CN111392066A - Helicopter rotor model icing wind tunnel test method - Google Patents
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Abstract
The invention discloses a helicopter rotor model icing wind tunnel test method, which belongs to the technical field of wind tunnel tests and mainly utilizes an icing wind tunnel system to realize icing effect and is combined with a helicopter rotor test platform to measure the aerodynamic performance of a helicopter rotor; the invention is based on a large-scale icing wind tunnel and a helicopter rotor wind tunnel test platform, and provides a helicopter rotor model icing characteristic test method in advance, so that the helicopter rotor wind tunnel test process is standardized, and a wind tunnel test task can be safely and reliably carried out with high quality and high efficiency; the method can conveniently and accurately evaluate the influence of icing on the aerodynamic performance of the helicopter rotor model, and can provide powerful wind tunnel test data for developing the research on the icing problem of the helicopter rotor in China.
Description
Technical Field
The invention relates to a wind tunnel test method for icing of a helicopter rotor model, and belongs to the technical field of wind tunnel tests.
Background
The helicopter is a special aircraft which can effectively complete the flight motions of hovering, vertical landing and landing, forward flying, backward flying, lateral flying and the like by means of the rotation of a rotor wing to provide lift force, advancing force and operating force. When the helicopter flies to a certain height in the air and passes through an icing cloud layer, moving or non-moving parts exposed outside the helicopter body are likely to be iced, wherein the icing of the rotor wing is more sensitive, and the vibration caused by the asymmetrical shedding of the icing on the rotor wing blades and the great increase of the torque of the main rotor wing in a short icing time seriously affect the safe flight of the helicopter. Therefore, in order to realize the capability of the helicopter for flying all day long, one of the main factors influencing the flight safety, namely the influence of the icing of the components such as the rotor wing of the helicopter on the performance, needs to be solved.
According to the requirement of helicopter icing flight envelope specification, flight test under the real icing meteorological condition is the most ideal research means, but the actual flight test has large risk, long time consumption and high cost, and the required test condition cannot be quickly searched under the natural condition, so that the method is limited in application. The experiment research carried out in the icing wind tunnel can provide a safe and controllable flight simulation environment, provide high-quality data for theoretical analysis, and has relatively low cost. Therefore, the wind tunnel test is the most important means for carrying out the research on the icing performance of the helicopter rotor at present, the research on the wind tunnel test for carrying out the icing of the helicopter rotor model is carried out, a large amount of test data is obtained, the development of the rotor icing theory and the test technology can be promoted, and the development of an anti-icing and deicing system of the helicopter model can be promoted.
The helicopter rotor model test carried out in the icing wind tunnel must follow certain similarity criteria, and the complete similarity criteria include: the flow fields around the dry and frozen surfaces are similar; the action of the paddle on the pneumatic force is similar; the momentum of the liquid water drops is similar; the energy balance where freezing occurs is similar to the force that produces ice shedding. It is generally impossible to be completely similar, but in icing tunnels, liquid water content, average water droplet diameter and icing time are important similar parameters and need to be converted according to similar criteria.
The helicopter rotor icing test research is still in the starting stage in China, and the test research in the aspect is not effectively developed. Under the high-speed rotation state of the rotor wing, how to safely and effectively develop the research on the icing characteristic of the rotor wing, and to find out the icing mechanism of the rotor wing is of great importance to the research on the icing problem of helicopters in China and the progress of key technologies such as ice prevention/removal and the like. In recent years, a large icing wind tunnel is built in China and operated for production, and meanwhile, a helicopter rotor wind tunnel test platform is developed in a matching way, so that equipment basic conditions are provided for the research of helicopter icing and anti/deicing tests independently developed in China. Therefore, a reliable rotor model icing characteristic test method is researched based on large icing wind tunnel and helicopter rotor wind tunnel test platforms, and the method is the key for further improving the helicopter icing test technical system in China.
Disclosure of Invention
The invention aims to: aiming at the existing problems, the icing wind tunnel test method for the helicopter rotor model is provided, the icing test process of the helicopter rotor model is standardized, and the wind tunnel test task can be developed safely and reliably with high quality and high efficiency.
