CN112829949A - Airplane icing risk monitoring method - Google Patents
Airplane icing risk monitoring method Download PDFInfo
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- CN112829949A CN112829949A CN202011563630.1A CN202011563630A CN112829949A CN 112829949 A CN112829949 A CN 112829949A CN 202011563630 A CN202011563630 A CN 202011563630A CN 112829949 A CN112829949 A CN 112829949A
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- 238000000034 method Methods 0.000 title claims abstract description 90
- 238000012544 monitoring process Methods 0.000 title claims abstract description 50
- 230000008569 process Effects 0.000 claims abstract description 57
- 230000008859 change Effects 0.000 claims abstract description 32
- 238000007664 blowing Methods 0.000 claims abstract description 31
- 238000004088 simulation Methods 0.000 claims abstract description 31
- 230000000694 effects Effects 0.000 claims abstract description 19
- 238000005507 spraying Methods 0.000 claims abstract description 11
- 238000012360 testing method Methods 0.000 claims abstract description 10
- 238000012502 risk assessment Methods 0.000 claims abstract description 4
- 238000005485 electric heating Methods 0.000 claims description 28
- 239000007788 liquid Substances 0.000 claims description 28
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 25
- 238000010438 heat treatment Methods 0.000 claims description 10
- 239000007921 spray Substances 0.000 claims description 7
- 230000005484 gravity Effects 0.000 claims description 6
- 230000008030 elimination Effects 0.000 claims description 4
- 238000003379 elimination reaction Methods 0.000 claims description 4
- 206010034719 Personality change Diseases 0.000 abstract description 12
- 230000036544 posture Effects 0.000 description 9
- 230000008014 freezing Effects 0.000 description 8
- 238000007710 freezing Methods 0.000 description 8
- 230000003068 static effect Effects 0.000 description 8
- 230000009471 action Effects 0.000 description 6
- 230000006872 improvement Effects 0.000 description 4
- 238000005259 measurement Methods 0.000 description 4
- 238000012806 monitoring device Methods 0.000 description 4
- 230000005494 condensation Effects 0.000 description 3
- 238000009833 condensation Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
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Abstract
The invention relates to the technical field of airplane risk monitoring, in particular to an airplane icing risk monitoring method, which comprises flight condition simulation, attitude adjustment, ice shape recording, deicing test and risk analysis; the flying condition simulation assembly further comprises a ring frame, an air blowing cylinder and a spraying port; because the phase change condition that the aerodynamic performance of the airplane is interfered in the icing process is difficult to obtain, and the airplane model in the icing wind tunnel weakens the simulation effect under the fixed posture, the accuracy of airplane icing risk monitoring is further reduced; therefore, the invention reflects the attitude change of the airplane with the influenced pneumatic performance after icing by sliding the ball top arranged on the supporting rod and the ball mouth of the airplane model, monitors the stress change condition of the airplane model in simulated flight in the ring frame by matching the elastic cushion ring at the end part of the ball mouth with the pressure sensor below the ball top, and obtains the specific parameters of the airplane with the influenced pneumatic performance in the icing state, thereby improving the accuracy of the airplane icing risk monitoring method.
Description
Technical Field
The invention relates to the technical field of airplane risk monitoring, in particular to an airplane icing risk monitoring method.
Background
The icing of the airplane refers to the phenomenon that ice layers are accumulated on certain parts of the surface of the airplane body, and is mainly formed by icing after supercooled water drops in cloud or supercooled rain in falling water touches the airplane body, and can also be formed by water vapor directly desublimating the surface of the airplane body; the atmospheric temperature is gradually reduced along with the increase of the altitude, the atmosphere contains water vapor formed by the evaporation of water on the ground, the atmospheric temperature changes along with the dew point and the water vapor content of the atmospheric environment in the flying process of the airplane, and then the icing is formed on the airplane, and if an ice layer is accumulated on the surface of the airplane in the flying process of the airplane, the aerodynamic appearance of the airplane is influenced, so that the aerodynamic performance of the airplane is reduced, and the flying accident is caused.
Therefore, the research on the icing appearance of the airplane under different meteorological conditions is important for monitoring the icing risk of the airplane, and the currently obtained icing appearance of the airplane mainly passes through three ways of simulation calculation, flight test and icing wind tunnel simulation; the simulation calculation lacks accurate description on the complex phase change process of icing after cold water drops impact on the surface of the airplane; flight tests are difficult to meet icing tests under various meteorological conditions, and are often used for verifying the performance of an aircraft anti-icing and deicing system; the icing wind tunnel simulation can artificially simulate parameters of various meteorological conditions and obtain the repeated icing appearance parameters of the airplane.
