CN110963046A - Method for determining icing condition of unmanned aerial vehicle airfoil - Google Patents
Method for determining icing condition of unmanned aerial vehicle airfoil Download PDFInfo
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- CN110963046A CN110963046A CN201911337755.XA CN201911337755A CN110963046A CN 110963046 A CN110963046 A CN 110963046A CN 201911337755 A CN201911337755 A CN 201911337755A CN 110963046 A CN110963046 A CN 110963046A
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- 238000000034 method Methods 0.000 title claims abstract description 24
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 25
- 238000005094 computer simulation Methods 0.000 claims description 2
- 238000004364 calculation method Methods 0.000 description 7
- 239000007788 liquid Substances 0.000 description 7
- 238000004088 simulation Methods 0.000 description 3
- 230000009194 climbing Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000010187 selection method Methods 0.000 description 1
- 238000006467 substitution reaction 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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Abstract
The application provides a method for determining an icing condition of an airfoil of an unmanned aerial vehicle, the method comprising: determining the flight condition of the unmanned aerial vehicle: separating a flight task section under an icing condition according to flight sections used by the unmanned aerial vehicle for carrying out different tasks in flight, dispersing the flight sections into flight sections with different lengths, and determining the possible flight time and distance of the unmanned aerial vehicle in an icing area within the maximum vertical height range and the maximum horizontal range of a cloud layer; determining critical icing conditions: acquiring a series of different icing parameters for a certain fixed flight condition of the unmanned aerial vehicle according to the corresponding relation among various specified flight conditions, and determining the critical icing condition of the unmanned aerial vehicle; determining flight state parameters: according to different flight conditions, under the selected critical icing conditions, the combination is different, and the flight parameters are associated with the determined critical icing conditions so as to determine the flight parameters under the critical icing conditions.
Description
Technical Field
The application belongs to the technical field of aerospace, and particularly relates to a method for determining an icing condition of an unmanned aerial vehicle airfoil.
Background
Along with the development of society, unmanned aerial vehicle's frequency of use is higher and higher, uses the scene more and more abundant, and the natural environment that unmanned aerial vehicle faces also is more and more complicated, and what wherein will face very likely is that unmanned aerial vehicle crosses supercooled water cloud layer, and causes unmanned aerial vehicle airfoil to produce the phenomenon of icing. The airfoil can produce great influence to unmanned aerial vehicle's aerodynamic performance after freezing to influence unmanned aerial vehicle's safety in utilization.
However, no method specially selected for the icing condition of the unmanned aerial vehicle airfoil exists in the prior art.
Disclosure of Invention
It is an object of the present application to provide a method of determining icing conditions for an unmanned aerial vehicle airfoil to address or mitigate at least one of the problems of the background art.
In one aspect, the technical solution provided by the present application is: a method of determining an icing condition for an airfoil of a drone, the method comprising:
determining the flight condition of the unmanned aerial vehicle: separating a flight task section under an icing condition according to flight sections used by the unmanned aerial vehicle for carrying out different tasks in flight, dispersing the flight sections into flight sections with different lengths, and determining the possible flight time and distance of the unmanned aerial vehicle in an icing area within the maximum vertical height range and the maximum horizontal range of a cloud layer;
determining critical icing conditions: acquiring a series of different icing parameters for a certain fixed flight condition of the unmanned aerial vehicle according to the corresponding relation among various specified flight conditions, and determining the critical icing condition of the unmanned aerial vehicle;
determining flight state parameters: according to different flight conditions, under the selected critical icing conditions, the combination is different, and the flight parameters are associated with the determined critical icing conditions so as to determine the flight parameters under the critical icing conditions.
In the present application, the icing condition is an air pressure altitude of 6.7km or less.
In this application, the flight condition of the unmanned aerial vehicle takes the average height, the average speed and the average angle of attack within the flight segment as the flight condition.
In this application, icing parameters include temperature, water content, water droplet diameter.
In the application, the obtained icing parameters can be obtained through calculation simulation or wind tunnel tests.
In the present application, the flight parameters include flight speed, flight altitude and flight angle of attack.
In another aspect, the present application provides a technical solution that: a drone having an airfoil, the icing condition of the airfoil being determined according to the method as set out in any one of the preceding claims.
