CN115973420A - Wing hot gas anti-icing control system and air anti-icing pressure control method - Google Patents
Wing hot gas anti-icing control system and air anti-icing pressure control method Download PDFInfo
- Publication number
- CN115973420A CN115973420A CN202211611682.0A CN202211611682A CN115973420A CN 115973420 A CN115973420 A CN 115973420A CN 202211611682 A CN202211611682 A CN 202211611682A CN 115973420 A CN115973420 A CN 115973420A
- Authority
- CN
- China
- Prior art keywords
- icing
- wing
- temperature
- pressure
- valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
The invention provides a wing hot gas anti-icing control system and an air anti-icing pressure control method. The system comprises a wing anti-icing valve, a wing anti-icing pressure sensor, a wing anti-icing temperature sensor, a wing anti-icing ground temperature monitoring sensor, a wing anti-icing monitoring pressure sensor, a wing anti-icing controller, a bleed air fan valve and a flute pipe, wherein the wing anti-icing controller comprises an independent control channel and an independent monitoring channel, and the wing anti-icing valve comprises an independent valve turn-off circuit and a valve adjusting circuit. The invention can realize ground and air anti-icing, can calculate anti-icing more accurately than the reference upstream bleed air temperature anti-icing according to the wing anti-icing pressure sensor, and can still perform anti-icing or maximum anti-icing under the condition of ensuring the optimal condition of the airplane as far as possible under the conditions of single bleed air anti-icing, bleed air fault or performance reduction and the like. Therefore, the invention not only can effectively reduce energy consumption and improve economy and safety, but also has good anti-icing effect and good universality.
Description
Technical Field
The invention relates to the field of anti-icing design, in particular to a wing hot gas anti-icing control system. In addition, the invention also relates to an air anti-icing pressure control method.
Background
An aircraft anti-icing system is a system for preventing or eliminating ice accretion on certain parts of the surface of an aircraft in flight, which heats the surface of the aircraft prone to ice accretion, mainly by means of hot air from the engine or by converting electrical energy into thermal energy, in order to prevent ice accretion or to melt the ice layer. Especially, icing on the leading edges of wings and empennages, or on the leading edges of propellers, air inlet ducts and cockpit windshields, can cause flight risks in severe cases, for example, icing on the leading edges of wings and empennages can change the profile shape, reduce lift, increase drag, even make flight control difficult and unstable, and icing on other parts can bring various difficulties. For this reason, an anti-icing system should be installed at a portion prone to ice formation.
The main anti-icing area on the airplane comprises wings, a tail wing, an engine air inlet, a propeller, a windshield glass fiber and temperature and pressure measuring probes. Depending on the location and the amount of energy required for anti-icing, different anti-icing methods are available for different areas. Aircraft anti-icing systems mainly fall into three categories: first, the ice is prevented by using hot air equipment; secondly, spraying anti-icing liquid with a very low freezing point to the part which is easy to freeze to prevent ice or dissolve the ice; thirdly, electric energy is used for ice prevention, namely resistance wires are pasted on parts which are easy to freeze, such as the front edge of the propeller and windshield glass, and the electric current generates heat to dissolve the ice when passing through the resistance wires.
Modern large and medium sized passenger aircraft use hot air to ice-protect the leading edges of wings and empennages. The hot air originates from the compressor of the turbojet engine. The anti-icing pipeline is hidden at the leading edge of the wing, and the hot air flows inside for one circle, so that the water vapor can be prevented from being frozen at the leading edge of the wing. The hotter air flows aft and over the airfoil, which in turn may form a protective layer.
Currently, there are several main schemes in the technical field:
for example, the existing document CN105059553B proposes an intelligent hot gas anti-icing system based on anti-icing bleed air flow required, which is based on an atmospheric liquid water content tester installed on the back of an aircraft, an aircraft speed, an attack angle, an ambient temperature, and an anti-icing temperature installed on an anti-icing bleed air pipeline to realize a bleed air flow value required for real-time anti-icing on demand, and realize closed-loop control according to an anti-icing bleed air sensor installed on the anti-icing bleed air pipeline.