At present, in the process of icing wind tunnel simulation, the influence on the aerodynamic performance of the airplane is calculated by observing the ice-shaped appearance formed after icing and combining the shape of the structure of the airplane, so as to monitor the risk of the airplane flying in an icing state, but the influence is difficult to obtain the phase change condition of the airplane with the disturbed aerodynamic performance in the icing process, and the airplane model in the icing wind tunnel weakens the simulation effect of the actual dynamic icing process under a fixed posture, thereby reducing the accuracy of monitoring the icing risk of the airplane.
Some technical solutions related to methods for monitoring the risk of icing of an aircraft have been proposed in the prior art, and for example, a chinese patent with application number 2015105442879 discloses a method comprising a plurality of operations performed in real time during the flight of an aircraft. That is, the method may include monitoring a continuous electrical signal output by a sensor on a surface of the aircraft, wherein an amplitude of the electrical signal may be related to an amount of ice buildup; the solution includes calculating a Liquid Water Content (LWC) value from a variation of the electrical signal, and iteratively calculating a Total Water Exposure (TWE) value from the LWC value. The TWE value may represent a total water exposure of the aircraft from a time of an initial event and may be calculated as an accumulated value over a number of iterations. And the method may include performing remedial or warning measures if the TWE value reaches the TWE threshold; however, when the aircraft of the technical scheme is used for an icing risk experiment, the aircraft has corresponding requirements on meteorological conditions, and the problem that the flight risk of the aircraft in the icing process under different meteorological conditions can be measured is limited.
In view of the above, in order to overcome the above technical problems, the present invention provides an aircraft icing risk monitoring method, which adopts a special aircraft icing risk monitoring method to solve the above technical problems.
Disclosure of Invention
In order to make up for the defects of the prior art, the invention provides an aircraft icing risk monitoring method, which comprises the steps of slidably mounting a ball top arranged on a support rod and a ball opening of an aircraft model, reflecting the attitude change of the aircraft with influenced aerodynamic performance after icing, and matching an elastic cushion ring at the end part of the ball opening with a pressure sensor below the ball top to monitor the stress change condition of the aircraft model in real time during simulated flight in a ring frame, so as to obtain the specific parameters of the influenced aerodynamic performance of the aircraft in an icing state, thereby improving the accuracy of the aircraft icing risk monitoring method.
The invention relates to a method for monitoring the icing risk of an airplane, which comprises the following steps:
s1, flight condition simulation: installing the airplane model into an icing wind tunnel, and adjusting the operation parameters of the icing wind tunnel to ensure that the airplane model is in the range of minus 40-0 ℃, the diameter of liquid drops in the icing wind tunnel is 15-50 mu m, and the liquid water content in the icing wind tunnel is controlled to be 0-3g/m3To simulate the icing process of an aircraft in flight;
s2, posture adjustment: in the process of adjusting parameters of the icing wind tunnel in S1, simultaneously controlling a support rod in the icing wind tunnel to adjust the attitude of the airplane model so as to simulate the change process of the attitude angle of the airplane in the flying process and obtain the icing conditions of the airplane in different states;
s3, ice shape recording: and (4) calculating the influence of the outline of the frozen ice on the airplane model in the S2 on the aerodynamic performance of the airplane, monitoring the stress change process of the airplane model according to the pressure sensor in the supporting rod, and judging the theoretical critical value of the icing risk of the airplane model:
s4, deicing test: in the icing process of the airplane model in S2, simultaneously starting the electric heating sheets installed in the airplane model to simulate the operation of deicing equipment of the airplane in actual flight, testing the deicing effect on the airplane model and further obtaining the interference of heating modules at different positions on the airplane model on the icing process;
s5, risk analysis: the pneumatic performance analysis is carried out on the airplane model through the ice shape recorded in the S3, the influence of the ice shape on the safety of the flight process is judged, the pneumatic performance of the airplane model in the deicing process in the S4 is recorded, and the deicing state of the electric heating sheet is adjusted by combining the pneumatic parameters of the airplane model under different conditions;
the icing wind tunnel comprises an icing condition simulation component and a controller in S1-S5; the flight condition simulation assembly is used for monitoring the state of the aircraft model and changing the operation parameters of the flight condition simulation assembly under the regulation of the controller; the flying condition simulation assembly also comprises a ring frame, an air blowing cylinder and a spraying port; the ring frame is arranged in the icing wind tunnel intermittently along the axial direction, a support rod is further arranged in the ring frame, a ball top is arranged at the top of the support rod, and an annular pressure sensor is further arranged between the ball top and the support rod; the top of the supporting rod is arranged on the gravity center of the airplane model; a ball opening is formed in the gravity center position of the airplane model, and an elastic cushion ring is arranged at the end part of the ball opening; the airplane model is installed through sliding contact between the ball opening and the ball top, and is limited by the elastic cushion ring and the pressure sensor; the pressure sensor is used for monitoring pressure change of the elastic cushion ring in the circumferential direction of the elastic cushion ring; the head of the airplane model is provided with an air blowing cylinder in the direction, and the air blowing cylinder is arranged at the end part of the ring frame; the end part of the ring frame is also provided with a bogie, the bogie is wrapped on the circumference of the air blowing cylinder, and the angle of air flow blown to the airplane model by the air blowing cylinder is adjusted; the circumferential direction of the ring frame is also provided with a spraying port, and the spraying port sprays liquid drops to the airplane model in the ring frame; the air blowing cylinder introduces cold airflow into the icing wind tunnel to freeze liquid drops attached to the airplane model;
