CN102897324B - Anti-icing device for aircraft - Google Patents
Anti-icing device for aircraft Download PDFInfo
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- CN102897324B CN102897324B CN201210243673.0A CN201210243673A CN102897324B CN 102897324 B CN102897324 B CN 102897324B CN 201210243673 A CN201210243673 A CN 201210243673A CN 102897324 B CN102897324 B CN 102897324B
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Abstract
The invention relates to an anti-icing device for an aircraft. The anti-icing device for an aircraft comprises an input module, an anti-icing controller and an anti-icing module, wherein the input module is coupled to the anti-icing controller via hardwired connection and an avionics system bus, and used for generating a manual control signal for controlling the running of the anti-icing module; the anti-icing controller is used for receiving the manual control signal, sending an automatic control signal to the anti-icing module to control the running of the anti-icing module while receiving the manual control signal with a first value, and sending the manual control signal to the anti-icing module to control the running of the anti-icing module while receiving the manual control signal which is different from the first value; and the anti-icing module is coupled to the anti-icing controller, and used for receiving the manual control signal and the automatic control signal, and responding to the manual control signal and the automatic control signal to be started or stopped.
Description
Technical field
The present invention relates to anti-icing equipment, more specifically, the present invention relates to a kind of aircraft anti-icing device for aircraft engine intake.
Background technology
Icing phenomenon may occur when aircraft flies under icing meteorology condition, especially aircraft engine intake more easily freezes under driving engine swabbing action.Inlet channel freezes and can change the profile of engine inlets inside face, thus causes the effective admission area of engine inlets to reduce, and then engine thrust may be caused to decline and surge.In addition, the ice be accumulated in engine inlets comes off and may damage engine blower blade, even can cause engine off, thus affect flight safety time serious.Therefore, need to start aircraft anti-icing system in time under icing meteorology condition, to prevent and/or to remove the accumulated ice in the accumulated ice on the aircraft under state of flight, particularly inlet channel.It should be noted that term " ice " involved in the application should comprise various ice, frost and composition thereof.
In order to the normal operation preventing accumulated ice from affecting aircraft, on the aircraft of some models, (such as B777 type and A380 type aircraft) is equipped with aircraft anti-icing system.This aircraft anti-icing system comprises icing detector and anti-icing controller.Wherein, icing detector is installed in the position of the easy accumulated ice of aircraft, such as plane nose, wing or engine inlets etc., and is used to the accumulated ice state detecting these positions.Such as, icing detector has probe, and the oscillation frequency of this probe is relevant to the quality that detecting head surface freezes: the oscillation frequency of probe can rise along with the increase of icing quality.Meanwhile, this icing detector can compare probe vibration frequency and a certain threshold value.After probe vibration frequency exceedes this threshold value, detector can send icing signal.Anti-icing controller couples mutually with icing detector.After anti-icing controller receives the icing signal that icing detector sends, this anti-icing controller can automatically start according to icing signal or cut out the anti-icing module in anti icing system, such as, be arranged on the anti-icing valve in engine inlets.In addition, this anti icing system is also provided with for the manually operated control panel of manipulation personnel.The order of this control panel can be sent to anti-icing controller by avionics system bus, and then manually controls the operation of anti-icing module.
But avionics system bus cannot may use because of fault in some cases, like this, the control signal of control panel cannot send to anti-icing controller, and this makes aviator be difficult to carry out switch anti icing system by control panel.It reduce the safety and reliability of aircraft anti-icing system.
Summary of the invention
Visible, need to provide a kind of aircraft anti-icing device with higher reliability.
According to an aspect of the present invention, provide a kind of aircraft anti-icing device, described aircraft anti-icing device comprises load module, anti-icing controller and anti-icing module, wherein: described load module is connected by rigid line and avionics system bus is couple to described anti-icing controller, for generating the manual control signal run for controlling described anti-icing module; Described anti-icing controller is for receiving described manual control signal, and when receiving the described manual control signal of the first value, automatic control signal is sent to control the operation of described anti-icing module to described anti-icing module, and when receiving the described manual control signal of non-first value, send described manual control signal to control the operation of described anti-icing module to described anti-icing module; Described anti-icing module couples, to described anti-icing controller, for receiving described manual control signal and described automatic control signal, and is opened in response to described manual control signal and described automatic control signal or is closed.