The method of the application uses the section to analyze completely to unmanned aerial vehicle's task, and the gained flight leg is the real flight leg of unmanned aerial vehicle, and the analysis is closer to the practical use, can provide a feasible method for the selection of unmanned aerial vehicle icing condition.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of a method for determining an icing condition for an airfoil of an UAV according to the present application.
Fig. 2 is a flight profile of an unmanned aerial vehicle according to an embodiment of the present application.
FIG. 3 is a graph of the relationship between the continuous maximum lower liquid water content and the average effective water droplet diameter in the examples of the present application.
FIG. 4 is a graph of continuous maximum ambient temperature versus barometric height for an embodiment of the present application.
FIG. 5 shows the relationship between the continuous maximum lower liquid water content and the horizontal distance between clouds in the present example.
FIG. 6 is a graph of liquid water content versus average effective water droplet diameter at maximum discontinuity in an example of the present application.
FIG. 7 is a graph of ambient temperature versus barometric height at discontinuous maximum in an embodiment of the present application.
FIG. 8 is a graph of the liquid water content coefficient versus the cloud level range for the discontinuous maximum in the examples of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The main purpose of this application provides the selection method of a critical icing condition for unmanned aerial vehicle airfoil for unmanned aerial vehicle carries out icing analysis, aerodynamic analysis and flight safety analysis etc..
Icing conditions are selected according to the icing meteorological conditions (according to relevant contents of China civil aviation regulations) of flight profiles used by the unmanned aerial vehicle for executing different tasks, and the flight icing working conditions and the critical icing conditions of the unmanned aerial vehicle are respectively synthesized according to three types of icing conditions of continuous maximum icing, discontinuous maximum icing and maximum takeoff icing.
Wherein, the maximum takeoff icing condition is specified in detail in the relevant content of the Chinese civil aviation regulation, and the simulation calculation is carried out according to the specification. The present application is primarily directed to continuous maximum icing and intermittent maximum icing analysis.
Therefore, as shown in fig. 1, the method for determining the icing condition of the airfoil of the unmanned aerial vehicle provided by the application comprises the following steps:
s1, analyzing flight conditions: separating a flight task section under an icing condition according to flight sections used by the unmanned aerial vehicle for carrying out different tasks in flight, dispersing the flight sections into flight sections with different lengths, and determining the possible flight time and distance of the unmanned aerial vehicle in an icing area within the maximum vertical height range and the maximum horizontal range of the cloud layer. Due to the limitation of the conventional icing and wind tunnel test calculation, the average height, the average speed and the average attack angle in the flight segment can be selected and calculated as flight conditions in the application.
Herein, the icing condition refers to an air pressure altitude of 6.7km or less.
S2, determining a critical icing condition: for a certain fixed flight condition of the unmanned aerial vehicle, a series of different icing parameters are obtained according to the corresponding relation among various conditions specified in China civil aviation regulations, and the critical icing condition of the unmanned aerial vehicle is determined.
It should be noted that a certain fixed flight condition only defines the flight angle of attack, the flight altitude and the flight speed, and the flight distance is selected according to different conversion coefficients specified in the "civil aviation regulations of China".
In the present application, the series of different icing parameters may be obtained by computational simulation or wind tunnel tests.
In addition, the above icing parameters include temperature, water content, water droplet diameter, and the like.
S3, determining flight state parameters: according to different flight conditions, different flight parameters are combined under the selected critical icing condition, the flight parameters are introduced into the determined critical icing condition for relevant selection, and finally the flight parameters under the critical icing condition are determined.
It should be noted that, if the calculation and wind tunnel test capabilities are stronger, the selection of the critical icing condition and the determination of the flight state parameter should be considered and selected together.
In the present application, the flight parameters include flight speed, flight angle of attack, flight altitude, and the like.
An exemplary unmanned flight profile is illustrated in fig. 2. Assuming that the climbing rate of the airplane is a fixed value, the fixed value in the embodiment is 10 m/s; the horizontal component of the flying speed is uniform acceleration movement, and the speed is 400km/h from the altitude of 0m during takeoff, the speed of 200km/h during climbing to the altitude of 10km, and the cruising speed is 400 km/h; the gliding stage and the takeoff stage are just opposite, the speed is 400km/h when the altitude is 10km, the horizontal speed is reduced at a constant speed, and the speed is 200km/h when the altitude is 0 m. Meanwhile, the unmanned aerial vehicle is assumed to fly linearly and does not fly in a hovering mode at a certain position. A flight profile in which the flight pressure altitude is less than 6.7km, i.e., the portion below the dotted line in fig. 2, is extracted. Because the flight profile is symmetrical front and back, only the takeoff climb phase is analyzed, and the glide phase is similar to the climb phase and is not described in detail. 670s are needed for flying from the ground to the altitude of 6.7 km. The horizontal flying distance was 49.69 km.