in the prior art, an airplane is tested in an icing wind tunnel, the influence on the aerodynamic performance of the airplane is usually calculated by observing the ice-shaped appearance formed after icing and combining the shape of the structure of the airplane, so as to monitor the risk of the airplane flying in an icing state, but the phase change condition of the airplane with the disturbed aerodynamic performance in the icing process is difficult to obtain, and the airplane model in the icing wind tunnel weakens the simulation effect of the actual dynamic icing process under a fixed posture, so that the accuracy of monitoring the icing risk of the airplane is reduced;
therefore, the invention installs the airplane model in the ring frame of the icing wind tunnel through the supporting rod arranged in the ring frame, the air flow of the air drum barrel and the orientation of the airplane model form a changed included angle state by adjusting the bogie at the end part of the ring frame, under the action of the spray ports on the circumferential direction of the ring frame, liquid drops are sprayed onto the airplane model through the omnidirectional angle to simulate the liquid drops in all directions contacted by the airplane in the process of altitude change, and the attitude change of the airplane model during icing is transmitted to the pressure sensor through the elastic backing ring by the sliding installation between the ball top of the supporting rod and the ball opening of the airplane model, further obtaining stress values of the airplane model in different postures, changing the posture of the airplane model under the influence of the aerodynamic performance by combining the icing process of liquid drops on the airplane model, and further changing the subsequent condensation shape of an icing part to obtain a more real icing shape of the airplane; the invention utilizes the ball top arranged on the supporting rod and the ball opening of the airplane model to be installed in a sliding way, reflects the attitude change of the airplane with the influenced pneumatic performance after the airplane is frozen, and monitors the stress change condition of the airplane model in the ring frame in real time when the airplane model simulates flying through the matching of the elastic cushion ring at the end part of the ball opening and the pressure sensor below the ball top, thereby obtaining the specific parameters of the influenced pneumatic performance of the airplane in the frozen state and further improving the accuracy of the airplane freezing risk monitoring method.
Preferably, a traction table and a guide frame are arranged below the supporting rod, and the supporting rod is fixed on the traction table; the traction table is slidably mounted on the guide frame, and a driving oil cylinder is arranged between the traction table and the end part of the guide frame; when the pressure sensor is used, the contact and icing processes between the airplane and liquid drops at different speeds are simulated by controlling the wind power in the air drum, and the air drum can generate different static pressure losses of the airplane model in the ring frame under the wind power change state, so that the accuracy of the stress value of the airplane model reflected by the pressure sensor is weakened, and the measurement precision of the aerodynamic performance of the pressure sensor is reduced; through the traction table and the guide frame which are arranged below the supporting rod, after the wind power of the air blowing cylinder is adjusted, the position of the airplane model in the ring frame is changed through the driving of the oil cylinder, the stress values of the pressure sensors of the airplane model and the air blowing cylinder in different distance states are measured, static pressure loss data of the airplane model in the icing wind tunnel are obtained, the interference of the static pressure loss on the measured data of the airplane model under different wind power conditions is further reduced, and therefore the measuring precision of the airplane icing risk monitoring method is improved.
Preferably, the side part of the guide frame is also provided with paired roller wheels, and the guide frame is slidably mounted on the circumferential direction of the ring frame; the roller wheel is clamped on the surface of the ring frame, a driving servo motor is installed at the end part of the roller wheel, and the roller wheel drives the guide frame to change the position of the guide frame on the ring frame; during the use, through with leading truck slidable mounting on the ring frame, under the drive of roller bearing wheel, make the leading truck remove along the circumference of ring frame, and then drive the aircraft model in the ring frame and change its deflection angle, the removal of traction table and the wind-force that changes in the blast cylinder on the cooperation leading truck, the formation process that freezes after the simulation aircraft receives the liquid drop to spray under different flight gestures, the reinforcing monitoring aircraft appearance that freezes is to the accuracy of aerodynamic performance interference, and can obtain the aircraft and receive the influence of the risk of freezing in the flight gesture change process, thereby the accuracy of aircraft risk monitoring method that freezes has been promoted.
