CN112498737A - Fatigue test method for light airplane - Google Patents
Fatigue test method for light airplane Download PDFInfo
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- CN112498737A CN112498737A CN202011432758.4A CN202011432758A CN112498737A CN 112498737 A CN112498737 A CN 112498737A CN 202011432758 A CN202011432758 A CN 202011432758A CN 112498737 A CN112498737 A CN 112498737A
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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
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The application belongs to the field of airplane fatigue strength, and particularly relates to a light airplane fatigue test method. The method comprises the following steps: step one, acquiring a task section of a light airplane; dividing each task profile into a plurality of different flight phases; acquiring maneuvering load data of the light aircraft in different flight phases and equivalent gust load data of the light aircraft; step four, superposing the maneuvering load data of the light aircraft and equivalent gust load data to obtain a flight load spectrum of the light aircraft; and fifthly, carrying out fatigue test on the light airplane according to the flight load spectrum. The fatigue test method for the light aircraft can solve the problem of compiling the flight load spectrum of the light aircraft, not only contains maneuvering flight loads, but also considers the influence of gust loads, and reflects the actual load history of the light aircraft relatively truly, so that the fatigue test for the light aircraft is realized.
Description
Technical Field
The application belongs to the field of airplane fatigue strength, and particularly relates to a light airplane fatigue test method.
Background
The service life of the aircraft structure is determined according to the full-scale structure fatigue test result, so that the fatigue load spectrum applied to the structure is important when the full-scale fatigue test is carried out. The fatigue load spectrum should be as close as possible to the true operating conditions of the aircraft during service. However, the actual operating conditions vary due to the randomness of the fatigue loads, and the actual loads have to be simplified to a "load spectrum" representative of the real situation due to the constraints of the loading equipment conditions or to the compression test time. Therefore, compiling an appropriate load spectrum that simulates the actual use of an aircraft is the first task in the fatigue design of the aircraft structure or the life assessment of existing aircraft models, and has a significant impact on success or failure, cost, workload and time of subsequent analysis and testing operations.
The use mode of the light airplane is different from that of the fighter plane and the transport plane, the load spectrums of the fighter plane and the transport plane have corresponding descriptions in the durability and damage tolerance specifications, and the light airplane load spectrum has no specification for reference. The light airplane needs to perform certain maneuvering actions when executing certain tactical tasks, and the maneuvering overload is smaller than that of a fighter plane and larger than that of a transporter. Meanwhile, the light airplane is influenced by gust load, the selection of the gust speed and the cycle number exceeds the selection range of the discrete gust equivalent load spectrum, and the gust speed and the cycle number of the light airplane need to be calculated again. The light airplane is subjected to the dual effects of airframe load and gust load at the same time, and how the two loads are superposed is not specified.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a light airplane fatigue test method to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
a fatigue test method for a light airplane comprises the following steps:
step one, acquiring a task section of a light airplane;
dividing each task profile into a plurality of different flight phases;
acquiring maneuvering load data of the light aircraft in different flight phases and equivalent gust load data of the light aircraft;
step four, superposing the maneuvering load data of the light aircraft and equivalent gust load data to obtain a flight load spectrum of the light aircraft;
and fifthly, carrying out fatigue test on the light airplane according to the flight load spectrum.
Optionally, in step one, the mission profile includes scout, assault, air defense, trick and ground.
Optionally, the flight phases of the assault profile include departure, climbing, cruising, gliding, assault, climbing, gliding, and approach in sequence.
Optionally, in step three, the acquiring maneuvering load data of the light aircraft in different flight phases includes:
acquiring an overload curve of a similar machine type when a corresponding task is executed;
and converting the overload of the similar airplane type into the overload of the light airplane according to a regularization method to obtain an overload curve of the light airplane.
Optionally, an operation formula in the regularization method is as follows:
wherein the content of the first and second substances,
in order to overload the light aircraft in real time,
in order to maximize the overload of the light aircraft,
in order to overload the similar models in real time,
the maximum overload for similar models.
The invention has at least the following beneficial technical effects:
the fatigue test method for the light aircraft can solve the problem of compiling the flight load spectrum of the light aircraft, not only contains maneuvering flight loads, but also considers the influence of gust loads, and reflects the actual load history of the light aircraft relatively truly, so that the fatigue test for the light aircraft is realized.