As shown in fig. 3 to 8, the continuous maximum icing is analyzed first, the maximum vertical height is 1.98km according to fig. 3, and the maximum horizontal range is 310 nautical miles (574.12km) according to fig. 5, and it can be seen that the maximum range of the unmanned aerial vehicle in the icing area does not exceed the continuous maximum icing horizontal range. The flying distance in the cloud layer is limited by the maximum cloud layer height, the longest flying time in the cloud layer is 198s, and the maximum flying distance in the cloud layer is 62.2km (33.59 nautical miles) within 198s below 6.7km from the altitude of 4.72km to 6.7km, namely, the minimum water drop correction coefficient is 0.79 according to the graph shown in FIG. 5, so the water drop correction coefficient ranges from 0.79 to 1.34. According to the figure 4, the temperature range selectable at the altitude of 6.7km is-20 ℃ and below, the corresponding relation between the water content and the average effective diameter of the water drops can be selected from the figure 3, different water contents are selected, and then the average effective diameter of the water drops is determined. If the altitude range varies, the possible temperatures can be selected according to fig. 4, and different liquid water contents can be selected to determine the average effective water droplet diameter. A series of combinations are formed, the density degree of the combinations can be selected according to the calculation capacity, icing calculation simulation or icing test is completed to find out critical icing conditions, wherein icing time is related to a water content correction coefficient, and different horizontal flight distance ranges correspond to different liquid water content correction coefficients and flight time. Or the temperature and altitude relationship may be eliminated for simplicity of calculation, combining different liquid water contents, average effective water droplet diameter and horizontal flight distance.
The method of the application uses the section to analyze completely to unmanned aerial vehicle's task, and the gained flight leg is the real flight leg of unmanned aerial vehicle, and the analysis is closer to the practical use, can provide a feasible method for the selection of unmanned aerial vehicle icing condition.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A method of determining an icing condition for an airfoil of an unmanned aerial vehicle, the method comprising:
determining the flight condition of the unmanned aerial vehicle: separating a flight task section under an icing condition according to flight sections used by the unmanned aerial vehicle for carrying out different tasks in flight, dispersing the flight sections into flight sections with different lengths, and determining the possible flight time and distance of the unmanned aerial vehicle in an icing area within the maximum vertical height range and the maximum horizontal range of a cloud layer;
determining critical icing conditions: acquiring a series of different icing parameters for a certain fixed flight condition of the unmanned aerial vehicle according to the corresponding relation among various specified flight conditions, and determining the critical icing condition of the unmanned aerial vehicle;
determining flight state parameters: according to different flight conditions, under the selected critical icing conditions, the combination is different, and the flight parameters are associated with the determined critical icing conditions so as to determine the flight parameters under the critical icing conditions.
2. The method of determining an icing condition for an unmanned aerial vehicle airfoil of claim 1, wherein the icing condition is an air pressure altitude of less than 6.7 km.
3. The method of determining drone airfoil icing conditions of claim 1, wherein the drone's flight conditions have as flight conditions an average altitude, an average speed, and an average angle of attack within the flight segment.
4. The method of determining UAV airfoil icing conditions of claim 1, wherein the icing parameters include temperature, water content, water droplet diameter.
5. The method for determining icing conditions for an unmanned aerial vehicle airfoil of claim 3, wherein the obtained icing parameters are obtained by computational simulation or wind tunnel testing.
6. The method of determining UAV airfoil icing conditions of claim 1, wherein the flight parameters comprise flight speed, flight altitude, and flight angle of attack.
7. A drone, characterized in that it has an airfoil whose icing conditions are determined according to the method of any one of claims 1 to 6.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117093953A (en) * | 2023-10-20 | 2023-11-21 | 成都流体动力创新中心 | A method and system for rapid correction and prediction of aircraft icing based on the fusion of multiple meteorological elements |
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