CN105620783A - Method for arranging falling impact load resisting safety belt mooring connectors of high T-tail - Google Patents
Method for arranging falling impact load resisting safety belt mooring connectors of high T-tail Download PDFInfo
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- CN105620783A CN105620783A CN201410605560.XA CN201410605560A CN105620783A CN 105620783 A CN105620783 A CN 105620783A CN 201410605560 A CN201410605560 A CN 201410605560A CN 105620783 A CN105620783 A CN 105620783A
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Abstract
The invention discloses a method for arranging falling impact load resisting safety belt mooring connectors of a high T-tail. The method includes the following steps that A, falling impact loads borne by the connectors are accurately evaluated according to the arrangement of a wingspan and ribs of a horizontal tail structure in combination with an impulse load principle as well as Chinese national standards and mechanical properties related to a safety belt; B, the number of the connectors is reasonably set according to load data obtained in the step A; C, the effect that the safety belt is easily hung on the safety belt connectors is guaranteed according to the sizes of the safety belt connectors, the sizes of holes of the mooring connectors are reduced to the maximum degree, and the sectional dimensions of the connectors are reduced as much as possible so as to reduce the weight of the connectors; D, catia is used for modeling, and detail design such as connection, chamfering and rounding is considered; and E, PATRAN is used for building a finite element model and conducting optimization analysis. The safety belt mooring connector arrangement involved in the method can effectively improve the maintainability of an airplane, guarantee the life safety of maintenance personnel and prevent structural damage.
Description
Technical field
The invention belongs to aircraft structure strength and Supportability design field, particularly to the method that the anti-shock of a fall load insurance tie-down point of a kind of high T empennage is arranged.
Background technology
High T empennage due to horizontal tail top airfoil from ground up to about 15m, the span is about 17m, for preventing maintainer injures and deaths of falling from must arrange safety belt tie-down point, number too much can increase weight and affect aeroperformance and damaged structure, and number crosses that I haven't seen you for ages and cause safety belt, and long to cause impact load excessive. How reasonable Arrangement and design, domestic except the present invention at present, but without other high T empennages, and external relevant design also cannot find corresponding data at present.
Summary of the invention
The technical problem to be solved in the present invention is in that, the damage of the maintainability improving aircraft and the life security ensureing attendant and prevention structure.
There is provided a kind of high T empennage method that anti-shock of a fall load insurance tie-down point is arranged for solving the problems referred to above technical solution of the present invention, comprise the following steps:
The layout of the A span according to horizontal tail structure and rib, and in conjunction with shock loading principle and safety belt concerned countries standard and mechanical property, the shock of a fall load that accurate evaluation joint bears;
B reasonably arranges according to the number of the step A load data butt joint obtained;
C easily hangs up with guarantee insurance belt lacing according to the size of safety belt joint, reduces the bore size of tie-down point to greatest extent, and reduces contact cross-section size to reduce joint weight as far as possible;
D adopts catia to be modeled, it is considered to the detailed design such as connection, chamfering and rounding;
E adopts PATRAN carry out the foundation of FEM (finite element) model and be optimized analysis.
Preferably, also include after described step E:
F does not adopt circular cross-section for convenience of working joint suspension ring cross section;
G adopts the characteristic of composite according to attachment structure, selects high-quality TC4 titanium alloy with preventing galvanic corrosion.
Tie-down point is carried out rational deployment and layout by the present invention, the shock loading that scientifically assessment tie-down point bears, and according to shock loading reasonable selection high-quality TC4 titanium alloy to alleviate construction weight, for alleviating the impact that horizontal tail profile is pneumatic, according to safety belt joint installation dimension, force down the height of joint to greatest extent, and be connected with box section ribs root dovetail reinforcement district, analyze finally by optimizing, rationally determine the detailed design such as rounding. This joint design is simple, and processing technology is good, lightweight, and design considerations is strong, and in a word, design science is reasonable, and theoretical contact engineering is actual, easy to use and reliable.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, specific embodiments of the present invention are further described in detail, wherein:
Fig. 1 is the method flow diagram that the anti-shock of a fall load insurance tie-down point of high T empennage is arranged;
Fig. 2 is the method for optimizing flow chart that the anti-shock of a fall load insurance tie-down point of high T empennage is arranged.
Detailed description of the invention
Below in conjunction with embodiment, the inventive method is described in further detail.
This invention further investigation by impact loading intensity principle, and consult safety belt corresponding airline standard and national standard, tie-down point has been carried out rational deployment and layout, scientifically have evaluated the shock loading that tie-down point bears, and according to shock loading reasonable selection high-quality TC4 titanium alloy to alleviate construction weight, for alleviating the impact that horizontal tail profile is pneumatic, according to safety belt joint installation dimension, force down the height of joint to greatest extent, and be connected with box section ribs root dovetail reinforcement district, analyze finally by optimizing, rationally determine the detailed design such as rounding. this joint design is simple, and processing technology is good, lightweight, and design considerations is strong, and in a word, design science is reasonable, and theoretical contact engineering is actual, easy to use and reliable.