By adopting load module in this aircraft anti-icing device, and utilize rigid line connection and avionics system bus to connect load module and anti-icing controller, this to make when avionics system bus et out of order cannot transmission of signal time, anti-icing controller still can connect by rigid line the manual input receiving manipulation personnel, and then make manipulation personnel come unlatching or the closedown of the anti-icing module of Non-follow control, to guarantee that anti-icing module can normally work.Which greatly enhances aircraft anti-icing system reliability of operation.
In one embodiment, described anti-icing controller also for receiving the wheel load signal from described avionics system bus, and generates described automatic control signal based on described wheel load signal and described manual control signal.
In one embodiment, described aircraft anti-icing device also comprises: icing detector, it is couple to described anti-icing controller by described avionics system bus, for detecting the icing situation of plane reservation position, and provides icing testing result to described anti-icing controller; Described anti-icing controller also for receiving described icing testing result, and generates described automatic control signal based on described icing testing result.By using icing detector, anti-icing controller can accurately be determined, and aircraft is detected the icing condition of position, thus processes for ground.
In one embodiment, described aircraft anti-icing device also comprises: display module, and it is couple to described icing detector, for receiving described icing testing result and showing described icing testing result.Icing testing result shown by display module can be used for manipulation personnel reference, to determine whether to open anti-icing module.
In one embodiment, described load module is integrated on the control panel of aircraft, and it is for receiving the input of manipulation personnel, and generates described manual control signal based on described input.
In one embodiment, described anti-icing module comprises anti-icing valve.
In one embodiment, described anti-icing module is installed in the inlet channel of aero-engine.
Embodiment part is hereinafter set forth by above characteristic of the present invention and other characteristics clearly.
Accompanying drawing explanation
Read the following detailed description to non-limiting example by referring to accompanying drawing, more easily can understand features, objects and advantages of the invention.Wherein, same or analogous Reference numeral represents same or analogous device.
Fig. 1 shows the aircraft anti-icing device 100 for aircraft anti-icing system according to a first embodiment of the present invention;
Fig. 2 shows the aircraft anti-icing device 200 for aircraft anti-icing system according to a second embodiment of the present invention;
Fig. 3 shows the control panel 300 of the load module be mounted with in the aircraft anti-icing device 200 of Fig. 2.
Detailed description of the invention
Discuss enforcement and the use of embodiment below in detail.But, should be appreciated that discussed specific embodiment only exemplarily illustrates and implement and use ad hoc fashion of the present invention, but not limit the scope of the invention.
Fig. 1 shows aircraft anti-icing device 100 according to a first embodiment of the present invention.
In actual applications, this aircraft anti-icing device 100 is arranged on the easy ice field of aircraft, the inlet channel of such as aero-engine, or the wing of aircraft etc.Wherein, inlet channel refers to the inlet channel leading edge portion of fanjet.This aircraft anti-icing device 100 can manipulate the order of personnel based on aircraft or automatically start anti-icing module wherein according to the testing result of aircraft icing condition, continues to be formed in this region to eliminate or at least to stop or reduce ice.
As shown in Figure 1, this aircraft anti-icing device 100 comprises load module 101, anti-icing controller 103 and anti-icing module 105, wherein:
Load module 101 is couple to anti-icing controller 103 by rigid line connection 107 and avionics system bus 109, for generating the manual control signal run for controlling anti-icing module 105.
Anti-icing controller 103 is for receiving manual control signal, and when receiving the manual control signal of the first value, automatic control signal is sent to control the operation of anti-icing module 105 to anti-icing module 105, and when receiving the manual control signal of non-first value, send manual control signal to control the operation of anti-icing module 105 to anti-icing module 105.
Anti-icing module 105 is couple to anti-icing controller 103, for receiving manual control signal and automatic control signal, and opens in response to manual control signal and automatic control signal or closes.
Particularly, load module 101 be such as keyboard, control lever, knob or other be applicable to receiving manipulation personnel and input and generate the equipment of corresponding electric signal.Load module 101 can be integrated on the control panel of aircraft, so that the operating personal of aircraft uses.