Preferably, the support rod is also provided with a lifting rod, and a bump is also arranged on the top of the ball above the lifting rod; the convex block is parallel to the axial direction of the ring frame and is attached and arranged in a concave pit arranged in the ball opening; when the device is used, the distance between the airplane model and the ring frame is adjusted through the arranged lifting rod, the variation range of pneumatic parameters generated by the airplane model under the action of the air blowing cylinder is enlarged, and the device is matched with the movement of the traction table and the guide frame, so that the airplane model can be subjected to three-dimensional attitude adjustment in the icing wind tunnel, the authenticity of the flight state of the simulated airplane is enhanced, the accurate process of airplane icing is further obtained, and the lug and the pit which are arranged in the ball top and the ball mouth limit the phenomenon that the pneumatic performance of the airplane model after icing is interfered, the flight attitude is prevented from being out of control, meanwhile, the threshold value that the airplane enters the out-of-control state under the influence of different icing degrees is obtained, and therefore the accuracy of the airplane icing risk monitoring method is improved.
Preferably, a contact piece is further arranged on the contact surface of the convex block and the concave pit; the electric heating pieces are arranged on the airplane model and are positioned at the slat and flap parts of the airplane model; the controller adjusts the running state of the electric heating pieces through the electric connection between the contact pieces; during the use, aircraft self has corresponding defroster, can resist the condition of icing of slight degree, through setting up the electric heat piece on aircraft model, communicate to the controller between the contact on, make it heat aircraft model to the effect of defroster when moving in the simulation aircraft, and under aircraft model is in the state of icing, start the elimination effect of electric heat piece observation to the condition of icing on aircraft model, in order to monitor the improvement effect to aircraft model aerodynamic performance, thereby the accuracy of aircraft icing risk monitoring method has been promoted.
Preferably, the engine part of the airplane model is also provided with an air return groove, and the air return groove is protruded on the circumferential direction of the inner wall of the engine; the inner wall of the engine is also provided with a surrounding electric heating wire, and the electric heating wire keeps a constant heating state; the air return groove guides airflow entering the interior of the engine to the wing through a pipeline and discharges the airflow along a nozzle of the engine; when the airplane icing risk monitoring device is used, the heating wires arranged on the inner wall of the engine are used for simulating the engine part with high temperature during airplane operation, meanwhile, the air flow entering the engine is guided to the wings by the air return grooves to circulate, the airplane icing risk monitoring device is equivalent to an engine air-entraining structure in an airplane deicing device and is combined with the electric heating sheets on the airplane model to detect the icing risk of the airplane in different operation states, and therefore the accuracy of the airplane icing risk monitoring method is improved.
The invention has the following beneficial effects:
1. the invention reflects the attitude change of the airplane affected by the aerodynamic performance after icing by sliding the ball top arranged on the supporting rod and the ball opening of the airplane model, and monitors the stress change condition of the airplane model in the ring frame during simulated flight in real time by matching the elastic cushion ring at the end part of the ball opening and the pressure sensor below the ball top, thereby obtaining the specific parameters of the airplane affected by the aerodynamic performance in the icing state.
2. According to the invention, the distance between the airplane model and the ring frame is adjusted by the traction table and the guide frame which are arranged below the support rod and the lifting rod which are arranged in a matching manner, the icing forming process of the airplane after being sprayed by liquid drops under different flight attitudes is simulated, the influence of icing risks on the airplane in the flight attitude change process is monitored, and the threshold value of the airplane entering the off-control state under the influence of different icing degrees is obtained.
3. The invention simulates the operation effect of the deicing device in the airplane through the electric heating sheets arranged on the airplane model and the heating wires arranged on the inner wall of the engine, so as to monitor the improvement effect on the aerodynamic performance of the airplane model and detect the icing risk of the airplane in different operation states.
Drawings
The invention is further described with reference to the following figures and embodiments.