First embodiment of the invention provides a kind of high T empennage method that anti-shock of a fall load insurance tie-down point is arranged, comprises the following steps:
The layout of the A span according to horizontal tail structure and rib, and in conjunction with shock loading principle and safety belt concerned countries standard and mechanical property, the shock of a fall load that accurate evaluation joint bears;
B reasonably arranges according to the number of the step A load data butt joint obtained;
C easily hangs up with guarantee insurance belt lacing according to the size of safety belt joint, reduces the bore size of tie-down point to greatest extent, and reduces contact cross-section size to reduce joint weight as far as possible;
D adopts catia to be modeled, it is considered to the detailed design such as connection, chamfering and rounding;
E adopts PATRAN carry out the foundation of FEM (finite element) model and be optimized analysis.
Second embodiment of the invention provides a kind of preferred scheme, also includes after described step E:
F does not adopt circular cross-section for convenience of working joint suspension ring cross section;
G adopts the characteristic of composite according to attachment structure, selects high-quality TC4 titanium alloy with preventing galvanic corrosion.
Tie-down point is carried out rational deployment and layout by the present invention, the shock loading that scientifically assessment tie-down point bears, and according to shock loading reasonable selection high-quality TC4 titanium alloy to alleviate construction weight, for alleviating the impact that horizontal tail profile is pneumatic, according to safety belt joint installation dimension, force down the height of joint to greatest extent, and be connected with box section ribs root dovetail reinforcement district, analyze finally by optimizing, rationally determine the detailed design such as rounding. This joint design is simple, and processing technology is good, lightweight, and design considerations is strong, and in a word, design science is reasonable, and theoretical contact engineering is actual, easy to use and reliable.
Claims (2)
1. the method that the one kind high anti-shock of a fall load insurance tie-down point of T empennage is arranged, it is characterised in that comprise the following steps:
The layout of the A span according to horizontal tail structure and rib, and in conjunction with shock loading principle and safety belt concerned countries standard and mechanical property, the shock of a fall load that accurate evaluation joint bears;
B reasonably arranges according to the number of the step A load data butt joint obtained;
C easily hangs up with guarantee insurance belt lacing according to the size of safety belt joint, reduces the bore size of tie-down point to greatest extent, and reduces contact cross-section size to reduce joint weight as far as possible;
D adopts catia to be modeled, it is considered to the detailed design such as connection, chamfering and rounding;
E adopts PATRAN carry out the foundation of FEM (finite element) model and be optimized analysis.
2. method according to claim 1, it is characterised in that also include after described step E:
F does not adopt circular cross-section for convenience of working joint suspension ring cross section;
G adopts the characteristic of composite according to attachment structure, selects high-quality TC4 titanium alloy with preventing galvanic corrosion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410605560.XA CN105620783A (en) | 2014-10-31 | 2014-10-31 | Method for arranging falling impact load resisting safety belt mooring connectors of high T-tail |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410605560.XA CN105620783A (en) | 2014-10-31 | 2014-10-31 | Method for arranging falling impact load resisting safety belt mooring connectors of high T-tail |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620783A true CN105620783A (en) | 2016-06-01 |
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| CN201410605560.XA Pending CN105620783A (en) | 2014-10-31 | 2014-10-31 | Method for arranging falling impact load resisting safety belt mooring connectors of high T-tail |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173159A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Strength design method of tail structure |
| CN112417600A (en) * | 2020-11-20 | 2021-02-26 | 中国直升机设计研究所 | Method for rapidly calculating static strength of helicopter oil tank cabin |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005071261A1 (en) * | 2004-01-26 | 2005-08-04 | Vestas Wind Systems A/S | Methods of handling a wind turbine blade and system therefor |
| CN101287904A (en) * | 2005-09-21 | 2008-10-15 | Lm玻璃纤维有限公司 | Attachment devices on a wind turbine blade and a method of servicing utilizing these devices |
-
2014
- 2014-10-31 CN CN201410605560.XA patent/CN105620783A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005071261A1 (en) * | 2004-01-26 | 2005-08-04 | Vestas Wind Systems A/S | Methods of handling a wind turbine blade and system therefor |
| CN101287904A (en) * | 2005-09-21 | 2008-10-15 | Lm玻璃纤维有限公司 | Attachment devices on a wind turbine blade and a method of servicing utilizing these devices |
Non-Patent Citations (1)
| Title |
|---|
| 陈剑波等: "基于有限元分析和结构优化的飞机垂尾质量估算", 《计算机辅助工程》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173159A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Strength design method of tail structure |
| CN112417600A (en) * | 2020-11-20 | 2021-02-26 | 中国直升机设计研究所 | Method for rapidly calculating static strength of helicopter oil tank cabin |
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Application publication date: 20160601 |