CN113221240B - Method for compiling ground load spectrum of serial multi-strut landing gear - Google Patents
Method for compiling ground load spectrum of serial multi-strut landing gear Download PDFInfo
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- CN113221240B CN113221240B CN202110469287.2A CN202110469287A CN113221240B CN 113221240 B CN113221240 B CN 113221240B CN 202110469287 A CN202110469287 A CN 202110469287A CN 113221240 B CN113221240 B CN 113221240B
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- 238000001228 spectrum Methods 0.000 title claims abstract description 61
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- 238000004088 simulation Methods 0.000 claims description 18
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Abstract
The application belongs to the technical field of ground load spectrum programming of a tandem multi-strut landing gear, and particularly relates to a ground load spectrum programming method of the tandem multi-strut landing gear, which comprises the following steps: determining the distribution characteristics of fatigue loads of each aircraft mission section among each landing gear strut; determining the most serious landing gear support column in each landing gear support column, and taking the landing gear support column as a spectrum editing object; the maximum value of the spectrum load of each landing gear strut in each aircraft task section is applied to the landing gear strut as a spectrum editing object, so as to obtain a tandem multi-strut landing gear ground load spectrum.
Description
Technical Field
The application belongs to the technical field of ground load spectrum programming of a tandem multi-strut landing gear, and particularly relates to a ground load spectrum programming method of a tandem multi-strut landing gear.
Background
In the tandem type multi-strut landing gear of the aircraft, a plurality of landing gear struts are equidistantly arranged on a single-side main landing gear, all the landing gear struts have the same structure and are mutually independent, and the spectrum load of each landing gear strut is distributed statically at multiple points by adopting the aircraft with the tandem type multi-strut landing gear configuration.
At present, an aircraft adopting a tandem multi-strut landing gear configuration has the advantages that the distribution rule of the strut loads of each landing gear is determined by combining with load actual measurement data in the detailed design stage of the aircraft, so that the programming work of the ground load spectrum of the landing gear of the aircraft is difficult to develop in the design stage of an aircraft scheme, the fatigue design of the aircraft based on the design is delayed from the static strength design of the aircraft, multiple iterations are required in the later stage, the efficiency is low, and the design period of the aircraft is severely restricted.
The present application has been made in view of the above-described technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method of tandem multi-strut landing gear ground load spectrum preparation that overcomes or alleviates at least one of the known technical disadvantages.
The technical scheme of the application is as follows:
a method of compiling a ground load spectrum for a tandem multi-strut landing gear, comprising:
determining the distribution characteristics of fatigue loads of each aircraft mission section among each landing gear strut;
determining the most serious landing gear support column in each landing gear support column, and taking the landing gear support column as a spectrum editing object;
The maximum value of the spectrum load of each landing gear strut in each aircraft task section is applied to the landing gear strut as a spectrum editing object, so as to obtain a tandem multi-strut landing gear ground load spectrum.
According to at least one embodiment of the present application, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of fatigue loads of each aircraft mission section among the landing gear struts specifically includes:
analysis and summary of design experience for aircraft having similar landing gear configurations is made with reference to determining the distribution characteristics of fatigue loads for each aircraft mission section among each landing gear leg.
In accordance with at least one embodiment of the present application, in the method for compiling a ground load spectrum for a tandem multi-strut landing gear, the determining a distribution characteristic of fatigue loads of each aircraft mission section among landing gear struts includes:
Determining the distribution characteristics of fatigue loads of the ground taxi task section of the aircraft among the landing gear struts;
The distribution characteristics of the aircraft landing leg fatigue loads among the various landing gear struts are determined.
According to at least one embodiment of the present application, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of the fatigue load of the ground taxi task section of the aircraft among the landing gear struts specifically includes:
and constructing an aircraft simulation model, performing simulation analysis on the aircraft ground sliding task section, and determining the distribution characteristics of the fatigue load of the aircraft ground sliding task section among all landing gear struts.