FIG. 1 is a flow chart of a method of monitoring aircraft icing risk according to the present invention;
FIG. 2 is a perspective view of a flight condition simulation assembly of the present invention;
FIG. 3 is a perspective view of the internal structure of the flight simulator assembly of the present invention;
FIG. 4 is an enlarged view of a portion of FIG. 2 at A;
FIG. 5 is a partial enlarged view at B in FIG. 3;
FIG. 6 is an enlarged view of a portion of FIG. 3 at C;
in the figure: the device comprises a ring frame 1, a bogie 11, an air blowing cylinder 2, a spraying opening 3, a support rod 4, a ball top 41, a convex block 411, a pressure sensor 42, a contact sheet 421, a ball opening 43, a concave pit 431, an elastic cushion ring 44, a lifting rod 45, a traction table 5, an oil cylinder 51, a guide frame 6, a rolling wheel 61, an electric heating sheet 7, an air return groove 8 and an electric heating wire 9.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
As shown in fig. 1 to 6, the method for monitoring the icing risk of an aircraft according to the present invention includes the following steps:
s1, flight condition simulation: installing the airplane model into an icing wind tunnel, and adjusting the operation parameters of the icing wind tunnel to ensure that the airplane model is in the range of minus 40-0 ℃, the diameter of liquid drops in the icing wind tunnel is 15-50 mu m, and the liquid water content in the icing wind tunnel is controlled to be 0-3g/m3To simulate the icing process of an aircraft in flight;
s2, posture adjustment: in the process of adjusting parameters of the icing wind tunnel in S1, simultaneously controlling a support rod 4 in the icing wind tunnel to adjust the attitude of the airplane model so as to simulate the change process of the attitude angle of the airplane in the flying process and obtain the icing conditions of the airplane in different states;
s3, ice shape recording: and (3) calculating the influence of the outline of the frozen ice on the airplane model in the S2 on the aerodynamic performance of the airplane, monitoring the stress change process of the airplane model according to the pressure sensor 42 in the supporting rod 4, and judging the theoretical critical value of the icing risk of the airplane model:
s4, deicing test: in the icing process of the airplane model in S2, simultaneously starting the electric heating sheets 7 installed in the airplane model to simulate the operation of deicing equipment of the airplane in actual flight, testing the deicing effect on the airplane model and further obtaining the interference of heating modules at different positions on the airplane model on the icing process;
s5, risk analysis: the pneumatic performance analysis is carried out on the airplane model through the ice shape recorded in the S3, the influence of the ice shape on the safety of the flight process is judged, the pneumatic performance of the airplane model in the deicing process in the S4 is recorded, and the deicing state of the electric heating plate 7 is adjusted by combining the pneumatic parameters of the airplane model under different conditions;
the icing wind tunnel comprises an icing condition simulation component and a controller in S1-S5; the flight condition simulation assembly is used for monitoring the state of the aircraft model and changing the operation parameters of the flight condition simulation assembly under the regulation of the controller; the flying condition simulation assembly also comprises a ring frame 1, an air blowing cylinder 2 and a spraying port 3; the ring frame 1 is arranged in the icing wind tunnel intermittently along the axial direction, a support rod 4 is further arranged in the ring frame 1, a ball top 41 is arranged at the top of the support rod 4, and an annular pressure sensor 42 is further arranged between the ball top 41 and the support rod 4; the top of the support rod 4 is arranged on the center of gravity of the airplane model; a ball opening 43 is formed in the gravity center position of the airplane model, and an elastic cushion ring 44 is arranged at the end part of the ball opening 43; the airplane model is installed through sliding contact between the ball opening 43 and the ball top 41, and is limited by the elastic cushion ring 44 and the pressure sensor 42; the pressure sensor 42 is used for monitoring the pressure change of the elastic cushion ring 44 in the circumferential direction; the head of the airplane model is provided with an air blowing cylinder 2 in an oriented manner, and the air blowing cylinder 2 is arranged at the end part of the ring frame 1; the end part of the ring frame 1 is also provided with a bogie 11, the bogie 11 is wrapped in the circumferential direction of the air blowing barrel 2, and the angle of air flow blown to the airplane model by the air blowing barrel 2 is adjusted; the spraying ports 3 are also formed in the circumferential direction of the ring frame 1, and liquid drops are sprayed onto the airplane model in the ring frame 1 through the spraying ports 3; the air drum barrel 2 introduces cold air flow into the icing wind tunnel to freeze liquid drops attached to the airplane model;
in the prior art, an airplane is tested in an icing wind tunnel, the influence on the aerodynamic performance of the airplane is usually calculated by observing the ice-shaped appearance formed after icing and combining the shape of the structure of the airplane, so as to monitor the risk of the airplane flying in an icing state, but the phase change condition of the airplane with the disturbed aerodynamic performance in the icing process is difficult to obtain, and the airplane model with a fixed posture weakens the simulation effect of the actual dynamic icing process, so that the accuracy of monitoring the icing risk of the airplane is reduced;
therefore, the invention installs the airplane model in the ring frame 1 of the icing wind tunnel by the supporting rod 4 arranged in the ring frame 1, makes the air flow of the air blowing cylinder 2 and the orientation of the airplane model form a changed included angle state by adjusting the bogie 11 at the end part of the ring frame 1, sprays liquid drops on the airplane model through an omnidirectional angle under the action of the spray port 3 on the circumference of the ring frame 1, simulates the liquid drops in each direction contacted by the airplane in the height change process, and transmits the attitude change of the airplane model during icing to the pressure sensor 42 through the elastic backing ring 44 by the sliding installation between the ball top 41 of the supporting rod 4 and the ball port 43 of the airplane model, further obtains the stress values of the airplane model under different attitudes, combines the icing process of the liquid drops on the airplane model, makes the attitude change under the influence of aerodynamic performance, further changes the subsequent condensation shape of the ice junction, obtaining a more real icing appearance of the airplane; the invention utilizes the ball top 41 arranged on the support rod 4 and the ball mouth 43 of the airplane model to be installed in a sliding way, reflects the attitude change of the airplane with the influenced pneumatic performance after the airplane is frozen, and monitors the stress change condition of the airplane model in the ring frame 1 during simulated flight through the matching of the elastic cushion ring 44 at the end part of the ball mouth 43 and the pressure sensor 42 below the ball top 41 in real time, thereby obtaining the specific parameters of the influenced pneumatic performance of the airplane in the freezing state and further improving the accuracy of the airplane freezing risk monitoring method.