The technical scheme adopted by the invention is as follows:
a helicopter rotor model icing wind tunnel test method comprises the following steps:
step 1, debugging each system of a rotor model test bed before completing a test, and executing step 2 after each system works normally;
step 2, acquiring a zero reading as an initial reading when the inclination angle of the rotor shaft is zero, and executing step 3 if the initial reading is correct;
step 3, starting the rotor wing to safely operate, then starting a wind tunnel refrigerating system, driving the wind tunnel, cooling by adjusting the wind speed, wherein the rotor wing is operated in real time in the cooling process to enable the lift force, the pitching moment and the rolling moment of the rotor wing to be always kept within a safe range, and after the ambient temperature of the wind tunnel is reduced to a test value and stabilized, executing the step 4;
and 4, increasing the rotating speed of the rotor wing to the test rotating speed, then adjusting the wind speed to the test wind speed, and in the process of adjusting the wind speed, the rotor wing needs to be operated in real time, so that the lift force, the pitching moment and the rolling moment of the rotor wing are always kept within a safe range. After the wind speed is adjusted to a test value and stabilized, executing the step 5;
step 5, controlling a rotor wing control system and a main shaft tilting system in real time, carrying out a rotor wing forward flight balancing test, balancing the load of the rotor wing to a test value, and executing step 6 after the load of the rotor wing is balanced to the test value and is stable;
step 6, collecting rotor performance data in a non-icing environment, processing and outputting results, and executing step 7 after collecting according to required time;
and 7, setting the air pressure of the wind tunnel spray rake water, the water air temperature, the nozzle density and the spraying time, starting a wind tunnel spraying system, collecting rotor performance data in an icing environment, processing and outputting a result, and stopping collection until spraying is finished. After the data acquisition is finished, executing the step 8;
step 8, stopping the wind tunnel, and simultaneously operating the rotor wing to enable the lift force, the pitching moment and the rolling moment of the rotor wing to be always kept within a safe range, and executing step 9 when the wind speed is less than 10 m/s;
step 9, controlling the rotor wing control system and the main shaft tilting system to return to zero, stopping the rotor wing test stand, and executing step 10 after the wind tunnel and the rotor wing are completely stopped;
and step 10, shooting a model ice accumulation picture in a test section, and recording and measuring the ice shape condition.
Further, the debugging in step 1 is: the method comprises the following steps of elimination of ground resonance of a rotor model and a test bed system, inspection of hub motion coordination capability, calibration of a rotor control system, inspection of dynamic balance of the rotor model, inspection and adjustment of common conicity of the rotor model.
Further, in the step 3, when the rotor total pitch is 2 degrees and the longitudinal and transverse cyclic pitch variation is 0 degree, the rotor is started to safely operate at the target rotating speed.
Further, the target rotor speed is not higher than 500 rpm.
Further, in step 5, the vertical force of the rotor wing is adjusted to the test value, and the pitching moment and the rolling moment of the hub are kept to be zero.
Further, in the step 3, the wind speed for cooling is not lower than 35 m/s.
Further, the safety early warning system is further included so as to monitor the vibration condition of the test bed in real time, and under the icing condition, the vibration quantity is ensured to be within a safety range, so that emergency stop can be realized under the dangerous condition.
Further, in the step 8, the wind tunnel is stopped, and the pitch and the roll of the rotor wing are controlled to be within 20 Nm.
Further, when step 7 is implemented, the rotor model adopts a control mode of 'trim state' to acquire the influence trend of icing on the performance of the rotor.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
the helicopter rotor model icing wind tunnel test method is based on a large icing wind tunnel and a helicopter rotor wind tunnel test platform, firstly provides a helicopter rotor model icing characteristic test method, standardizes the helicopter rotor wind tunnel test process, and can develop wind tunnel test tasks with high quality, high efficiency, safety and reliability; the problem of how to ensure the safe operation of the rotor model due to the long time in the wind tunnel cooling process is solved; the control mode and the data acquisition and analysis method of the helicopter rotor model in the icing state are established, the influence of icing on the aerodynamic performance of the helicopter rotor model can be conveniently and accurately evaluated, and powerful wind tunnel test data can be provided for developing the research on the icing problem of the helicopter rotor in China.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic flow diagram of the present invention.