For another example, the prior documents US20140290749A1 and US8843253B1 control the anti-icing flow based on the bleed air pressure, bleed air temperature and flying height upstream of the anti-icing valve, are open loop control, and only monitor the anti-icing temperature.
As another example, the prior document CN202863770U proposes to regulate the pressure by means of a pressure regulator according to a temperature sensor and a pressure sensor; the anti-icing valve is only used for controlling the opening and closing of the anti-icing, and the inner and outer anti-icing valves are used for adjusting the anti-icing pressure of the inner measuring pipeline and controlling the pressure in an open loop control manner; and monitoring ground overheating by adopting a ground overtemperature switch.
As described above, it is obvious that the prior documents US20140290749A1, US8843253B1 and CN202863770U propose open-loop control according to the bleed air temperature and pressure, while the prior document CN105059553B proposes anti-icing (pressure and temperature are a certain set of fixed values) by accurately calculating the required anti-icing bleed air flow value in real time according to the aircraft speed, the attack angle, the ambient temperature and the anti-icing temperature installed on the anti-icing bleed air pipeline, and realizing closed-loop control.
However, the anti-icing flow of the wing hot gas anti-icing system of the current aircraft mainly needs to be anti-iced according to the maximum requirement in the whole flight envelope range, so that the waste of engine bleed air is easily caused, high energy consumption is brought, and the safety, the anti-icing effect and the universality are not good.
Disclosure of Invention
The present invention has been made to solve the above-mentioned problems, and a primary object of the present invention is to provide a wing hot gas anti-icing control system and an air anti-icing pressure control method, which do not cause waste of engine bleed air, thereby effectively reducing energy consumption, improving economy and safety, and having good anti-icing effect and good versatility.
Another object of the present invention is to provide an aircraft including the above-mentioned wing hot gas anti-icing control system.
In order to achieve the above object, according to one aspect of the present invention, there is provided a wing hot gas anti-icing system comprising a wing anti-icing shutter, a wing anti-icing pressure sensor, a wing anti-icing temperature sensor, a wing anti-icing ground temperature monitoring sensor, a wing anti-icing monitoring pressure sensor, a wing anti-icing controller, a bleed air fan shutter, and a flute type duct,
wherein the wing anti-icing controller comprises an independent control channel and a monitoring channel, the wing anti-icing valve comprises an independent valve turn-off circuit and a valve adjusting circuit,
the valve adjusting circuit, the wing anti-icing pressure sensor and the wing anti-icing temperature sensor of the wing anti-icing valve are connected with the control channel of the wing anti-icing controller, and the valve turn-off circuit, the wing anti-icing ground temperature monitoring sensor and the wing anti-icing monitoring pressure sensor of the wing anti-icing valve are connected with the monitoring channel of the wing anti-icing controller.
Preferably, in the above-mentioned wing hot gas anti-icing system, still include handing over and transporting bleed valve, the wing hot gas anti-icing system is left-right symmetric arrangement and comprises left wing hot gas anti-icing system and right wing hot gas anti-icing system, wherein, left wing hot gas anti-icing system with right wing hot gas anti-icing system by handing over and transporting bleed valve intercommunication.
Preferably, in the above wing hot gas anti-icing system, the structure of any one side of the left wing hot gas anti-icing system and the right wing hot gas anti-icing system is: the downstream of wing anti-icing valve just is in install in proper order at the entrance of anti-icing flute type pipe wing anti-icing pressure sensor with wing anti-icing temperature sensor follows then along anti-icing flute type pipe installs in proper order wing anti-icing ground temperature monitoring sensor with wing anti-icing monitoring pressure sensor, wherein, bleed fan valve via engine bleed extremely the upper reaches of wing anti-icing valve, and wing anti-icing temperature sensor with bleed fan valve is connected.
Preferably, in the wing hot gas anti-icing system, on the ground, the wing anti-icing controller periodically and intermittently performs anti-icing according to the wing anti-icing pressure sensor and the wing anti-icing temperature sensor and according to a set time, and monitors whether the ground is over-temperature or not through the wing anti-icing ground temperature monitoring sensor.