As an embodiment of the invention, a traction table 5 and a guide frame 6 are arranged below the support rod 4, and the support rod 4 is fixed on the traction table 5; the traction table 5 is slidably mounted on the guide frame 6, and a driving oil cylinder 51 is arranged between the traction table 5 and the end part of the guide frame 6; when the device is used, the contact and icing processes between the airplane and liquid drops at different speeds are simulated by controlling the wind power in the air blowing cylinder 2, and the airplane model in the ring frame 1 can generate different static pressure losses under the wind power change state of the air blowing cylinder 2, so that the accuracy of the stress value of the airplane model reflected by the pressure sensor 42 is weakened, and the measurement precision of the aerodynamic performance of the airplane is reduced; through the traction table 5 and the guide frame 6 which are arranged below the support rod 4, after the wind power of the air blowing cylinder 2 is adjusted, the position of the airplane model in the ring frame 1 is changed through the driving of the oil cylinder 51, the stress values of the pressure sensor 42 of the airplane model and the air blowing cylinder 2 in different distance states are measured, the static pressure loss data of the airplane model in the icing wind tunnel are obtained, the interference of the static pressure loss on the airplane model measurement data under different wind power conditions is further reduced, and the measurement precision of the airplane icing risk monitoring method is improved.
As an embodiment of the present invention, the side of the guiding frame 6 is further provided with a pair of roller wheels 61, and the guiding frame 6 is slidably mounted on the circumferential direction of the ring frame 1; the roller wheel 61 is clamped on the surface of the ring frame 1, a driving servo motor is arranged at the end part of the roller wheel 61, and the roller wheel 61 drives the guide frame 6 to change the position of the guide frame on the ring frame 1; during the use, through with leading truck 6 slidable mounting on ring frame 1, under the drive of roller wheel 61, make leading truck 6 remove along ring frame 1's circumference, and then drive the aircraft model in the ring frame 1 and change its deflection angle, the wind-force that changes in the removal of traction table 5 and the blast cylinder 2 on the cooperation leading truck 6, the freezing shaping process after the simulation aircraft is sprayed by the liquid drop under different flight attitudes, the reinforcing monitoring aircraft freezes the accuracy that the appearance disturbed the aerodynamic performance, and can obtain the aircraft and receive the influence of the risk of freezing in the flight attitude change process, thereby the accuracy of aircraft freezing risk monitoring method has been promoted.
As an embodiment of the present invention, a lifting rod 45 is further disposed in the supporting rod 4, and a protrusion 411 is further disposed on the top 41 above the lifting rod 45; the convex block 411 is parallel to the axial direction of the ring frame 1, and the convex block 411 is attached and installed in a concave pit 431 arranged in the ball socket 43; when the device is used, the distance between the airplane model and the ring frame 1 is adjusted through the arranged lifting rod 45, the variation range of pneumatic parameters generated by the airplane model under the action of the air blowing cylinder 2 is enlarged, and the traction table 5 and the guide frame 6 are matched to move, so that the airplane model is subjected to three-dimensional attitude adjustment in the icing wind tunnel, the authenticity of the flight state of the simulated airplane is enhanced, and the accurate process of airplane icing is further obtained.
As an embodiment of the present invention, a contact 421 is further disposed on a contact surface of the protrusion 411 and the recess 431; the airplane model is provided with an electric heating sheet 7, and the electric heating sheet 7 is positioned at the slat and flap parts of the airplane model; the controller adjusts the running state of the electric heating plate 7 through the electric connection between the contact pieces 421; during the use, aircraft self has corresponding defroster, can resist the icing condition of slight degree, through setting up electric heat piece 7 on aircraft model, on the intercommunication to the controller between contact 421, make it heat aircraft model to the effect of defroster when moving in the simulation aircraft, and be in under the state of freezing at aircraft model, start electric heat piece 7 and observe the elimination effect to the icing condition on aircraft model, in order to monitor the improvement effect to aircraft model aerodynamic performance, thereby the accuracy of aircraft icing risk monitoring method has been promoted.