FIG. 2 is a schematic structural diagram of a wind tunnel test system.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
Examples
A helicopter rotor model icing wind tunnel test method is shown in figures 1 and 2 and comprises the following steps:
step 1, debugging each system of a rotor model test bed before completing a test, and executing step 2 after each system works normally;
step 2, acquiring a zero reading as an initial reading when the inclination angle of the rotor shaft is zero, and executing step 3 if the initial reading is correct;
step 3, starting the rotor wing to safely operate, then starting a wind tunnel refrigerating system, driving the wind tunnel, cooling by adjusting the wind speed, wherein the rotor wing is operated in real time in the cooling process to enable the lift force, the pitching moment and the rolling moment of the rotor wing to be always kept within a safe range, and after the ambient temperature of the wind tunnel is reduced to a test value and stabilized, executing the step 4;
and 4, increasing the rotating speed of the rotor wing to the test rotating speed, then adjusting the wind speed to the test wind speed, and in the process of adjusting the wind speed, the rotor wing needs to be operated in real time, so that the lift force, the pitching moment and the rolling moment of the rotor wing are always kept within a safe range. After the wind speed is adjusted to a test value and stabilized, executing the step 5;
step 5, controlling a rotor wing control system and a main shaft tilting system in real time, carrying out a rotor wing forward flight balancing test, balancing the load of the rotor wing to a test value, and executing step 6 after the load of the rotor wing is balanced to the test value and is stable;
step 6, collecting rotor performance data in a non-icing environment, processing and outputting results, and executing step 7 after collecting according to required time;
and 7, setting the air pressure of the wind tunnel spray rake water, the water air temperature, the nozzle density and the spraying time, starting a wind tunnel spraying system, collecting rotor performance data in an icing environment, processing and outputting a result, and stopping collection until spraying is finished. After the data acquisition is finished, executing the step 8;
8, stopping the wind tunnel, simultaneously operating the longitudinal and transverse periodic variable distances of the rotor wing, and executing the step 9 when the wind speed is less than 10 m/s;
step 9, controlling the rotor wing control system and the main shaft tilting system to return to zero, stopping the rotor wing test stand, and executing step 10 after the wind tunnel and the rotor wing are completely stopped;
and step 10, shooting a model ice accumulation picture in a test section, and recording and measuring the ice shape condition.
In this embodiment, the initial state and the related data before and after icing can be effectively obtained through the steps, in the actual test process, the normal operation of the system can be realized through the initial reading respectively, meanwhile, the safety of the system can be effectively guaranteed, then, the related parameters in the icing environment can be effectively obtained through the data acquisition before and after icing, and the effective test data can also effectively guarantee the safety of the helicopter rotor model through the test method, further research on the helicopter rotor icing test in China can also be promoted, and the promotion of the research capability of the helicopter rotor icing test in China can be promoted.
Secondly, at present, large icing wind tunnels and helicopter rotor wind tunnel test platforms belong to developed systems, according to the fact that open documents CN201911041914.1 and CN201911041931.5 are both designed for the large icing wind tunnels, and the helicopter rotor icing wind tunnel test platforms are combined, the problem that the aerodynamic performance of a helicopter rotor model can be effectively researched in an icing environment can be solved by using the test method in the embodiment.
As a further specific design, the debugging in step 1 is: the method comprises the following steps of elimination of ground resonance of a rotor model and a test bed system, inspection of hub motion coordination capability, calibration of a rotor control system, inspection of dynamic balance of the rotor model, inspection and adjustment of common conicity of the rotor model. In a normal helicopter rotor wind tunnel test, in order to ensure the safe operation of the whole system, the inspection before the test is necessary, and is particularly important for the situations.
Based on the above specific design, as more specific, in step 3, when the rotor total pitch is 2 ° and the pitch variation in the longitudinal and transverse directions is 0 °, the rotor is started to safely operate at the target rotation speed. In the design, the rotor total pitch is 2 degrees, and the longitudinal and transverse periodic variable pitch is 0 degree, which is a safe initial state in the test process.
A more specific description is given of the above-mentioned target rotational speed, which is the rotational speed of the helicopter rotor, and more specifically, the target rotational speed is the helicopter rotor rotational speed not exceeding 500 rpm.
As a more specific description, the test values of the test rotational speed and the test wind speed set for the test requirements are set according to different test conditions of the test requirements, for example, the test is performed on the condition that the rotational speed of the helicopter rotor is 1800 rpm and the wind speed is 50m/s, and then the test rotational speed and the wind speed are set according to the specific values.
As a more specific design, based on the above specific embodiment, in step 5, the rotor vertical force is adjusted to the test value while keeping the hub pitch moment and the hub roll moment to be zero. In the design, the vertical force of the rotor wing is a set value before the test, and the specific value of the set value is set according to different rotor wings, the size of the set value is set by relevant parameters of a rotor wing model, and the main purpose of the set value is to be more closely to the real simulation of the helicopter. And the design of keeping the pitch moment and the roll moment of the hub to be zero is an ideal value, and in actual operation, the values of the pitch moment and the roll moment of the hub are usually kept to be close to zero, so that a better test effect is realized.
In the description of step 3, the wind speed is used to adjust the temperature to achieve the cooling effect, and in order to ensure the cooling effect, generally, in step 3, the wind speed for cooling is not lower than 35 m/s. In actual operation, the wind speed may be designed to be 35-60 m/s.