Drawings
FIG. 1 is a flow chart of a method for fatigue testing a lightweight aircraft according to one embodiment of the present application;
FIG. 2 is a graphical representation of a maneuver overload curve of a fatigue test method for a lightweight aircraft according to one embodiment of the present application;
FIG. 3 is a schematic diagram illustrating a gust load and a maneuver load superimposed on a fatigue test method for a lightweight aircraft according to an embodiment 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. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 3.
The application provides a light airplane fatigue test method, which comprises the following steps:
s001, acquiring a mission profile of the light airplane;
s002, dividing each task section into a plurality of different flight stages;
s003, acquiring maneuvering load data of the light aircraft in different flight phases and equivalent gust load data of the light aircraft;
s004, superposing maneuvering load data of the light airplane and equivalent gust load data to obtain a flight load spectrum of the light airplane;
and S005, carrying out a fatigue test on the light airplane according to the flight load spectrum.
In one embodiment of the application, the task names of the light aircraft are determined according to different using modes of the light aircraft in different environments, and the proportion of different task sections is determined. In this embodiment, the mission profile may include reconnaissance, assault, air defense, stunt, and ground, see table 1.
TABLE 1
Secondly, dividing each task section into a plurality of different flight phases according to parameters such as height, speed, flight distance, attack angle, overload range and the like of each task in different flight phases. In the present embodiment, the light aircraft assault profile flight phase is divided as shown in table 2.
TABLE 2
And then acquiring maneuvering load data of the light aircraft in different flight phases and equivalent gust load data of the light aircraft.
In one embodiment of the present application, acquiring maneuvering load data of a light aircraft at different flight phases comprises:
acquiring an overload curve of a similar machine type when a corresponding task is executed;
and converting the overload of the similar airplane type into the overload of the light airplane according to a regularization method to obtain an overload curve of the light airplane.
According to the light aircraft fatigue test method, the maneuvering overload curves of the light aircraft are selected from overload curves of similar aircraft types executing corresponding tasks, due to the fact that the maximum overload of the two aircraft types is different, the regularization operation formula is used, the overload of the similar aircraft types is converted into the light aircraft overload according to the regularization method, the light aircraft overload-time history curve is finally obtained, and different flight stages are marked in the curve, as shown in fig. 2.
In this embodiment, the operation formula in the regularization method is:
wherein the content of the first and second substances,
in order to overload the light aircraft in real time,
in order to maximize the overload of the light aircraft,
in order to overload the similar models in real time,
the maximum overload for similar models.
In this embodiment, the calculation of the real-time overload value of the light aircraft is shown in table 3.
TABLE 3
According to the light aircraft fatigue test method, the light aircraft gust overload refers to the overload spectrum compiling explanation of each flight phase in the civil aircraft structure durability and damage tolerance design manual, and the equivalent gust load and the cycle number of different flight phases are found out by combining the characteristics of different flight phases of each task of light flight. And if the height and the flight distance in the mission segment exceed the ranges in the manual, fitting the equivalent gust load corresponding to the light aircraft flying in the phase by adopting a Lagrange algorithm. In this embodiment, the calculation results of the gust load of the light aircraft during each flight phase of the assault mission are shown in table 4.
TABLE 4
Further, based on the maneuvering load data of each task, the gust load obtained at each flight phase of each task section is superposed with the maneuvering load to obtain a final flight load spectrum of the light airplane, as shown in fig. 3. And finally, carrying out fatigue test on the light airplane according to the flight load spectrum.
The light aircraft fatigue test method has the advantages that the light aircraft flight load spectrum compilation process is simple and convenient, the calculation efficiency is high, the problem of light aircraft flight load spectrum compilation can be solved, the maneuvering flight load is included, the influence of gust load is considered, the actual load process of the light aircraft is reflected really, and the compilation of the light aircraft flight load spectrum can lay a foundation for the fatigue calculation analysis of the aircraft. The method can simulate the real use condition of the airplane, is simple and convenient to use, saves test time and saves expenses.
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 (5)
1. A fatigue test method for a light airplane is characterized by comprising the following steps:
step one, acquiring a task section of a light airplane;
dividing each task profile into a plurality of different flight phases;
acquiring maneuvering load data of the light aircraft in different flight phases and equivalent gust load data of the light aircraft;
step four, superposing the maneuvering load data of the light aircraft and equivalent gust load data to obtain a flight load spectrum of the light aircraft;
and fifthly, carrying out fatigue test on the light airplane according to the flight load spectrum.