As an embodiment of the invention, the engine part of the airplane model is further provided with an air return groove 8, and the air return groove 8 is protruded in the circumferential direction of the inner wall of the engine; the inner wall of the engine is also provided with a surrounding electric heating wire 9, and the electric heating wire 9 keeps a constant heating state; the air return duct 8 guides the airflow entering the interior of the engine to the wing through a pipeline and discharges the airflow along a nozzle of the engine; when the airplane icing risk monitoring device is used, the heating wires arranged on the inner wall of the engine are used for simulating the engine part with high temperature during airplane operation, meanwhile, the air flow entering the engine is guided to the wings by the air return grooves 8 for circulation, the airplane icing risk monitoring device is equivalent to an engine air-entraining structure in an airplane deicing device and is combined with the electric heating sheets 7 on the airplane model to detect the icing risk of the airplane in different operation states, and therefore the accuracy of the airplane icing risk monitoring method is improved.
When in use, the airplane model is arranged in the ring frame 1 of the icing wind tunnel through the support rod 4 arranged in the ring frame 1, the air flow of the air blowing cylinder 2 and the orientation of the airplane model form a changed included angle state by adjusting the bogie 11 at the end part of the ring frame 1, under the action of the spray ports 3 on the circumferential direction of the ring frame 1, liquid drops are sprayed onto the airplane model through the omnidirectional angle to simulate the liquid drops in all directions contacted by the airplane in the process of altitude change, and the attitude change of the airplane model during icing is transmitted to the pressure sensor 42 through the elastic cushion ring 44 by the sliding installation between the spherical top 41 of the supporting rod 4 and the spherical port 43 of the airplane model, further obtaining stress values of the airplane model in different postures, changing the posture of the airplane model under the influence of the aerodynamic performance by combining the icing process of liquid drops on the airplane model, and further changing the subsequent condensation shape of an icing part to obtain a more real icing shape of the airplane; the traction table 5 and the guide frame 6 are arranged below the support rod 4, so that after the wind power of the air blowing cylinder 2 is adjusted, the position of the airplane model in the ring frame 1 is changed through the driving of the oil cylinder 51, the stress values of the pressure sensor 42 of the airplane model and the air blowing cylinder 2 in different distance states are measured, the static pressure loss data of the airplane model in the icing wind tunnel are obtained, and the interference of the static pressure loss on the measured data of the airplane model under different wind power conditions is further reduced; the guide frame 6 is slidably mounted on the ring frame 1, the guide frame 6 is driven by the roller wheels 61 to move along the circumferential direction of the ring frame 1, so that an airplane model in the ring frame 1 is driven to change the deflection angle of the airplane model, the icing forming process of the airplane sprayed by liquid drops under different flight attitudes is simulated by matching the movement of the traction table 5 on the guide frame 6 and the changed wind power in the blast cylinder 2, the accuracy of monitoring the interference of the icing appearance of the airplane on the pneumatic performance is enhanced, and the influence of icing risks of the airplane in the flight attitude change process can be obtained; the lifting rod 45 is arranged to adjust the distance between the airplane model and the ring frame 1, the change range of pneumatic parameters generated by the airplane model under the action of the air blowing cylinder 2 is enlarged, and the traction table 5 and the guide frame 6 are matched to move, so that the airplane model is subjected to three-dimensional attitude adjustment in the icing wind tunnel, the authenticity of the flight state of the simulated airplane is enhanced, and the accurate icing process of the airplane is further obtained, and the lug 411 and the pit 431 which are arranged in the ball top 41 and the ball mouth 43 limit the aerodynamic performance of the airplane model after icing to be interfered, the flight attitude is prevented from being out of control, and meanwhile, the threshold value of the airplane entering the out-of-control state under the influence of different icing degrees is obtained; the electric heating sheet 7 arranged on the airplane model is communicated to the controller through the contact sheets 421 to heat the airplane model so as to simulate the operation effect of a deicing device in the airplane, and the electric heating sheet 7 is started to observe the elimination effect of the icing condition on the airplane model when the airplane model is in an icing state so as to monitor the improvement effect of the aerodynamic performance of the airplane model; the heating wires arranged on the inner wall of the engine simulate the high-temperature engine part of the airplane in operation, and meanwhile, the air flow entering the engine is guided to the wings for circulation by the aid of the air return grooves 8, so that the airplane deicing device is equivalent to an engine air-entraining structure in the airplane deicing device and is combined with the electric heating sheets 7 on the airplane model to detect the icing risk of the airplane in different operation states.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. An aircraft icing risk monitoring method is characterized by comprising the following steps:
s1, flight condition simulation: installing the airplane model into an icing wind tunnel, and adjusting the operation parameters of the icing wind tunnel to ensure that the airplane model is in the range of minus 40-0 ℃, the diameter of liquid drops in the icing wind tunnel is 15-50 mu m, and the liquid water content in the icing wind tunnel is controlled to be 0-3g/m3To simulate the icing process of an aircraft in flight;