According to at least one embodiment of the present application, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of the fatigue load of the landing task section of the aircraft among the landing gear struts specifically includes:
and constructing an aircraft simulation model, performing simulation analysis on the aircraft landing task section, and determining the distribution characteristics of the fatigue load of the aircraft landing task section among all landing gear struts.
According to at least one embodiment of the present application, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of the fatigue load of the landing task section of the aircraft among the landing gear struts specifically includes:
and (5) performing an aircraft landing gear ground drop test to determine the distribution characteristics of the fatigue load of the landing task section of the aircraft among the landing gear struts.
The application has at least the following beneficial technical effects:
According to the method, based on the distribution characteristic of fatigue loads of all aircraft task sections among all landing gear struts, the landing gear struts with the most serious bearing capacity are used as spectrum-editing objects, and the maximum value of the spectrum loads of all landing gear struts in all aircraft task sections is applied to the landing gear struts as the spectrum-editing objects, so that the serial multi-strut landing gear ground load spectrum which can be input in the fatigue design of the aircraft scheme design task section piece can be quickly obtained, the aircraft fatigue design can be synchronous with the aircraft static strength design, the later iteration times are reduced, the design efficiency is improved, and the development period of the aircraft is shortened.
Drawings
FIG. 1 is a flow chart of a method for compiling a ground load spectrum for a tandem multi-strut landing gear provided by an embodiment of the present application;
FIG. 2 is a schematic illustration of a tandem multi-strut landing gear arrangement;
FIG. 3 is a schematic illustration of a tandem multi-strut landing gear ground load spectrum builder provided by an embodiment of the present application;
FIG. 4 is a schematic illustration of an aircraft having a landing gear-like configuration provided by an embodiment of the present application;
FIG. 5 is a schematic illustration of constructing an aircraft simulation model provided by an embodiment of the present application;
FIG. 6 is a schematic diagram of the distribution characteristics of vertical and heading loads among the landing gear struts of an aircraft ground taxi mission segment based on a constructed aircraft simulation model provided by an embodiment of the present application;
FIG. 7 is a schematic illustration of the distribution characteristics of fatigue loads among various landing gear struts based on a constructed aircraft simulation model for simulation analysis of aircraft landing mission segments provided by an embodiment of the present application;
FIG. 8 is a ground load spectrum for landing gear struts at one landing provided by an embodiment of the present application.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; further, the drawings are for illustrative purposes, wherein the terms describing the positional relationship are limited to the illustrative description only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The application is described in further detail below with reference to fig. 1 to 8.
A method of compiling a ground load spectrum for a tandem multi-strut landing gear, comprising:
determining the distribution characteristics of fatigue loads of each aircraft mission section among each landing gear strut;
determining a maximum value of each landing gear strut spectral load in each aircraft mission section according to the fatigue load distribution characteristics;
determining the most serious landing gear support column in each landing gear support column, and taking the landing gear support column as a spectrum editing object;
The maximum value of the spectrum load of each landing gear strut in each aircraft task section is applied to the landing gear strut as a spectrum editing object, so as to obtain a tandem multi-strut landing gear ground load spectrum.
For the method for compiling the ground load spectrum of the tandem multi-strut landing gear disclosed in the above embodiment, it can be understood by those skilled in the art that, based on the distribution characteristic of fatigue load of each aircraft mission section among the landing gear struts, the landing gear struts with the most serious load are used as the spectrum compiling objects, and the maximum value of the spectrum load of each landing gear strut in each aircraft mission section is applied to the landing gear struts as the spectrum compiling objects, so that the ground load spectrum of the tandem multi-strut landing gear which can be used as the input of the fatigue design in the design stage of the aircraft scheme can be obtained rapidly, and the containment design is carried out based on the principles of enhancing maintainability, interchangeability and equal strength design of each strut, so that the fatigue design of the aircraft can be synchronized with the static strength design of the aircraft, the later iteration times can be reduced, the design efficiency can be improved, and the development period of the aircraft can be shortened.
