CN112591135A - Aircraft static test load loading method - Google Patents
Aircraft static test load loading method Download PDFInfo
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- CN112591135A CN112591135A CN202011209359.1A CN202011209359A CN112591135A CN 112591135 A CN112591135 A CN 112591135A CN 202011209359 A CN202011209359 A CN 202011209359A CN 112591135 A CN112591135 A CN 112591135A
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- 238000012360 testing method Methods 0.000 title claims abstract description 39
- 238000011068 loading method Methods 0.000 title claims abstract description 37
- 230000003068 static effect Effects 0.000 title claims abstract description 32
- 238000000034 method Methods 0.000 claims abstract description 25
- 238000005452 bending Methods 0.000 claims abstract description 15
- 238000013461 design Methods 0.000 abstract description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
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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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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The application belongs to the field of loading design of static test loads of airplanes, and particularly relates to a loading method of static test loads of airplanes, which comprises the following steps: applying a concentrated load on the aircraft; applying course balancing load on the airplane to balance the course of the airplane, and applying vertical balancing load to make the bending moment of the examined part on the airplane reach a preset value. According to the method, concentrated load is applied to the airplane, namely the loaded state of the airplane bearing the concentrated load is simulated, a static test of the airplane bearing the concentrated load is carried out, course balancing load is applied to the airplane to balance the course of the airplane, vertical balancing load is applied to the airplane to enable the bending moment of the check part on the airplane to reach a preset value, effective application of the load of the check part on the airplane can be achieved, and the check part on the airplane is checked.
Description
Technical Field
The application belongs to the field of loading design of static test loads of airplanes, and particularly relates to a loading method of static test loads of airplanes.
Background
In the process of aircraft development, an aircraft static load test is required to be carried out, and parts with complex loading conditions and stress on the aircraft are examined.
The airplane can bear larger concentrated loads under certain conditions, for example, when the airplane takes off in an ejection mode and lands in a blocking mode, the airplane represents the most serious loaded state, a static test is carried out under the state, and the examination of the concentrated load bearing structure is of great significance.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present patent application.
Disclosure of Invention
The present application seeks to provide a method of loading an aerostatic test load that overcomes or mitigates at least one of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
an aircraft static test load loading method comprises the following steps:
applying a concentrated load on the aircraft;
applying course balancing load on the airplane to balance the course of the airplane, and applying vertical balancing load to make the bending moment of the examined part on the airplane reach a preset value.
According to at least one embodiment of the application, in the above-mentioned method for loading the static test load of the airplane,
the concentrated load is the concentrated load of the catapult takeoff of the airplane.
According to at least one embodiment of the application, in the above-mentioned method for loading the static test load of the airplane,
the concentrated load is the concentrated load of the landing block of the airplane.
According to at least one embodiment of the application, in the above-mentioned method for loading the static test load of the airplane,
the method comprises the following steps of applying course balancing load on the airplane to balance the course of the airplane, applying vertical balancing load to enable the bending moment of an examined part on the airplane to reach a preset value, and specifically comprises the following steps:
the method comprises the steps of applying course balancing load to a plurality of components with larger bearing capacity on the airplane to balance the course of the airplane, and applying vertical balancing load to enable the bending moment of an examined part on the airplane to reach a preset value.
According to at least one embodiment of the application, in the above-mentioned method for loading the static test load of the airplane,
the parts with larger bearing capacity comprise an engine and an oil tank.
According to at least one embodiment of the application, in the above-mentioned method for loading the static test load of the airplane,
the parts with larger bearing capacity comprise a wing mounting joint, a main landing gear mounting joint and an engine mounting structure.
According to at least one embodiment of the application, in the above-mentioned method for loading the static test load of the airplane,
the assessment site includes a concentrated load bearing structure.
The application has at least the following beneficial technical effects:
the method is designed for applying concentrated load on the airplane, namely simulating the loaded state of the concentrated load borne by the airplane, carrying out static test under the concentrated load borne by the airplane, applying course balancing load on the airplane to balance the courses of the airplane, and applying vertical balancing load on the airplane to enable the bending moment of an examined part on the airplane to reach a preset value, so that the effective application of the load on the examined part on the airplane can be realized, and the examined part on the airplane can be examined.
Drawings
FIG. 1 is a flow chart of an aircraft static test load loading method provided by an embodiment of the application;
fig. 2 is a schematic view of loading by an aircraft static test load loading method provided in an embodiment of the present application.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate 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 when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
An aircraft static test load loading method comprises the following steps:
applying a concentrated load on the aircraft;
applying course balancing load on the airplane to balance the course of the airplane, and applying vertical balancing load to make the bending moment of the examined part on the airplane reach a preset value.
For the method for loading the static test load of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the method is designed to apply the concentrated load F to the airplane, i.e., simulate the loaded state of the concentrated load borne by the airplane, perform the static test under the concentrated load borne by the airplane, apply the course balancing load to the airplane to balance the courses of the airplane, and apply the vertical balancing load to the airplane to make the bending moment of the examined part on the airplane reach a predetermined value, so that the effective application of the load of the examined part on the airplane can be realized, and the examined part on the airplane can be examined.
In some optional embodiments, in the above method for loading an aerostatic test load, the concentrated load is an aircraft catapult-assisted take-off concentrated load.
