CN109335015B - Pneumatic load processing method based on nacelle body structure design - Google Patents
Pneumatic load processing method based on nacelle body structure design Download PDFInfo
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- CN109335015B CN109335015B CN201811437128.9A CN201811437128A CN109335015B CN 109335015 B CN109335015 B CN 109335015B CN 201811437128 A CN201811437128 A CN 201811437128A CN 109335015 B CN109335015 B CN 109335015B
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- 238000003672 processing method Methods 0.000 title claims abstract description 10
- 238000000034 method Methods 0.000 claims description 11
- 230000003068 static effect Effects 0.000 abstract description 4
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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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- 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
- B64D47/00—Equipment not otherwise provided for
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Abstract
The application discloses a pneumatic load processing method based on nacelle body structure design, which comprises the following steps: judging whether the load peak point of the pneumatic load under different working conditions is greater than a first preset peak value or not; judging whether the structures of the cabin body at the load peak point which is larger than the first preset peak value in the pneumatic loads under different working conditions are continuous or not; flattening load peak points which are larger than the first preset peak value in the pneumatic loads under different working conditions; judging whether the load peak point of the pneumatic load under different working conditions is smaller than a second preset peak value or not; and performing linear straightening treatment on the load peak point smaller than the second preset peak value in the pneumatic loads under different working conditions. The pneumatic load processing method based on the nacelle body structural design can obtain a pneumatic distribution load more convenient for the nacelle body structural design, can simplify the determination and implementation of a static scheme, and further can greatly shorten the development period of the nacelle structure.
Description
Technical Field
The application belongs to the field of airplane structure design, and particularly relates to a pneumatic load processing method based on nacelle body structure design.
Background
The aircraft external hanging nacelle bears pneumatic loads in three directions, the pneumatic load distribution in each direction is complex, the structural strength design of a cabin body is inconvenient, and a static test scheme is difficult to determine and implement.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a pneumatic load handling method based on a nacelle body structure design.
The application discloses a pneumatic load processing method based on nacelle body structure design, which comprises the following steps:
step one, judging whether the load peak point of the pneumatic load under different working conditions is larger than a first preset peak value or not, and if so, performing step two;
step two, judging whether the cabin structures at the load peak points which are larger than the first preset peak value in the pneumatic loads under different working conditions are continuous, and if so, performing step three;
thirdly, flattening load peak points which are larger than the first preset peak value in the pneumatic loads under different working conditions;
step four, judging whether the load peak point of the pneumatic load under different working conditions is smaller than a second preset peak value, and if so, performing step five;
and fifthly, linearly straightening load peak points smaller than the second preset peak value in the pneumatic loads under different working conditions.
According to at least one embodiment of the application, in the third step, the planarization treatment is performed based on two load forms of pneumatic suction and pneumatic pressure.
According to at least one embodiment of the present application, in the fifth step, the linear straightening process is performed based on two load forms of pneumatic suction and pneumatic pressure.
According to at least one embodiment of the present application, the method for treating the pneumatic load based on the structural design of the nacelle body further comprises:
and step six, carrying out deformation calculation on the structure of the cabin body through the pneumatic loads under different working conditions obtained in the step five, and checking whether the rigidity index requirement of the cabin body is met.
The application has at least the following beneficial technical effects:
the pneumatic load processing method based on the nacelle body structural design can obtain a pneumatic distribution load more convenient for the nacelle body structural design, can simplify the determination and implementation of a static scheme, and further can greatly shorten the development period of the nacelle structure.
Drawings
FIG. 1 is a diagram illustrating a pod raw aerodynamic load distribution in one embodiment of the aerodynamic load handling method of the present application;
FIG. 2 is a simplified distribution of aerodynamic loads of a nacelle according to an embodiment of the method of aerodynamic load handling 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 pneumatic load handling method based on the structural design of the nacelle body according to the present invention will be described in further detail with reference to fig. 1 to 2.
The application discloses a pneumatic load processing method based on nacelle body structure design, which comprises the following steps:
step one, judging whether the load peak point of the aerodynamic load under different working conditions (namely different flight states) is larger than a first preset peak value or not, and if so, performing step two;
step two, judging whether the cabin structure at the load peak point which is larger than the first preset peak value in the pneumatic loads under different working conditions is continuous (in order to judge whether the load after the leveling treatment can be borne), and if so, performing step three;
thirdly, carrying out flattening treatment on load peak points which are larger than the first preset peak value in the pneumatic loads under different working conditions (ensuring that the load of a flattening treatment area is the same as that before treatment);
step four, judging whether the load peak point of the pneumatic load under different working conditions is smaller than a second preset peak value, and if so, performing step five;
and fifthly, linearly straightening load peak points smaller than the second preset peak value in the pneumatic loads under different working conditions.
Further, in the third step, the flattening treatment is carried out based on two load modes of pneumatic suction and pneumatic pressure; similarly, in step five, the linear straightening treatment is carried out based on two load forms of pneumatic suction and pneumatic pressure.