Manual control signal at least comprises the first value and is different from the second value and the 3rd value of the first value.Particularly, manual control signal first is worth corresponding to making anti-icing controller 103 be in automatic operational mode, namely, when anti-icing controller 103 receives the manual control signal of the first value, automatically can judge whether to need to open anti-icing module 105 according to received icing testing result.Second value of manual control signal is in open mode corresponding to making anti-icing controller 103, namely when anti-icing controller 103 receives the manual control signal of the second value, no longer automatic decision is the need of the anti-icing module 105 of unlatching, but directly the manual control signal of this second value is supplied to anti-icing module 105, open to make this anti-icing module 105.Similarly, 3rd value of manual control signal is in " shut " mode" corresponding to making anti-icing controller 103, namely when anti-icing controller 103 receives the manual control signal of the 3rd value, no longer automatic decision is the need of the anti-icing module 105 of unlatching, but directly the manual control signal of the 3rd value is supplied to anti-icing module 105, close to make this anti-icing module 105.
Wherein, load module 101 and anti-icing controller 103 by rigid line be connected 107 and avionics system bus 109 couple mutually.Wherein, when load module 101 receives the input of the manual control signal making its output the first value, the manual control signal of this first value is sent to anti-icing controller 103 by means of only avionics system bus 109 by this load module 101.And when load module 101 receives the input of the manual control signal making its output second value or the 3rd value, this load module 101 connects 107 by avionics system bus 109 and rigid line and the manual control signal of this second value or the 3rd value is sent to anti-icing controller 103.Like this, when avionics system bus 109 non-et out of order, load module 101 can be set to the manual control signal of output first value, and makes anti-icing controller 103 automatically control the operation of anti-icing module 105.And when avionics system bus 109 et out of order cannot transmission of signal time, anti-icing controller 103 still can connect by rigid line the manual input that 107 receive manipulation personnel, the manual control signal of the second value namely making anti-icing module 105 open, or the manual control signal of the 3rd value that anti-icing module 105 is closed, and then make manipulation personnel can the unlatching of the anti-icing module 105 of Non-follow control or closedown, to guarantee that anti-icing module 105 can normally work.Which greatly enhances whole aircraft anti-icing device 100 reliability of operation.
In one embodiment, anti-icing controller 103 also for receiving the wheel load signal from avionics system bus 109, and generates described automatic control signal based on wheel load signal and manual control signal.Particularly, wheel load signal is used to indicate aircraft and is in state of flight or non-state of flight.When anti-icing controller 103 receive instruction aircraft be in the wheel load signal of state of flight time, anti-icing controller 103 can provide manual control signal or automatic control signal based on aforesaid different manual control signal to anti-icing module 105 further.And when anti-icing controller 103 receive instruction aircraft be in the wheel load signal of non-state of flight time, anti-icing controller 103 only provides automatic control signal or manual control signal that it is closed to anti-icing module 105.
According to the difference of embody rule, anti-icing module 105 can adopt various applicable elimination or at least reduce the device of ice of presumptive area on aircraft.In one embodiment, this anti-icing module 105 comprises anti-icing valve.This anti-icing valve can be arranged in the inlet channel of aero-engine, or other positions.
Fig. 2 shows aircraft anti-icing device 200 according to a second embodiment of the present invention.
As shown in Figure 2, this aircraft anti-icing device 200 comprises load module 201, anti-icing controller 203, anti-icing module 205 and icing detector 211, wherein:
Load module 201 is couple to anti-icing controller 203 by rigid line connection 207 and avionics system bus 209, for generating the manual control signal run for controlling anti-icing module 205.
Icing detector 211 is couple to anti-icing controller 203, for detecting the icing situation of plane reservation position, and exports testing result of freezing.
Anti-icing controller 203 is for receiving manual control signal, and when receiving the manual control signal of the first value, automatic control signal is sent to control the operation of anti-icing module 205 to anti-icing module 205, and when receiving the manual control signal of non-first value, send manual control signal to control the operation of anti-icing module 205 to anti-icing module 205; Anti-icing controller 203 also for receiving icing testing result, and generates automatic control signal based on icing testing result.