Preferably, in the wing hot gas anti-icing system, the wing anti-icing controller determines the required anti-icing pressure and temperature target value according to the inlet temperature of the anti-icing whistle type tube on the basis of the adjusted bleed air temperature and pressure according to the flight state (including altitude, speed and attack angle) of the aircraft in the air, and performs anti-icing by adjusting the downstream pressure of the wing anti-icing valve so as to meet the anti-icing flow demand.
Preferably, in the wing hot gas anti-icing system, the wing anti-icing temperature sensor monitors whether the air anti-icing temperature is low, and when the temperature measured by the wing anti-icing temperature sensor is lower than a set temperature value, the wing hot gas anti-icing system is determined to be in a low temperature state and timely notifies a pilot.
Preferably, in the above-mentioned wing hot gas anti-icing system, when the pressure difference between the wing anti-icing pressure sensor and the wing anti-icing monitoring pressure sensor is greater than or equal to a set value, it is determined as an anti-icing leakage state, and the anti-icing leakage state is reported to the pilot in time.
Preferably, in the above-mentioned wing hot gas anti-icing system, when the pressure value measured by the wing anti-icing pressure sensor is smaller than the set pressure value or the pressure value measured by the wing anti-icing monitoring pressure sensor is smaller than the set pressure value, it is determined as a low pressure state, and the low pressure state is reported to the pilot in time.
Preferably, in the above-mentioned wing hot gas anti-icing system, the relay may be included in the wing anti-icing controller or may be independent of the wing anti-icing controller.
According to another aspect of the present invention, there is provided an air anti-icing pressure control method, comprising the steps of:
firstly, adjusting the angle of an anti-icing valve of the wing, then measuring an adjusted anti-icing pressure measured value by a wing anti-icing pressure sensor, further judging whether the adjusted anti-icing pressure measured value is consistent with an anti-icing pressure target value,
secondly, measuring the regulated anti-icing temperature measured value by the wing anti-icing temperature sensor, further judging whether the regulated anti-icing temperature measured value is consistent with the anti-icing temperature target value,
thirdly, if the pressure is inconsistent, readjusting the pressure according to different set pressures and temperature groups meeting the anti-icing flow requirement,
and fourthly, if the final adjustment still cannot be met, performing proper upstream bleed air temperature adjustment.
According to a further aspect of the invention there is provided an aircraft including a wing hot gas anti-icing control system of the invention.
In view of the above, compared with the prior art, the core technology of the wing hot gas anti-icing control system and the aerial anti-icing pressure control method of the invention is as follows: the closed-loop control of the anti-icing pressure can be finely performed in a segmented mode according to the flight state of the airplane, different air-entraining temperatures, air-entraining pressure and the downstream temperature of the anti-icing valve, so that anti-icing control and monitoring can be performed, meanwhile, independent anti-icing pressure monitoring and ground anti-icing temperature monitoring can be performed, and when the temperature is over-temperature and over-pressure, the anti-icing valve can be turned off in an overrunning mode.
Due to the technical scheme, compared with the prior art, the wing hot gas anti-icing control system and the air anti-icing pressure control method can realize ground and air anti-icing; during air anti-icing, the anti-icing is more accurately calculated according to the wing anti-icing pressure sensor than the reference upstream bleed air temperature anti-icing; meanwhile, for the same anti-icing flow value at a certain moment, a plurality of anti-icing pressure and temperature groups are used for anti-icing control, so that anti-icing is more economical, and the upstream air entraining design is facilitated, so that under the conditions of single-shot air entraining anti-icing, air entraining fault or performance reduction and the like, anti-icing can still be carried out or anti-icing to the maximum extent can be carried out under the condition of ensuring the aircraft to be optimal as far as possible. In addition, intermittent anti-icing is adopted during ground anti-icing, overtemperature is monitored, and during anti-icing, the conditions of anti-icing temperature, pressure, leakage detection and the like are monitored, so that a pilot is notified, and the anti-icing is turned off through an independent monitoring function as required. Therefore, the ice prevention is not required to be carried out according to the maximum requirement in the whole flight envelope range, so that the waste of engine air entraining is avoided, the energy consumption can be effectively reduced, the economy and the safety are improved, the ice prevention effect is good, and the universality is good.