In some alternative embodiments, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of fatigue loads of each aircraft task segment among the landing gear struts specifically includes:
analysis and summary of design experience for aircraft having similar landing gear configurations is made with reference to determining the distribution characteristics of fatigue loads for each aircraft mission section among each landing gear leg.
In some alternative embodiments, the method for compiling a ground load spectrum for a tandem multi-strut landing gear includes determining a distribution characteristic of fatigue loads of each aircraft mission section among each landing gear strut, including:
Determining the distribution characteristics of fatigue loads of the ground taxi task section of the aircraft among the landing gear struts;
The distribution characteristics of the aircraft landing leg fatigue loads among the various landing gear struts are determined.
In some alternative embodiments, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of the fatigue load of the ground taxi task section of the aircraft among the landing gear struts specifically includes:
and constructing an aircraft simulation model, performing simulation analysis on the aircraft ground sliding task section, and determining the distribution characteristics of the fatigue load of the aircraft ground sliding task section among all landing gear struts.
In some optional embodiments, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of the fatigue load of the landing task section of the aircraft among the landing gear struts specifically includes:
and constructing an aircraft simulation model, performing simulation analysis on the aircraft landing task section, and determining the distribution characteristics of the fatigue load of the aircraft landing task section among all landing gear struts.
In some optional embodiments, in the method for compiling a ground load spectrum of a tandem multi-strut landing gear, the determining the distribution characteristics of the fatigue load of the landing task section of the aircraft among the landing gear struts specifically includes:
and (5) performing an aircraft landing gear ground drop test to determine the distribution characteristics of the fatigue load of the landing task section of the aircraft among the landing gear struts.
The layout of a tandem multi-strut landing gear is shown in fig. 2, where n=2 in one particular embodiment, the ground load spectrum may be tailored according to the procedure shown in fig. 3, as follows:
determining the distribution characteristics of fatigue loads of each aircraft mission section among the landing gear struts, analyzing and summarizing design experience of an aircraft with a similar landing gear configuration as shown in fig. 4, and referring to determining the distribution characteristics of fatigue loads of each aircraft mission section among the landing gear struts; or alternatively
By constructing an aircraft simulation model, as shown in fig. 5, performing simulation analysis on an aircraft landing task section and a ground taxi task section, determining the distribution characteristics of fatigue loads of the aircraft landing task section and the ground taxi task section among landing gear struts, and obtaining the distribution characteristics of vertical and heading loads of the aircraft ground taxi task section among the landing gear struts as shown in fig. 6, and the distribution characteristics of fatigue loads of the aircraft landing task section among the landing gear struts as shown in fig. 7;
According to the design principle of the serial multi-strut landing gear, selecting the landing gear strut with the most serious bearing for carrying out containment design, and taking the selected landing gear strut as a spectrum editing object;
Based on the distribution characteristics of fatigue loads of each aircraft mission section among the landing gear struts, the maximum value of the spectrum loads of each aircraft landing gear strut in different aircraft mission sections is obtained, the maximum value of the spectrum loads of the aircraft mission sections is formed into a load spectrum, and the load spectrum is applied to the landing gear struts which are the spectrum editing objects, so that the ground load spectrum of the landing gear struts on one landing is obtained, as shown in fig. 8.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (6)
1. A method of compiling a ground load spectrum for a tandem multi-strut landing gear, comprising:
determining the distribution characteristics of fatigue loads of each aircraft mission section among each landing gear strut;
determining the most serious landing gear support column in each landing gear support column, and taking the landing gear support column as a spectrum editing object;
Applying the maximum value of the spectrum load of each landing gear strut in each aircraft task section to the landing gear strut as a spectrum editing object to obtain a ground load spectrum of the tandem multi-strut landing gear;
the determining of the distribution characteristics of fatigue loads of the various aircraft mission segments among the various landing gear struts comprises:
Determining the distribution characteristics of fatigue loads of the ground taxi task section of the aircraft among the landing gear struts;
The distribution characteristics of the aircraft landing leg fatigue loads among the various landing gear struts are determined.