Anti-icing module 205 for receiving manual control signal and automatic control signal, and is opened in response to manual control signal and automatic control signal or closes.
Particularly, icing detector 211 is used to the icing condition detecting plane reservation position.Such as, icing detector 211 has probe, and the oscillation frequency of this probe is relevant to the quality that detecting head surface freezes: the oscillation frequency of probe can rise along with the increase of icing quality.Meanwhile, this icing detector 211 can compare probe vibration frequency and a certain threshold value.After probe vibration frequency exceedes this threshold value, icing detector 211 can send the icing testing result that instruction plane reservation position freezes.Again such as, icing detector 211 may be used for the temperature detecting plane reservation position, and when temperature is lower than a certain temperature threshold, icing detector 211 sends its icing testing result of freezing of instruction.In response to this icing testing result, anti-icing controller 203 sends to anti-icing module 205 automatic control signal that it is opened.Like this, by using icing detector 211, anti-icing controller 203 can accurately be determined, and aircraft is detected the icing condition of position, thus processes for ground.
In one embodiment, aircraft anti-icing device 200 also comprises: display module 213, and it is couple to icing detector 211, for receiving the icing testing result that provided by icing detector 211 and showing this icing testing result.Like this, icing testing result can be used for manipulation personnel reference, to determine whether manually to open anti-icing module 205 by load module 201.
Fig. 3 shows the control panel 300 of the load module be mounted with in the aircraft anti-icing device 200 of Fig. 2.This control panel 300 is such as arranged on the gauge panel of aircraft, for aircraft manipulation librarian use.
As shown in Figure 3, this control panel 300 comprises two control dials 301 and 302, wherein control dial 301 is for inputting and indicating the operation of the anti-icing equipment of aircraft lefthand engine, and control dial 302 is for inputting and indicating the operation of the anti-icing equipment of aircraft righthand engine.
Wherein, control dial 301 and 302 has three different knob position separately, and wherein each knob position corresponds to a value of manual control signal.Particularly, the knob position being labeled as " automatically " corresponds to the first value of manual control signal, and namely when control dial 301 is in the knob position of " automatically ", the load module 201 in Fig. 2 exports the manual control signal of the first value.The knob position being labeled as "ON" corresponds to the second value of manual control signal, and the load module 201 namely in Fig. 2 exports the manual control signal of the second value.The knob position being labeled as "Off" corresponds to the 3rd value of manual control signal, and the load module 201 namely in Fig. 2 exports the manual control signal of the 3rd value.
Although illustrate in detail in accompanying drawing and aforesaid description and describe the present invention, it is illustrative and exemplary for should thinking that this is illustrated and describes, instead of restrictive; The invention is not restricted to above-mentioned embodiment.
The those skilled in the art of those the art can pass through research specification sheets, disclosed content and accompanying drawing and appending claims, understand and implement other changes to the embodiment disclosed.In the claims, word " comprises " element and step of not getting rid of other, and wording " one " does not get rid of plural number.In the practical application of invention, the function of the multiple technical characteristics quoted during a part possibility enforcement of rights requires.Any Reference numeral in claim should not be construed as the restriction to scope.
Claims (7)
1. an aircraft anti-icing device, is characterized in that, described aircraft anti-icing device comprises load module, anti-icing controller and anti-icing module, wherein:
Described load module is connected by rigid line and avionics system bus is couple to described anti-icing controller, for generating the manual control signal run for controlling described anti-icing module;
Described anti-icing controller is for receiving described manual control signal, and when receiving the described manual control signal of the first value, automatic control signal is sent to control the operation of described anti-icing module to described anti-icing module, and when receiving the described manual control signal of non-first value, send described manual control signal to control the operation of described anti-icing module to described anti-icing module;
Described anti-icing module couples, to described anti-icing controller, for receiving described manual control signal and described automatic control signal, and is opened in response to described manual control signal and described automatic control signal or is closed.
2. aircraft anti-icing device according to claim 1, is characterized in that, described anti-icing controller also for receiving the wheel load signal from described avionics system bus, and generates described automatic control signal based on described wheel load signal and described manual control signal.