The preferred embodiments can be combined arbitrarily to obtain preferred embodiments of the present invention on the basis of common general knowledge in the field.
Drawings
For a better understanding of the above and other objects, features, advantages and functions of the invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.
FIG. 1 is a schematic diagram illustrating the configuration of a preferred embodiment of the hot gas anti-icing control system for an airfoil of the present invention;
FIG. 2 schematically illustrates a flow diagram of an aerial anti-icing pressure control method;
fig. 3 schematically shows a principle diagram of the independent monitoring of the shutter shutoff.
List of reference numerals in the figures in the technical solutions and embodiments:
1. anti-icing valve for wing
11. Valve shutoff circuit
12. Valve regulating circuit
2. Anti-icing pressure sensor for wing
3. Wing anti-icing temperature sensor
4-wing anti-icing ground temperature monitoring sensor
5-wing anti-icing monitoring pressure sensor
6. Anti-icing controller for wing
61. Control channel
62. Monitoring channel
7. Air-entraining fan valve
8. Anti-icing flute type pipe
9. Air entraining valve for transportation
Flight state of A plane
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
In this regard, it is first noted that in the detailed description of these embodiments, it is not possible for the specification to describe in detail all of the features of an actual embodiment in order to provide a concise description. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions are often made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be further appreciated that such a development effort might be complex and tedious, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as a complete understanding of this disclosure.
In addition, it is to be noted that technical terms or scientific terms used in the claims and the specification should have a general meaning as understood by those having ordinary skill in the art to which the present invention belongs, unless otherwise defined. The terms "a" or "an," and the like, do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprise" or "comprises", and the like, means that the element or item listed before "comprises" or "comprising" covers the element or item listed after "comprising" or "comprises" and its equivalent, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, nor are they restricted to direct or indirect connections.
A preferred embodiment of the hot gas anti-icing system for an airfoil of the present invention will be described in detail with reference to fig. 1 so that the advantages and features of the invention may be readily understood by those skilled in the art, and thus the scope of the invention will be more clearly defined.
In general, as shown in FIG. 1, a schematic diagram of the configuration of the hot gas anti-icing system of the airfoil of the present invention is schematically illustrated.
As shown in the figure, the wing hot gas anti-icing system mainly comprises: the device comprises a wing anti-icing valve 1, a wing anti-icing pressure sensor 2, a wing anti-icing temperature sensor 3, a wing anti-icing ground temperature monitoring sensor 4, a wing anti-icing monitoring pressure sensor 5, a wing anti-icing controller 6, a bleed air fan valve 7 and an anti-icing whistle type pipe 8.
Specifically, as shown in fig. 1, the wing anti-icing controller 6 includes a separate control channel 61 and monitoring channel 62, and the wing anti-icing shutter 1 includes a separate shutter shutdown circuit 11 and shutter regulation circuit 12. The valve regulating circuit 12, the wing anti-icing pressure sensor 2 and the wing anti-icing temperature sensor 3 of the wing anti-icing valve 1 are connected with a control channel 61 of the wing anti-icing controller 6, and the valve shutoff circuit 11, the wing anti-icing ground temperature monitoring sensor 4 and the wing anti-icing monitoring pressure sensor 5 of the wing anti-icing valve 1 are connected with a monitoring channel 62 of the wing anti-icing controller 6.
In addition, as shown in the figure, the wing hot gas anti-icing system further comprises a delivery bleed valve 9, and the wing hot gas anti-icing system is arranged in a bilateral symmetry manner and consists of a left wing hot gas anti-icing system and a right wing hot gas anti-icing system. Wherein, the hot gas anti-icing system of the left wing is communicated with the hot gas anti-icing system of the right wing through a delivery bleed valve 9. When the air-entraining fan valve 7 or the wing anti-icing valve 1 on one side has a fault, the cross-transportation air-entraining valve 9 is opened, and the engine air-entraining on the other side ensures that the whole wing hot air anti-icing system can normally work.