Further, the pneumatic load handling method based on the nacelle body structural design further includes:
and step six, carrying out deformation calculation on the cabin structure through the pneumatic loads under different working conditions obtained in the step five, and checking whether the cabin rigidity index requirement is met (the requirement is not met, and the first preset peak value is adjusted in a returning mode).
The following will further describe the pneumatic load handling method based on the structural design of the nacelle body according to the present application, taking a nacelle as an example, in combination with the above steps.
Step one, judging whether the load peak point of the pneumatic load under different working conditions is larger than a first preset peak value or not;
wherein, a certain pod has pneumatic distributed loads of 5 working conditions, and the pneumatic loads at the 2 frames of the cabin body are respectively 500N/mm, 300N/mm, 200N/mm, 100N/mm and 1500N/mm in the 5 working condition loads; under the load working condition 5, the pneumatic load at the frame axis of the cabin body 2 is greater than the preset peak value of 1000N/mm.
Step two, judging whether the cabin structure at the load peak point which is larger than the first preset peak value in the pneumatic loads under different working conditions is continuous or not);
the 2 frames of the cabin body are of a continuous structure, and the wallboard and the stringer are relatively strong in size and can bear the load after leveling treatment.
Thirdly, flattening load peak points which are larger than a first preset peak value in the pneumatic loads under different working conditions;
and carrying out load leveling treatment on areas 300mm before and after the 2-frame axis navigation. Under the principle of ensuring that the load of the flattening processing area is the same as that before the processing, the load value after the flattening processing is calculated to be 950N/mm, namely the load values of the areas 300mm before and after the 2-frame axis navigation are the same and are both 950N/mm.
Judging whether the load peak point of the pneumatic load under different working conditions is smaller than a second preset peak value or not;
under 5 working conditions, the load is smaller from the cabin tip to the position 300mm before the 2-frame axis, the maximum peak points are respectively 20N/mm, 40N/mm, 30N/mm, 50N/mm and 35N/mm, and are smaller than the preset peak value of 200N/mm.
And fifthly, linearly straightening load peak points smaller than a second preset peak value in the pneumatic loads under different working conditions.
And (3) linearly straightening the load from the cabin tip to the position 300mm before the 2-frame axial line flight, wherein the linear distribution after treatment can envelop the original distribution. The starting end of the straight line is the cabin tip before the flight, and the load value is 0; the end of the straight line is 300mm before the 2-frame axis flight, and the load is 950N/mm.
The pneumatic load processing method based on the nacelle body structural design can obtain a pneumatic distribution load more convenient for the nacelle body structural design, can simplify the determination and implementation of a static scheme, and further can greatly shorten the development period of the nacelle structure.
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 (4)
1. A pneumatic load processing method based on nacelle body structure design is characterized by comprising the following steps:
step one, judging whether the load peak point of the pneumatic load under different working conditions is larger than a first preset peak value or not, and if so, performing step two;
step two, judging whether the structures of the nacelle body at the load peak points which are larger than the first preset peak value in the pneumatic loads under different working conditions are continuous, and if so, performing step three;
thirdly, flattening load peak points which are larger than the first preset peak value in the pneumatic loads under different working conditions;
step four, judging whether the load peak point of the pneumatic load under different working conditions is smaller than a second preset peak value, and if so, performing step five;
and fifthly, linearly straightening load peak points smaller than the second preset peak value in the pneumatic loads under different working conditions.
2. The pneumatic load handling method based on the structural design of the nacelle body as claimed in claim 1, wherein in the third step, the flattening treatment is performed based on two load modes of pneumatic suction and pneumatic pressure.
3. The pneumatic load handling method based on the structural design of the nacelle body as claimed in claim 1, wherein in the step five, the linear straightening treatment is performed based on two load modes of pneumatic suction and pneumatic pressure.
4. The method for aerodynamic load handling based on structural design of a nacelle body of claim 1, further comprising:
and step six, carrying out deformation calculation on the nacelle body structure of the nacelle through the pneumatic loads under different working conditions obtained in the step five, and checking whether the requirements of the stiffness indexes of the nacelle body are met.
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| CN201811437128.9A CN109335015B (en) | 2018-11-28 | 2018-11-28 | Pneumatic load processing method based on nacelle body structure design |
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| CN201811437128.9A CN109335015B (en) | 2018-11-28 | 2018-11-28 | Pneumatic load processing method based on nacelle body structure design |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105447249A (en) * | 2015-11-25 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Static test load calculation method for engine nacelle structure |
| CN106156444A (en) * | 2016-07-27 | 2016-11-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft aerodynamic loading processing method and strength of aircraft computational methods |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2356788B1 (en) * | 2007-12-18 | 2012-02-22 | Airbus Operations, S.L. | METHOD AND SYSTEM FOR A QUICK CALCULATION OF AERODYNAMIC FORCES IN AN AIRCRAFT. |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105447249A (en) * | 2015-11-25 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Static test load calculation method for engine nacelle structure |
| CN106156444A (en) * | 2016-07-27 | 2016-11-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft aerodynamic loading processing method and strength of aircraft computational methods |
Non-Patent Citations (1)
| Title |
|---|
| "气动载荷处理方法研究";裴金利;《科技创新与应用》;20151231(第26期);正文第44页 * |
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