacently, and the photocell is triggered by the light emitted by the light source and reflected from an object located in front of the light source.
    In addition to light, sound can also be used to detect the position of the aircraft. In a device of this type, the source and receiver of sound are preferably located along a line that coincides with the direction of the line coming out of the nozzle, one of which is located behind the room in which the aircraft is moving. and the other near the nozzle. As long as the Sound can pass unhindered from the source to the receiver, the valve of this nozzle remains closed, but when an object appears in front of the nozzle and the sound closes, the valve opens and the treatment liquid begins to spray.
    p 5 jq
    权利要求:
    Claims (4)
    [1]
    35 claims

    1, The anti-icing and cleaning device control system of the aircraft, comprising a position sensor located on the aircraft’s movement path, and executing the valves connected to the liquid spraying device, so that in order to provide faster, more efficient and safe removal of ice at a lower cost and without risk to the staff, additional position sensors installed along the aircraft’s travel path and a software unit, whose inputs are connected, are introduced into it. s to the outputs of position sensors, and the outputs - the valves to the actuators, wherein the program unit comprises a relay arranged in a matrix.
    moreover, the relay coils are connected after V
    by matching groups in matrix rows between the inputs of the software block and the source of driving current, and the closing contacts of the corresponding relays are connected in series in the matrix columns between the operating current source and the outputs of the software block.
    [2]
    2. Pop-up system 1, characterized in that the program block is made in the form of interchangeable printed circuit boards corresponding to the type of aircraft.
    [3]
    3. A system according to claim 1, characterized in that a wind direction indicator, a wind force indicator and a selection unit connected to the indicator outputs are inserted into it
    printed circuit boards of a program block corresponding to certain wind parameters; the outputs of which are connected to the corresponding printed circuit board.
    [4]
    4. The system of claim 2, wherein the selection unit of the printed circuit boards corresponding to certain wind parameters includes relays arranged in a matrix, the columns of which are connected to the wind direction indicator outputs, and the rows to wind force indicator outputs or vice versa , the c-each point of intersection of the matrix is formed by series-connected closing contacts corresponding to their given row and column of the relay and is the output of the block.
    12
    qSij / j-qsj
    qs;
    -OO-i
    srig.Z
    zg
    to H:
    Compiled by T.Soboleva Editor M.Petrova Tehred M.Kodanich:; Proofreader M.Sharoshi
    800/64
    Circulation 422 - By letter of VNIIPI USSR State Committee
    for inventions and discoveries 113035, Moscow, Zh-35, Raushsk nab., 4/5
    Production and printing company, Uzhgorod, Projecto st., 4
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    同族专利:
    公开号 | 公开日
    FI61666C|1982-09-10|
    WO1979000331A1|1979-06-14|
    DE2861520D1|1982-02-25|
    SE7713619L|1979-06-02|
    EP0007958B1|1982-01-06|
    JPS6318560B2|1988-04-19|
    FI783672A|1979-06-02|
    FI61666B|1982-05-31|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    SE7713619A|SE412353B|1977-12-01|1977-12-01|DEPLOY DEPARTURE AND CLEANING SYSTEM|
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