In addition, the structure of the wing hot gas anti-icing system on any one side in the left wing hot gas anti-icing system and the right wing hot gas anti-icing system is as follows: the wing anti-icing pressure sensor 2 and the wing anti-icing temperature sensor 3 are sequentially installed at the downstream of the wing anti-icing valve 1 and at the inlet of the anti-icing flute tube 8, then the wing anti-icing ground temperature monitoring sensor 4 and the wing anti-icing monitoring pressure sensor 5 are sequentially installed along the anti-icing flute tube 8, the air-entraining fan valve 7 entrains air to the upstream of the wing anti-icing valve 1 through an engine, and the wing anti-icing temperature sensor 3 is connected with the air-entraining fan valve 7.
The wing hot gas anti-icing system measures the temperature according to the flight state of the airplane and the inlet of the wing anti-icing flute-shaped pipe, and performs anti-icing according to different set pressure and temperature groups in the air under the condition of controlling anti-icing pressure so as to ensure the flow required by anti-icing to control anti-icing; monitoring anti-icing over-temperature, low temperature, overpressure and low pressure in the anti-icing process, and independently turning off the anti-icing according to requirements; the ground is anti-iced according to a determined pressure value, and the anti-icing is independently turned off when overtemperature is detected; and the two pressure sensors are arranged to detect the anti-icing leakage of the wing. The working principle of the invention is as follows:
(1)ground anti-icing and over-temperature monitoring
In the ground, the wing anti-icing controller 6 periodically and intermittently prevents ice according to the wing anti-icing pressure sensor 2 and the wing anti-icing temperature sensor 3 according to the set time, and monitors whether the ground is over-temperature or not through the wing anti-icing ground temperature monitoring sensor:
when ground ice prevention or testing is carried out, the control channel 61 of the wing ice prevention controller 6 automatically and intermittently opens ice prevention according to logic (working time and non-working time are limited) so as to ensure that overheating does not occur while ground ice prevention or testing is carried out;
when ground ice prevention or test is carried out, the monitoring channel 62 of the wing ice prevention controller 6 independently monitors overtemperature through the wing ice prevention ground temperature monitoring sensor 4, and when overtemperature occurs, the monitoring channel 62 of the wing ice prevention controller 6 overrides and shuts off the wing ice prevention valve 1 through the valve shutdown circuit 11 of the wing ice prevention valve 1.
(2)Aerial relative economy anti-icing
In the air, the wing anti-icing controller 6 determines the required anti-icing pressure and temperature target value according to the adjusted bleed air temperature and pressure basis (upstream bleed air) according to the flight state A (including the height, the speed and the attack angle) of the airplane and the inlet temperature of the anti-icing whistle type pipe 8, and carries out anti-icing by adjusting the downstream pressure of the wing anti-icing valve 1 so as to meet the anti-icing flow requirement.
Specifically, fig. 2 schematically shows a flow chart of the air anti-icing pressure control method, and table 1 shows an air anti-icing temperature and pressure combination table. As shown in the figure, when the airplane encounters icing meteorological conditions in the flying process, the wing hot-gas anti-icing system is started:
firstly, adjusting the angle of the wing anti-icing valve 1, then measuring the adjusted anti-icing pressure measurement value by the wing anti-icing pressure sensor 2, further judging whether the adjusted anti-icing pressure measurement value Pa is consistent with the anti-icing pressure target value Px,
secondly, measuring the adjusted anti-icing temperature measured value Ta by the wing anti-icing temperature sensor, further judging whether the adjusted anti-icing temperature measured value Ta is consistent with the anti-icing temperature target value Tx or not,
thirdly, if the pressure is inconsistent with the ice-proof flow Q, the pressure is readjusted according to different set pressure and temperature groups meeting the requirement of the ice-proof flow Q,
and fourthly, if the final adjustment cannot be met, properly adjusting the upstream bleed air temperature.