2. The fatigue test method for light aircraft according to claim 1, wherein in the first step, the mission profile comprises scout, assault, air defense, stunt, and ground.
3. The method for fatigue testing of light aircraft according to claim 2, wherein the flight phases of the assault profile include departure, climb, cruise, glide, assault, climb, glide and approach in that order.
4. The light aircraft fatigue test method of claim 1, wherein in step three, the obtaining maneuvering load data of the light aircraft in different flight phases comprises:
acquiring an overload curve of a similar machine type when a corresponding task is executed;
and converting the overload of the similar airplane type into the overload of the light airplane according to a regularization method to obtain an overload curve of the light airplane.
5. The light aircraft fatigue test method of claim 4, wherein the operational formula in the regularization method is:
wherein the content of the first and second substances,
in order to overload the light aircraft in real time,
in order to maximize the overload of the light aircraft,
in order to overload the similar models in real time,
the maximum overload for similar models.
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| CN202011432758.4A CN112498737A (en) | 2020-12-09 | 2020-12-09 | Fatigue test method for light airplane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113435007A (en) * | 2021-05-27 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft wing fatigue damage determining and analyzing method and task scheduling method thereof |
| CN113704880A (en) * | 2021-08-07 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Static and vibration combined loading fatigue spectrum compiling method |
| WO2024021369A1 (en) * | 2022-07-28 | 2024-02-01 | 四川航天烽火伺服控制技术有限公司 | Load-spectrum-based test method, apparatus and device, and medium |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6125333A (en) * | 1997-11-06 | 2000-09-26 | Northrop Grumman Corporation | Building block approach for fatigue spectra generation |
| KR101318860B1 (en) * | 2012-04-20 | 2013-10-17 | 한국항공우주산업 주식회사 | Method of fatigue evaluation for helicopter composite blade |
| CN104679933A (en) * | 2014-07-30 | 2015-06-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane fatigue load designing method |
| CN107521721A (en) * | 2017-07-20 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test fuselage course load designing load method |
| CN109592074A (en) * | 2018-11-05 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of determination method of aircraft structure fatigue test loading frequency |
| EP3578945A1 (en) * | 2018-06-09 | 2019-12-11 | Bell Helicopter Textron Inc. | Method of fatigue testing a complex structure |
-
2020
- 2020-12-09 CN CN202011432758.4A patent/CN112498737A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6125333A (en) * | 1997-11-06 | 2000-09-26 | Northrop Grumman Corporation | Building block approach for fatigue spectra generation |
| KR101318860B1 (en) * | 2012-04-20 | 2013-10-17 | 한국항공우주산업 주식회사 | Method of fatigue evaluation for helicopter composite blade |
| CN104679933A (en) * | 2014-07-30 | 2015-06-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane fatigue load designing method |
| CN107521721A (en) * | 2017-07-20 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full scale fatigue test fuselage course load designing load method |
| EP3578945A1 (en) * | 2018-06-09 | 2019-12-11 | Bell Helicopter Textron Inc. | Method of fatigue testing a complex structure |
| CN109592074A (en) * | 2018-11-05 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of determination method of aircraft structure fatigue test loading frequency |
Non-Patent Citations (1)
| Title |
|---|
| 陈亮等: "无人作战机载荷谱编制方法", 飞机设计, vol. 38, no. 2, pages 37 - 40 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113435007A (en) * | 2021-05-27 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft wing fatigue damage determining and analyzing method and task scheduling method thereof |
| CN113435007B (en) * | 2021-05-27 | 2024-02-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining and analyzing fatigue damage of aircraft wing and task scheduling method thereof |
| CN113704880A (en) * | 2021-08-07 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Static and vibration combined loading fatigue spectrum compiling method |
| CN113704880B (en) * | 2021-08-07 | 2023-12-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue spectrum compiling method for static and vibration combined loading |
| WO2024021369A1 (en) * | 2022-07-28 | 2024-02-01 | 四川航天烽火伺服控制技术有限公司 | Load-spectrum-based test method, apparatus and device, and medium |
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