2. The method of preparing a ground load spectrum for a tandem multi-strut landing gear according to claim 1,
The method for determining the distribution characteristics of the fatigue load of the ground taxi task section of the aircraft among the landing gear struts comprises the following specific steps:
Analysis and summary of design experience for aircraft having similar landing gear configurations is made with reference to determining the distribution characteristics of aircraft ground taxi mission section fatigue loads among the individual landing gear struts.
3. The method of preparing a ground load spectrum for a tandem multi-strut landing gear according to claim 2,
The method for determining the distribution characteristics of the fatigue load of the ground taxi task section of the aircraft among the landing gear struts comprises the following specific steps:
and constructing an aircraft simulation model, performing simulation analysis on the aircraft ground sliding task section, and determining the distribution characteristics of the fatigue load of the aircraft ground sliding task section among all landing gear struts.
4. The method of preparing a ground load spectrum for a tandem multi-strut landing gear according to claim 1,
The method for determining the distribution characteristics of the fatigue load of the landing task section of the aircraft among landing gear struts comprises the following specific steps:
analysis and summary of design experience for aircraft having similar landing gear configurations is made with reference to determining the distribution characteristics of aircraft landing gear leg fatigue loads among the individual landing gear struts.
5. The method of preparing a ground load spectrum for a tandem multi-strut landing gear according to claim 4,
The method for determining the distribution characteristics of the fatigue load of the landing task section of the aircraft among landing gear struts comprises the following specific steps:
and constructing an aircraft simulation model, performing simulation analysis on the aircraft landing task section, and determining the distribution characteristics of the fatigue load of the aircraft landing task section among all landing gear struts.
6. The method of preparing a ground load spectrum for a tandem multi-strut landing gear according to claim 4,
The method for determining the distribution characteristics of the fatigue load of the landing task section of the aircraft among landing gear struts comprises the following specific steps:
and (5) performing an aircraft landing gear ground drop test to determine the distribution characteristics of the fatigue load of the landing task section of the aircraft among the landing gear struts.
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| CN202110469287.2A CN113221240B (en) | 2021-04-28 | 2021-04-28 | Method for compiling ground load spectrum of serial multi-strut landing gear |
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| CN106197967A (en) * | 2016-06-28 | 2016-12-07 | 中国科学院金属研究所 | A kind of method of testing of large-scale moving load component fatigue behaviour |
| CN106777551A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter low cycle fatigue loading composes preparation method |
| KR101896457B1 (en) * | 2017-04-14 | 2018-09-10 | 한국항공우주산업 주식회사 | The method of generating operational loads spectrum based on actual operational flight data |
| CN110688708A (en) * | 2019-09-26 | 2020-01-14 | 中国航空工业集团公司西安飞机设计研究所 | Ground load spectrum compiling method based on multi-support undercarriage |
| CN110884684A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Design method for strength test of helicopter after impact of bearingless tail blade |
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2021
- 2021-04-28 CN CN202110469287.2A patent/CN113221240B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103324778A (en) * | 2013-01-05 | 2013-09-25 | 中国航空工业集团公司西安飞机设计研究所 | Ground load determination method of multi-fulcrum airplane |
| CN106197967A (en) * | 2016-06-28 | 2016-12-07 | 中国科学院金属研究所 | A kind of method of testing of large-scale moving load component fatigue behaviour |
| CN106777551A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of helicopter low cycle fatigue loading composes preparation method |
| KR101896457B1 (en) * | 2017-04-14 | 2018-09-10 | 한국항공우주산업 주식회사 | The method of generating operational loads spectrum based on actual operational flight data |
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| CN110884684A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Design method for strength test of helicopter after impact of bearingless tail blade |
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