TABLE 1 Combined gauge for temp. and pressure of ice-proof in air
(3)Air anti-icing low temperature
And monitoring whether the air anti-icing temperature is low or not according to the wing anti-icing temperature sensor 3, judging the air anti-icing temperature to be in a low temperature state when the temperature measured by the wing anti-icing temperature sensor 3 is less than a set temperature value, and timely reporting to a pilot.
(4)Anti-ice leakage detection
Based on the flight state A and the temperature control value of the airplane, when the pressure difference value measured by the wing anti-icing pressure sensor 2 and the wing anti-icing monitoring pressure sensor 5 is greater than or equal to a set value A, the state is judged to be the anti-icing leakage state, and at the moment, the pilot is timely notified to operate and guide subsequent system fault positioning and maintenance.
(5)Anti-icing overpressure detection
Based on the flight state A and the temperature control value of the airplane, when the pressure value measured by the wing anti-icing pressure sensor 2 is greater than a set pressure value B or the pressure value measured by the wing anti-icing monitoring pressure sensor 5 is greater than a set pressure value C (wherein B > C), the airplane is judged to be in an overpressure state and the airplane is informed to a pilot in time.
(6)Anti-icing low voltage detection
And based on the flight state A and the temperature control value of the airplane, when the pressure value measured by the wing anti-icing pressure sensor 2 is smaller than a set pressure value D or the pressure value measured by the wing anti-icing monitoring pressure sensor 5 is smaller than a set pressure value E (wherein D > E), judging the airplane to be in a low-pressure state and timely reporting the airplane to a pilot.
(7)Independent and prioritized monitor turn-off functionality
Fig. 3 schematically shows the principle of the independent monitoring of the shutter shutdown. As shown in fig. 3, the wing anti-icing controller 6 adopts an independent control channel 61 and a monitoring channel 62, and the wing anti-icing shutter 1 includes an independent shutter shutdown circuit 11 and a shutter regulating circuit 12, and has a shutdown override function. It is worth mentioning here that the relay function may be included in the wing ice protection control 6 or be independent of the wing ice protection control 6.
In conclusion, the wing hot gas anti-icing control system and the air anti-icing pressure control method can realize ground and air anti-icing, and during air anti-icing, on the basis of upstream air guiding temperature regulation and pressure regulation, the anti-icing pressure is regulated through the anti-icing valve according to the required anti-icing flow Q, so as to perform anti-icing, and meanwhile, whether the anti-icing temperature and the anti-icing pressure are consistent with the target value or not is judged, and if not, the requirement of the anti-icing flow Q is finally met through regulating again according to the set temperature and pressure group. During air anti-icing, the anti-icing is more accurately calculated according to the wing anti-icing pressure sensor 2 than the anti-icing of the reference upstream bleed air temperature; meanwhile, for the same anti-icing flow value at a certain moment, a plurality of anti-icing pressure and temperature sets are used for anti-icing control, so that anti-icing is more economical, and the upstream air entraining design is facilitated, so that under the conditions of single-shot air entraining anti-icing, air entraining fault or performance reduction and the like, anti-icing can still be carried out or anti-icing to the maximum degree can be carried out under the condition of ensuring the optimal airplane as far as possible. In addition, intermittent anti-icing is adopted during ground anti-icing, overtemperature is monitored, and during anti-icing, the conditions of anti-icing temperature, pressure, leakage detection and the like are monitored, so that a pilot is notified, and the anti-icing is turned off through an independent monitoring function as required. Therefore, the ice prevention is not required to be carried out according to the maximum requirement in the whole flight envelope range, so that the waste of engine air entraining is avoided, the energy consumption can be effectively reduced, the economy and the safety are improved, the ice prevention effect is good, and the universality is good.