According to more specific design, in order to guarantee the operation safety of the system and the monitoring in the whole operation process, the whole test system further comprises a safety early warning system so as to monitor the vibration condition of the test bed in real time, and under the icing working condition, the vibration quantity is ensured to be within a safety range, so that emergency stop can be realized under the dangerous condition. Based on the data acquisition and processing of the whole system, the relevant key parameters of the system are monitored, and once the safety warning value is exceeded, the early warning system is started, so that the system can be stopped and an alarm signal can be sent out.
As a further design, specifically, in step 8, the wind tunnel is stopped, and the pitch of the rotor wing in the longitudinal direction and the transverse direction is controlled, so that the pitch moment and the roll moment of the hub are kept within 20 Nm.
As a further description, in steps 3 and 4, the rotor is operated in real time to keep the lift, pitch moment and roll moment of the rotor within safe ranges, which is a practical illustration, for example, in the case of the maximum design value of the lift of the rotor being 1000N, the lift of the rotor is usually 200N and 500N is a better choice, and the pitch moment and roll moment are usually within 20 Nm. At this time, 1/4-1/2, which is the maximum value (target value) for maintaining the lift of the rotor, is the preferred choice.
Specifically, in the above parameter collection, the test state parameters include an ambient temperature, a liquid water content, a water droplet diameter, an icing time, a wind tunnel wind speed, a rotor rotation speed, a rotor total pitch, a rotor cyclic pitch, a rotor shaft inclination angle, an advancing ratio, a rotor tension, a rotor torque, and the like.
In the icing time, the data acquisition also has certain requirements, namely: in icing time, rotor performance data are collected according to a certain sampling frequency, performance data are output once every several circles of rotation (the number of circles is determined according to test requirements), and the output data are average values in the process of several circles of rotation, so that time history data of rotor performance are obtained.
As a more specific design, when step 7 is implemented, the rotor model adopts a control mode of 'trim state' to acquire the influence trend of icing on the performance of the rotor. As a specific description, the control mode of the rotor model using the "trim state" is that the control mode is to lock the rotor operation parameters when the system does not start icing, and to obtain the influence trend of the whole icing process on the performance of the rotor in the control mode.
After the required wind tunnel test results are obtained, the following method is adopted to analyze the influence of icing on the aerodynamic performance of the helicopter rotor model.
a. Comparing and analyzing the variation trend of the vertical force of the rotor wing before and after icing;
b. comparing and analyzing the variation trend of the rotor torque before and after icing;
as specific description, collecting test parameters of vertical force and torque of the rotor wing before and after icing;
c. the influence trend of icing on the vertical force of the rotor wing during temperature change is contrastingly analyzed;
d. the influence trend of icing on the torque of the rotor wing when the temperature changes is contrastingly analyzed;
as a specific description, the temperature change is a test parameter for collecting the vertical force and the torque of the rotor wing when the given temperature values are different in the test;
e. the influence trend of icing on the vertical force of the rotor wing when the liquid water content changes is contrastingly analyzed;
f. the influence trend of icing on the torque of the rotor wing when the liquid water content changes is contrastingly analyzed;
specifically, the liquid water content changes to test parameters of collecting the vertical force and the torque of the rotor wing when the liquid water content values set in the test are different;
g. the influence trend of icing on the vertical force of the rotor wing when the diameter of the water drops changes is contrastingly analyzed;
h. the influence trend of icing on the torque of the rotor wing when the diameter of the water drops is changed is contrastingly analyzed;
specifically, the diameter change of the water drops is a test parameter for collecting the vertical force and the torque of the rotor wing when the diameter values of the water drops set in the test are different;
i. the influence trend of icing on the vertical force of the rotor wing when different pneumatic parameters (such as wind speed, advancing ratio, tension coefficient and the like) are changed is contrastively analyzed;
j. the influence trend of icing on the torque of the rotor wing when different pneumatic parameters (such as wind speed, advancing ratio, tension coefficient and the like) are changed is contrastively analyzed;
as a specific description, aerodynamic parameter change is a test parameter that a vertical force and a torque of a rotor wing are acquired when a test set aerodynamic parameter value is different;
k. and further research and analysis are carried out on the method by combining the obtained rotor ice-shaped two-dimensional profile and the appearance characteristics of the three-dimensional structure.