s2, posture adjustment: in the process of adjusting parameters of the icing wind tunnel in S1, simultaneously controlling a support rod (4) in the icing wind tunnel to adjust the attitude of the airplane model so as to simulate the change process of the attitude angle of the airplane in the flying process and obtain the icing conditions of the airplane in different states;
s3, ice shape recording: and (3) calculating the influence of the outline of the frozen ice on the airplane model in the S2 on the aerodynamic performance of the airplane, monitoring the stress change process of the airplane model according to the pressure sensor (42) in the supporting rod (4), and judging the theoretical critical value of the icing risk of the airplane model:
s4, deicing test: in the icing process of the airplane model in S2, simultaneously starting an electric heating sheet (7) installed in the airplane model, and simulating the operation of deicing equipment of the airplane in actual flight, so as to test the elimination effect of icing on the airplane model and further obtain the interference of heating modules at different positions on the airplane model on the icing process;
s5, risk analysis: the aerodynamic performance analysis is carried out on the airplane model through the ice shape recorded in the S3, the influence of the aerodynamic performance analysis on the safety of the flight process is judged, the aerodynamic performance of the airplane model in the deicing process in the S4 is recorded, and the deicing state of the electric heating sheet (7) is adjusted by combining the aerodynamic parameters of the airplane model under different conditions;
the icing wind tunnel comprises an icing condition simulation component and a controller in S1-S5; the flight condition simulation assembly is used for monitoring the state of the aircraft model and changing the operation parameters of the flight condition simulation assembly under the regulation of the controller; the flying condition simulation assembly further comprises a ring frame (1), a blast cylinder (2) and a spraying port (3); the ring frame (1) is arranged in the icing wind tunnel intermittently along the axial direction, a support rod (4) is further arranged in the ring frame (1), a ball top (41) is arranged at the top of the support rod (4), and an annular pressure sensor (42) is further arranged between the ball top (41) and the support rod (4); the top of the supporting rod (4) is arranged on the center of gravity of the airplane model; a ball opening (43) is formed in the gravity center position of the airplane model, and an elastic cushion ring (44) is arranged at the end part of the ball opening (43); the airplane model is installed through sliding contact between a ball opening (43) and a ball top (41), and is limited by an elastic cushion ring (44) and a pressure sensor (42); the pressure sensor (42) is used for monitoring the pressure change of the elastic cushion ring (44) in the circumferential direction; the head of the airplane model is provided with an air blowing cylinder (2) in the direction, and the air blowing cylinder (2) is arranged at the end part of the ring frame (1); the end part of the ring frame (1) is also provided with a bogie (11), the bogie (11) is wrapped on the circumferential direction of the air blowing barrel (2), and the angle of air flow blown to the airplane model by the air blowing barrel (2) is adjusted; the circumferential direction of the ring frame (1) is also provided with a spraying port (3), and the spraying port (3) sprays liquid drops to an airplane model in the ring frame (1); and the air blowing cylinder (2) introduces cold air flow into the icing wind tunnel to freeze liquid drops attached to the airplane model.
2. An aircraft icing risk monitoring method according to claim 1, characterized in that: a traction table (5) and a guide frame (6) are arranged below the support rod (4), and the support rod (4) is fixed on the traction table (5); the traction table (5) is slidably mounted on the guide frame (6), and a driving oil cylinder (51) is arranged between the traction table (5) and the end part of the guide frame (6).
3. An aircraft icing risk monitoring method according to claim 2, characterized in that: the side part of the guide frame (6) is also provided with paired roller wheels (61), and the guide frame (6) is slidably arranged on the circumferential direction of the ring frame (1); the roller wheel (61) is clamped on the surface of the ring frame (1), a driving servo motor is installed at the end part of the roller wheel (61), and the roller wheel (61) drives the guide frame (6) to change the position of the guide frame on the ring frame (1).
4. An aircraft icing risk monitoring method according to claim 2, characterized in that: a lifting rod (45) is further arranged in the supporting rod (4), and a bump (411) is further arranged on the top ball (41) above the lifting rod (45); the convex block (411) is parallel to the axial direction of the ring frame (1), and the convex block (411) is attached and installed in a concave pit (431) arranged in the ball opening (43).
5. An aircraft icing risk monitoring method according to claim 4, characterized in that: a contact sheet (421) is arranged on the contact surface of the bump (411) and the pit (431); the airplane model is provided with electric heating sheets (7), and the electric heating sheets (7) are positioned at the slat and flap parts of the airplane model; the controller adjusts the running state of the electric heating sheet (7) through the electric connection between the contact sheets (421).
6. An aircraft icing risk monitoring method according to claim 5, characterized in that: the engine part of the airplane model is also provided with a return air groove (8), and the return air groove (8) is protruded on the circumferential direction of the inner wall of the engine; the inner wall of the engine is also provided with a surrounding electric heating wire (9), and the electric heating wire (9) keeps a constant heating state; the return duct (8) directs the airflow entering the interior of the engine through a duct into the wing and out along the jet of the engine.
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