3. aircraft anti-icing device according to claim 1, is characterized in that, described aircraft anti-icing device also comprises:
Icing detector, it is couple to described anti-icing controller by described avionics system bus, for detecting the icing situation of plane reservation position, and provides icing testing result to described anti-icing controller;
Described anti-icing controller also for receiving described icing testing result, and generates described automatic control signal based on described icing testing result.
4. aircraft anti-icing device according to claim 3, is characterized in that, described aircraft anti-icing device also comprises:
Display module, it is couple to described icing detector, for receiving described icing testing result and showing described icing testing result.
5. aircraft anti-icing device according to claim 1, is characterized in that, described load module is integrated on the control panel of aircraft, and it is for receiving the input of manipulation personnel, and generates described manual control signal based on described input.
6. aircraft anti-icing device according to claim 1, is characterized in that, described anti-icing module comprises anti-icing valve.
7. aircraft anti-icing device according to claim 6, is characterized in that, described anti-icing module is installed in the inlet channel of aero-engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210243673.0A CN102897324B (en) | 2012-07-13 | 2012-07-13 | Anti-icing device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210243673.0A CN102897324B (en) | 2012-07-13 | 2012-07-13 | Anti-icing device for aircraft |
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| Publication Number | Publication Date |
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| CN102897324A CN102897324A (en) | 2013-01-30 |
| CN102897324B true CN102897324B (en) | 2015-06-10 |
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| CN201210243673.0A Active CN102897324B (en) | 2012-07-13 | 2012-07-13 | Anti-icing device for aircraft |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103101626B (en) * | 2012-12-04 | 2015-09-02 | 中国商用飞机有限责任公司 | Icing detector |
| CN104340368B (en) * | 2013-07-24 | 2017-02-08 | 中国国际航空股份有限公司 | Aircraft wing anti-icing valve monitoring system and method and maintaining method of aircraft wing anti-icing valve |
| CN103942371B (en) * | 2013-12-26 | 2016-11-16 | 西北工业大学 | Reliability sensitivity method is obtained under anti-icing bleed air system temperature fault |
| CN104950864B (en) * | 2014-03-26 | 2018-06-05 | 成都凯天电子股份有限公司 | The method of on-line checking aircraft engine anti-icing system characteristic |
| CN108128466B (en) * | 2018-04-26 | 2018-07-27 | 中国商用飞机有限责任公司 | Image-type icing detector and icing detection method |
| CN109625291A (en) * | 2018-12-04 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of biplane ice-detector system |
| CN111874234B (en) * | 2020-07-22 | 2022-06-24 | 南京航空航天大学 | Ice accumulation prediction method based on Ic index and relative vorticity and airborne equipment |
| CN112373696B (en) * | 2020-11-24 | 2022-03-01 | 中国商用飞机有限责任公司 | Aircraft anti-icing method and system |
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| GB621464A (en) * | 1943-08-11 | 1949-04-11 | Bendix Aviat Corp | Control system for de-icer equipment |
| CN102209666A (en) * | 2008-11-17 | 2011-10-05 | 埃尔塞乐公司 | Method for controlling an electrical deicing system |
| CN102407942A (en) * | 2011-09-06 | 2012-04-11 | 中国商用飞机有限责任公司 | Ice formation condition detector |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2891241B1 (en) * | 2005-09-23 | 2009-03-13 | Airbus France Sas | SYSTEM FOR DEFROSTING AND / OR DEMANDING AN AIRCRAFT SURFACE, METHOD FOR CONTROLLING SUCH A SYSTEM, AND AIRCRAFT EQUIPPED WITH SUCH A SYSTEM. |
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| GB621464A (en) * | 1943-08-11 | 1949-04-11 | Bendix Aviat Corp | Control system for de-icer equipment |
| CN102209666A (en) * | 2008-11-17 | 2011-10-05 | 埃尔塞乐公司 | Method for controlling an electrical deicing system |
| CN102407942A (en) * | 2011-09-06 | 2012-04-11 | 中国商用飞机有限责任公司 | Ice formation condition detector |
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| CN102897324A (en) | 2013-01-30 |
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