In conclusion, the helicopter rotor model icing wind tunnel test method is based on a large-scale icing wind tunnel and a helicopter rotor wind tunnel test platform, firstly provides a helicopter rotor model icing characteristic test method, enables the helicopter rotor wind tunnel test flow to be standardized, and can develop wind tunnel test tasks with high quality, high efficiency, safety and reliability; the problem of ensuring the safe operation of a rotor model in the long-time cooling process of the wind tunnel is solved; the control mode and the data acquisition and analysis method of the helicopter rotor model in the icing state are established, the influence of icing on the aerodynamic performance of the helicopter rotor model can be conveniently and accurately evaluated, and powerful wind tunnel test data can be provided for developing the research on the icing problem of the helicopter rotor in China.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (9)
1. A helicopter rotor model icing wind tunnel test method is characterized in that: the method comprises the following steps:
step 1, debugging each system of a rotor model test bed before completing a test, and executing step 2 after each system works normally;
step 2, acquiring a zero reading as an initial reading when the inclination angle of the rotor shaft is zero, and executing step 3 if the initial reading is correct;
step 3, starting the rotor wing to safely operate, then starting a wind tunnel refrigerating system, driving the wind tunnel, cooling by adjusting the wind speed, wherein the rotor wing is operated in real time in the cooling process to enable the lift force, the pitching moment and the rolling moment of the rotor wing to be always kept within a safe range, and after the ambient temperature of the wind tunnel is reduced to a test value and stabilized, executing the step 4;
step 4, the rotating speed of the rotor wing is increased to a test rotating speed, then the wind speed is adjusted to the test wind speed, the rotor wing needs to be operated in real time in the process of adjusting the wind speed, so that the lift force, the pitching moment and the rolling moment of the rotor wing are always kept within a safe range, and the step 5 is executed after the wind speed is adjusted to a test value and is stable;
step 5, controlling a rotor wing control system and a main shaft tilting system in real time, carrying out a rotor wing forward flight balancing test, balancing the load of the rotor wing to a test value, and executing step 6 after the load of the rotor wing is balanced to the test value and is stable;
step 6, collecting rotor performance data in a non-icing environment, processing and outputting results, and executing step 7 after collecting according to required time;
step 7, setting the air pressure, water temperature, nozzle density and spraying time of the wind tunnel spray rake, starting a wind tunnel spraying system, collecting rotor performance data in an icing environment, processing and outputting a result until spraying is finished, stopping collecting,
after the data acquisition is finished, executing the step 8;
step 8, stopping the wind tunnel, and simultaneously operating the rotor wing to enable the lift force, the pitching moment and the rolling moment of the rotor wing to be always kept within a safe range, and executing step 9 when the wind speed is less than 10 m/s;
step 9, controlling the rotor wing control system and the main shaft tilting system to return to zero, stopping the rotor wing test stand, and executing step 10 after the wind tunnel and the rotor wing are completely stopped;
and step 10, shooting a model ice accumulation picture in a test section, and recording and measuring the ice shape condition.
2. The helicopter rotor model icing wind tunnel test method according to claim 1, characterized by comprising: the debugging in the step 1 is as follows: the method comprises the following steps of elimination of ground resonance of a rotor model and a test bed system, inspection of hub motion coordination capability, calibration of a rotor control system, inspection of dynamic balance of the rotor model, inspection and adjustment of common conicity of the rotor model.
3. The helicopter rotor model icing wind tunnel test method according to claim 1, characterized by comprising: and in the step 3, when the rotor wing total pitch is 2 degrees and the longitudinal and transverse periodic variable pitch is 0 degree, the rotor wing is started to safely operate at the target rotating speed.
4. The helicopter rotor model icing wind tunnel test method according to claim 3, characterized by comprising: the rotor target speed is not higher than 500 rpm.
5. The helicopter rotor model icing wind tunnel test method according to claim 1, characterized by comprising: in step 5, the vertical force of the rotor wing is adjusted to a test value, and the pitching moment and the rolling moment of the hub are kept to be zero.
6. The helicopter rotor model icing wind tunnel test method according to claim 1, characterized by comprising: in the step 3, the wind speed for cooling is not lower than 35 m/s.
7. The helicopter rotor model icing wind tunnel test method according to claim 1, characterized by comprising: the safety early warning system is further included so as to monitor the vibration condition of the test bed in real time, and under the icing condition, the vibration quantity is ensured to be within a safety range, so that emergency stop can be realized under the dangerous condition.
8. The helicopter rotor model icing wind tunnel test method according to claim 1, characterized by comprising: and 8, stopping the wind tunnel, and simultaneously operating the longitudinal and transverse cyclic variable distances of the rotor wing to keep the pitch moment and the roll moment of the hub within 20 Nm.
9. The helicopter rotor model icing wind tunnel test method according to claim 1, characterized by comprising: in step 7, the rotor model adopts a control mode of 'trim state' to acquire the influence trend of icing on the performance of the rotor.
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