Preferred embodiments of the present invention have been described in detail above, but it is understood that other advantages and modifications will readily occur to those skilled in the art upon reading the foregoing teachings of the invention. Therefore, the invention in its broader aspects is not limited to the specific details and representative embodiments shown and described herein. Accordingly, reasonable combinations and modifications of the elements of the above-described embodiments can be made by those skilled in the art to make various modifications without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.
Claims (12)
1. A wing hot gas anti-icing system comprises a wing anti-icing valve, a wing anti-icing pressure sensor, a wing anti-icing temperature sensor, a wing anti-icing ground temperature monitoring sensor, a wing anti-icing monitoring pressure sensor, a wing anti-icing controller, a bleed fan valve and a flute-shaped pipe,
wherein the wing anti-icing controller comprises an independent control channel and a monitoring channel, the wing anti-icing valve comprises an independent valve turn-off circuit and a valve adjusting circuit,
the valve adjusting circuit, the wing anti-icing pressure sensor and the wing anti-icing temperature sensor of the wing anti-icing valve are connected with the control channel of the wing anti-icing controller, and the valve turn-off circuit, the wing anti-icing ground temperature monitoring sensor and the wing anti-icing monitoring pressure sensor of the wing anti-icing valve are connected with the monitoring channel of the wing anti-icing controller.
2. The airfoil hot gas anti-icing system of claim 1,
still include the transportation bleed valve, wing steam anti-icing system is bilateral symmetry and arranges and comprises left wing steam anti-icing system and right wing steam anti-icing system, wherein, left wing steam anti-icing system with right wing steam anti-icing system by the transportation bleed valve intercommunication.
3. The airfoil hot gas anti-icing system of claim 2,
the structure of any one side in the left wing hot gas anti-icing system and the right wing hot gas anti-icing system is as follows: the wing anti-icing pressure sensor and the wing anti-icing temperature sensor are sequentially arranged at the downstream of the wing anti-icing valve and at the inlet of the anti-icing flute type pipe, then the wing anti-icing ground temperature monitoring sensor and the wing anti-icing monitoring pressure sensor are sequentially arranged along the anti-icing flute type pipe,
the air-entraining fan valve entrains air to the upstream of the wing anti-icing valve through an engine, and the wing anti-icing temperature sensor is connected with the air-entraining fan valve.
4. The wing hot gas anti-icing system of any of claims 1 to 3,
and when the ground is over-temperature, the wing anti-icing controller periodically and intermittently prevents ice according to the wing anti-icing pressure sensor and the wing anti-icing temperature sensor and monitors whether the ground is over-temperature or not through the wing anti-icing ground temperature monitoring sensor.
5. The airfoil hot gas anti-icing system according to one of claims 1 to 3,
in the air, the wing anti-icing controller determines the required anti-icing pressure and temperature target value according to the inlet temperature of the anti-icing whistle type tube on the basis of the adjusted bleed air temperature and pressure according to the flight state of the airplane, and performs anti-icing by adjusting the downstream pressure of the wing anti-icing valve so as to meet the anti-icing flow requirement.
6. The airfoil hot gas anti-icing system of claim 5,
the flight state of the aircraft comprises the altitude, the speed and the attack angle.
7. The airfoil hot gas anti-icing system according to one of claims 1 to 3,
and monitoring whether the air anti-icing temperature is low or not according to the wing anti-icing temperature sensor, and judging the air anti-icing temperature to be in a low temperature state and timely reporting to a pilot when the temperature measured by the wing anti-icing temperature sensor is lower than a set temperature value.
8. The airfoil hot gas anti-icing system according to one of claims 1 to 3,
and when the pressure difference value measured by the wing anti-icing pressure sensor and the wing anti-icing monitoring pressure sensor is greater than or equal to a set value, judging the state of anti-icing leakage and timely reporting to a pilot.
9. The airfoil hot gas anti-icing system according to one of claims 1 to 3,
and when the pressure value measured by the wing anti-icing pressure sensor is smaller than the set pressure value or the pressure value measured by the wing anti-icing monitoring pressure sensor is smaller than the set pressure value, judging the pressure state to be a low-pressure state, and timely reporting the low-pressure state to a pilot.