In some optional embodiments, in the above method for loading an aircraft static test load, the concentrated load is an aircraft landing arrest concentrated load.
In some optional embodiments, in the above method for loading a static test load of an aircraft, the applying a heading balancing load to the aircraft to balance the heading of the aircraft and the applying a vertical balancing load to make the bending moment of an examined part on the aircraft reach a predetermined value specifically includes:
the method comprises the steps of applying heading balancing loads Fx1, Fx2, Fx3 and Fx4 to a plurality of components with large bearing capacity on the airplane to balance the heading of the airplane, and applying vertical balancing loads Fy1 and Fy2 to enable the bending moment of an examined part on the airplane to reach a preset value.
For the method for loading the static test load of the aircraft disclosed in the above embodiment, it can be understood by those skilled in the art that the method is designed on a plurality of components with larger bearing capacity on the aircraft, and applies the course trim load and the vertical trim load, that is, the course trim load and the vertical trim load are dispersed and applied on the plurality of components with larger bearing capacity on the aircraft, so that the problem that the aircraft structure is damaged due to overlarge local stress caused by applying the course trim load and the vertical trim load on a single point on the aircraft can be avoided.
For the loading method for the static test load of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the bending moment of the examined part on the airplane can accurately reach the predetermined value by finely adjusting the course trim load and the vertical trim load on each part with a large bearing capacity, and the predetermined value can be specifically determined by the relevant technical personnel according to the examination requirement when the application is applied, so that the loading method is convenient and flexible.
For the loading method for the static test load of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the course trim load and the vertical trim load on each component with a large bearing capacity are adjusted to make the bending moment of the examined part on the airplane accurately reach a predetermined value, and the bearing of the non-examined part on the airplane should not exceed a limit value.
In some optional embodiments, in the above method for loading the static test load of the aircraft, the component with a relatively high load bearing capacity includes a component with a relatively high concentrated mass on the aircraft, such as an engine, a fuel tank, and the like.
In some optional embodiments, in the above method for loading an aerostatic test load, the component with a relatively high load bearing capacity includes a component which is tested and verified to be capable of bearing a relatively high load on an aircraft, such as a wing mounting joint, a main landing gear mounting joint, an engine mounting structure, and the like.
In some optional embodiments, in the above method for loading the static test load of the aircraft, the assessment site includes a concentrated load bearing structure.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (7)
1. An aircraft static test load loading method is characterized by comprising the following steps:
applying a concentrated load on the aircraft;
applying course balancing load on the airplane to balance the course of the airplane, and applying vertical balancing load to make the bending moment of the examined part on the airplane reach a preset value.
2. A static test load loading method as set forth in claim 1,
the concentrated load is the concentrated load of the catapult takeoff of the airplane.
3. A static test load loading method as set forth in claim 1,
the concentrated load is the concentrated load of the landing block of the airplane.
4. An aerostatic test load loading method according to claim 1,
the method comprises the following steps of applying course balancing load on the airplane to balance the course of the airplane, applying vertical balancing load to enable the bending moment of an examined part on the airplane to reach a preset value, and specifically comprises the following steps:
the method comprises the steps of applying course balancing load to a plurality of components with larger bearing capacity on the airplane to balance the course of the airplane, and applying vertical balancing load to enable the bending moment of an examined part on the airplane to reach a preset value.
5. An aerostatic test load loading method according to claim 4,
the parts with larger bearing capacity comprise an engine and an oil tank.
6. An aerostatic test load loading method according to claim 4,
the parts with larger bearing capacity comprise a wing mounting joint, a main landing gear mounting joint and an engine mounting structure.
7. An aerostatic test load loading method according to claim 1,
the assessment site includes a concentrated load bearing structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011209359.1A CN112591135A (en) | 2020-11-03 | 2020-11-03 | Aircraft static test load loading method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011209359.1A CN112591135A (en) | 2020-11-03 | 2020-11-03 | Aircraft static test load loading method |
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| CN112591135A true CN112591135A (en) | 2021-04-02 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113704878A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying landing gear load to aircraft structure full-aircraft finite element model |
| CN114735237A (en) * | 2022-06-14 | 2022-07-12 | 中国飞机强度研究所 | Structure and method for applying out-of-plane static force in impact test surface of airplane structural component |
| WO2023029148A1 (en) * | 2021-09-06 | 2023-03-09 | 北京空间机电研究所 | Height-adjustable spacecraft storage tank simulated loading static experiment device and method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113704878A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying landing gear load to aircraft structure full-aircraft finite element model |
| CN113704878B (en) * | 2021-08-05 | 2023-10-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying load of landing gear by using aircraft structure full-aircraft finite element model |
| WO2023029148A1 (en) * | 2021-09-06 | 2023-03-09 | 北京空间机电研究所 | Height-adjustable spacecraft storage tank simulated loading static experiment device and method |
| CN114735237A (en) * | 2022-06-14 | 2022-07-12 | 中国飞机强度研究所 | Structure and method for applying out-of-plane static force in impact test surface of airplane structural component |
| CN114735237B (en) * | 2022-06-14 | 2022-08-30 | 中国飞机强度研究所 | In-plane out-of-plane static force applying structure and method for impact test of airplane structural component |
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