10. The airfoil hot gas anti-icing system according to one of claims 1 to 3,
the relay may be included within the wing ice protection control or separate from the wing ice protection control.
11. A method for aerial anti-icing pressure control using the wing hot gas anti-icing system of any of claims 1 to 10, comprising the steps of:
firstly, adjusting the angle of an anti-icing valve of the wing, then measuring an adjusted anti-icing pressure measured value by a wing anti-icing pressure sensor, further judging whether the adjusted anti-icing pressure measured value is consistent with an anti-icing pressure target value,
secondly, measuring the regulated anti-icing temperature measured value by the wing anti-icing temperature sensor, further judging whether the regulated anti-icing temperature measured value is consistent with the anti-icing temperature target value,
thirdly, if the pressure is inconsistent with the ice-proof flow, the pressure is readjusted according to different set pressure and temperature groups meeting the ice-proof flow requirement,
and fourthly, if the final adjustment still cannot be met, performing proper upstream bleed air temperature adjustment.
12. An aircraft, characterized in that the aircraft comprises a wing hot gas anti-icing system according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211611682.0A CN115973420A (en) | 2022-12-14 | 2022-12-14 | Wing hot gas anti-icing control system and air anti-icing pressure control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211611682.0A CN115973420A (en) | 2022-12-14 | 2022-12-14 | Wing hot gas anti-icing control system and air anti-icing pressure control method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115973420A true CN115973420A (en) | 2023-04-18 |
Family
ID=85965815
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211611682.0A Pending CN115973420A (en) | 2022-12-14 | 2022-12-14 | Wing hot gas anti-icing control system and air anti-icing pressure control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115973420A (en) |
-
2022
- 2022-12-14 CN CN202211611682.0A patent/CN115973420A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4783026A (en) | Anti-icing management system | |
| CN107271134B (en) | High-precision simulation method for icing wind tunnel hot gas anti-icing test | |
| US10737792B2 (en) | Turbofan engine fluid ice protection delivery system | |
| CA2768929C (en) | Environmental control system supply precooler bypass | |
| US7959109B2 (en) | Dual valve apparatus for aircraft engine ice protection and related methods | |
| CN107543649B (en) | Hot air deicing total pressure sensor | |
| EP3219957A1 (en) | Thermal management system for deicing aircraft with temperature based flow restrictor | |
| US10569888B2 (en) | Leading edge ice-protection system | |
| US8843253B1 (en) | Aircraft ice protection control system and method for mitigating engine over-bleed | |
| US20110225975A1 (en) | Method for controlling an electrical deicing system | |
| CN206990187U (en) | A kind of high-precision icing wind tunnel hot air anti-icing experiment simulator | |
| US10017262B2 (en) | Pulsed deicing system | |
| CN112211726B (en) | Continuous air entraining system based on turbojet engine | |
| EP2835517A1 (en) | An anti-ice system for preventing ice crystal accretion in gas turbine engines | |
| CN115973420A (en) | Wing hot gas anti-icing control system and air anti-icing pressure control method | |
| CN115452312B (en) | Hot gas flow measurement and control method and system | |
| CN110589026B (en) | Ground test device of closed-loop aircraft electric anti-icing system | |
| CA3078279C (en) | Method for the control of the anti-icing system of the aircraft gas turbine engine | |
| CN116255246A (en) | Turbofan engine composite anti-icing system with vertical take-off and landing power device | |
| CN104329171A (en) | Airplane and engine thereof | |
| US9976481B2 (en) | Dual pressure deicing system | |
| CN117241417B (en) | Electric heating anti-icing thermal load test method for front edge of aircraft air inlet | |
| US11358727B2 (en) | Method and apparatus for predicting conditions favorable for icing | |
| Tian et al. | An Experimental Study on a Hybrid Anti-/De-icing Strategy for Aero-Engine Inlet Guide Vane Icing Protection | |
| CN115973421A (en) | Hot gas anti-icing system with waste heat recovery function |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |