CN105243274B - A kind of method for the vibration frequency for determining the guided missile structure with wedge ring - Google Patents
A kind of method for the vibration frequency for determining the guided missile structure with wedge ring Download PDFInfo
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- CN105243274B CN105243274B CN201510644230.6A CN201510644230A CN105243274B CN 105243274 B CN105243274 B CN 105243274B CN 201510644230 A CN201510644230 A CN 201510644230A CN 105243274 B CN105243274 B CN 105243274B
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- guided missile
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- wedge ring
- vibration frequency
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Abstract
The invention discloses a kind of method for the vibration frequency for determining the guided missile structure with wedge ring.The method of the vibration frequency for determining the guided missile structure with wedge ring includes the following steps：Step 1：Establish the finite element numerical model of guided missile structure to be measured；Step 2：Establish osculating element and constrained and apply load；Step 3：Calculate amount of deflection and corner；Step 4：Simplify shell unit and beam element；Step 5：Wedge ring region in shell unit in step 4 is converted to etc. to the shell unit of quality with equivalent thickness；Step 6：Constrained and apply load；Step 7：Calculate amount of deflection and corner；Step 8：Draw amount of deflection linear fit coordinate diagram；Step 9：Obtain the vibration frequency of the finite element model of guided missile to be measured.Granting using the present invention, the vibration frequency result precision for the guided missile to be measured obtained is high, and method is simple, and computational efficiency is high.
Description
Technical field
The present invention relates to missile measure field, more particularly to a kind of vibration frequency for determining the guided missile structure with wedge ring
Method.
Background technology
In the prior art, when carrying out containing wedge ring guided missile structure Dynamic Characteristics, osculating element can not use, engineering
On continuous treatment method is generally employed to join domain, that is, ignore influence of the connection to structure global stiffness, connection tied
Structure may be only available for the structure being completely embedded as a non-individual body, this method, and larger mistake certainly will be brought for wedge ring connection
Difference.
Thus, it is desirable to have a kind of technical solution is come at least one drawbacks described above for overcoming or at least mitigating the prior art.
The content of the invention
It is an object of the invention to provide a kind of method for the vibration frequency for determining the guided missile structure with wedge ring to overcome
Or at least one drawbacks described above at least in the mitigation prior art.
To achieve the above object, the present invention provides a kind of method for the vibration frequency for determining the guided missile structure with wedge ring.
The method of the vibration frequency for determining the guided missile structure with wedge ring includes the following steps：Step 1：Establish guided missile structure to be measured
Finite element numerical model；Step 2：Establish wedge ring region and the contact list in guided missile structure to be measured with wedge ring region contact portion
Member, and guided missile structure to be measured is constrained and applies load；Step 3：The node on the neutral surface of guided missile to be measured is taken, is calculated
Under different loads, the amount of deflection and corner of the node on the neutral surface of the guided missile to be measured；Step 4：By in the step 2
The guided missile structure to be measured is simplified to shell unit and beam element；Step 5：The osculating element in the step 2 is compareed, will
Wedge ring region in shell unit in the step 4 is converted to etc. the shell unit of quality with equivalent thickness；Step 6：To the step
The beam element in shell unit and step 4 in rapid 5 is constrained and applies load；Step 7：Calculate under different loads, institute
State the amount of deflection and corner of the node on the neutral surface of the shell unit and beam element in step 6；Step 8：In amendment step 7
The rigidity of the shell unit of contact area, until the deflection data tried to achieve in step 7 is consistent with the deflection data of step 3, drafting is scratched
Spend linear fit coordinate diagram；Step 9：Obtain the vibration frequency of the finite element model of guided missile step 5 to be measured.
Preferably, the step 2 includes：Step 21：By wedge ring region division into the contact with guided missile to be measured of wedge ring region
Region and wedge ring region and the non-contact area of guided missile to be measured；Step 22：By the circle in contact area with guided missile structure to be measured
The node of cylinder contact is as osculating element；Step 23：Constraint is applied to one end of guided missile to be measured；Step 24：To guided missile to be measured
The one end for not applying constraint applies load.
Preferably, 15 groups of different load of numerical values recited are at least applied in the step 24.
Preferably, the wedge ring region in the shell unit in the step 5 such as is converted at the shell unit equivalent thickness tool of quality
Body method is to carry out the conversion between quality and thickness by following calculation formula：
M=s × ρ × d
In formula, m is contact area quality；S is contact area area；ρ is contact area density；D is contact area thickness.
Preferably, the shell unit in the step 5 and the beam element in step 4 are constrained and applies the tool of load
Body method is：Constraint is applied to one end of guided missile to be measured first, the one end for not applying constraint to guided missile to be measured then applies load.
Preferably, 15 groups of different load of numerical values recited are at least applied.
Preferably, the neutral surface is the plane where guided missile central axes.
In the method for the vibration frequency for determining the guided missile structure with wedge ring of the present invention, by by the wedge in shell unit
Ring region such as is converted at the shell unit equivalent thickness of quality, calculates the amount of deflection and corner of the node on the neutral surface of shell unit,
And combine the amount of deflection that calculates of finite element numerical model of guided missile structure to be measured and corner tries to achieve deflection value, then obtain to be measured
The vibration frequency of guided missile, as a result precision is high, and method is simple, and computational efficiency is high.
Brief description of the drawings
Fig. 1 is the flow diagram of the method for the vibration frequency for determining the guided missile structure with wedge ring of the present invention.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
The method for determining the vibration frequency of the guided missile structure with wedge ring according to the present invention, includes the following steps：Step
1：Establish the finite element numerical model of guided missile structure to be measured.
Step 2：Wedge ring region and the osculating element in guided missile structure to be measured with wedge ring region contact portion are established, and is treated
Survey guided missile structure and constrained and applied load.In the present embodiment, step 2 includes：
Step 21：By wedge ring region division into wedge ring region and guided missile to be measured contact area and wedge ring region with it is to be measured
The non-contact area of guided missile；Step 22：Using in contact area with the node that the cylinder of guided missile structure to be measured contacts as contacting
Unit；Step 23：Constraint is applied to one end of guided missile to be measured；Step 24：The one end for not applying constraint to guided missile to be measured applies load
Lotus.
In the present embodiment, 15 groups of different load of numerical values recited are at least applied in step 24.Advantageously, application
Load group number is more, and obtained value is closer to actual value.
Step 3：The node on the neutral surface of guided missile to be measured is taken, is calculated under different loads, the neutrality of the guided missile to be measured
The amount of deflection and corner of node on face.
Step 4：The guided missile structure to be measured in the step 2 is simplified to shell unit and beam element.
Step 5：The osculating element in the step 2 is compareed, by the wedge ring region in the shell unit in the step 4
The shell unit of quality is converted to etc. with equivalent thickness.In the present embodiment, the wedge ring region in the shell unit in step 5 is converted to
Shell unit equivalent thickness specific method etc. quality is to carry out the conversion between quality and thickness by following calculation formula：
M=s × ρ × d
In formula, m is contact area quality；S is contact area area；ρ is contact area density；D is contact area thickness.
Step 6：Shell unit in the step 5 and the beam element in step 4 are constrained and apply load.At this
In embodiment, the specific method for the shell unit in step 5 and the beam element in step 4 being constrained and being applied load is：
Constraint is applied to one end of guided missile to be measured first, the one end for not applying constraint to guided missile to be measured then applies load.
In the present embodiment, 15 groups of different load of numerical values recited are at least applied in step 6.Advantageously, application
Load group number is more, and obtained value is closer to actual value.
Step 7：Calculate under different loads, the shell unit in the step 6 and the node on the neutral surface of beam element
Amount of deflection and corner.
Step 8：The rigidity of the shell unit of contact area in amendment step 7, until in step 7 deflection data tried to achieve with
The deflection data of step 3 is consistent, draws amount of deflection linear fit coordinate diagram.
Step 9：Obtain the vibration frequency of the finite element model of guided missile step 5 to be measured.
It is understood that above-mentioned neutral surface is the plane where guided missile central axes, above-mentioned neutrality why is selected
Face, is due to change in load effect lower section shape, each point lateral displacement differs on section, selects the position of neutral surface
In-migration can characterize the global displacement in section, meanwhile, the corner of neutral surface is 0, neutral surface just like beam neutral axis, on neutral axis
Direct stress be equal to 0.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution described in foregoing embodiments, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical solution
God and scope.
Claims (7)
- A kind of 1. method for the vibration frequency for determining the guided missile structure with wedge ring, it is characterised in that the described method includes as follows Step：Step 1：Establish the finite element numerical model of guided missile structure to be measured；Step 2：Wedge ring region and the osculating element in guided missile structure to be measured with wedge ring region contact portion are established, and is led to be measured Play structure and constrained and applied load；Step 3：The node on the neutral surface of guided missile to be measured is taken, is calculated under different loads, on the neutral surface of the guided missile to be measured Node amount of deflection and corner；Step 4：The guided missile structure to be measured in the step 2 is simplified to shell unit and beam element；Step 5：Compare the osculating element in the step 2, by the wedge ring region in the shell unit in the step 4 with etc. Effect thickness such as is converted at the shell unit of quality；Step 6：Shell unit in the step 5 and the beam element in step 4 are constrained and apply load；Step 7：Calculate under different loads, the shell unit in the step 6 and the node on the neutral surface of beam element are scratched Degree and corner；Step 8：The rigidity of the shell unit of contact area in amendment step 7, until the deflection data and step tried to achieve in step 7 3 deflection data is consistent, draws amount of deflection linear fit coordinate diagram；Step 9：Obtain the vibration frequency of the finite element model of guided missile to be measured.
- 2. the method for the vibration frequency as claimed in claim 1 for determining the guided missile structure with wedge ring, it is characterised in that described Step 2 includes：Step 21：By contact area and wedge ring region of the wedge ring region division into wedge ring region and guided missile to be measured and guided missile to be measured Non-contact area；Step 22：Using the node contacted in contact area with the cylinder of guided missile structure to be measured as osculating element；Step 23：Constraint is applied to one end of guided missile to be measured；Step 24：The one end for not applying constraint to guided missile to be measured applies load.
- 3. the method for the vibration frequency as claimed in claim 2 for determining the guided missile structure with wedge ring, it is characterised in that described At least apply 15 groups of different load of numerical values recited in step 24.
- 4. the method for the vibration frequency as claimed in claim 1 for determining the guided missile structure with wedge ring, it is characterised in that described The shell unit equivalent thickness specific method that wedge ring region in shell unit in step 5 such as is converted at the quality is to pass through following meters Calculate the conversion between formula progress quality and thickness：M=s × ρ × dIn formula, m is contact area quality；S is contact area area；ρ is contact area density；D is contact area thickness.
- 5. the method for the vibration frequency as claimed in claim 1 for determining the guided missile structure with wedge ring, it is characterised in that to institute State the beam element in shell unit and step 4 in step 5 and constrained and applied the specific method of load and be：First to be measured One end of guided missile applies constraint, and the one end for not applying constraint to guided missile to be measured then applies load.
- 6. the method for the vibration frequency as claimed in claim 5 for determining the guided missile structure with wedge ring, it is characterised in that at least Apply 15 groups of different load of numerical values recited.
- 7. the method for the vibration frequency as claimed in claim 1 for determining the guided missile structure with wedge ring, it is characterised in that described Neutral surface is the plane where guided missile central axes.
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| CN201510644230.6A CN105243274B (en) | 2015-10-08 | 2015-10-08 | A kind of method for the vibration frequency for determining the guided missile structure with wedge ring |
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| CN105243274B true CN105243274B (en) | 2018-04-13 |
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| CN109558685B (en) * | 2018-12-05 | 2021-07-13 | 北京航空航天大学 | Projectile body fulcrum judging method and device, storage medium and electronic equipment |
Citations (2)
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| CN103455728A (en) * | 2013-09-13 | 2013-12-18 | 天津大学 | Method for tuning and optimizing parameters of dynamic absorber based on machining process |
| CN103577659A (en) * | 2012-07-18 | 2014-02-12 | 上海宝钢工业技术服务有限公司 | Method for analyzing influence of electric furnace transformer axial pre-tightening force on natural vibration frequency |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| KR20130098059A (en) * | 2012-02-27 | 2013-09-04 | 삼성전기주식회사 | Inertial sensor |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103577659A (en) * | 2012-07-18 | 2014-02-12 | 上海宝钢工业技术服务有限公司 | Method for analyzing influence of electric furnace transformer axial pre-tightening force on natural vibration frequency |
| CN103455728A (en) * | 2013-09-13 | 2013-12-18 | 天津大学 | Method for tuning and optimizing parameters of dynamic absorber based on machining process |
Non-Patent Citations (2)
| Title |
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| 大型气候环境实验室冷媒的分析选择;张惠等;《装备环境工程》;20150430;第12卷(第2期);第104-109页 * |
| 大展弦比直机翼双机身飞机中机身与机翼的最佳布置问题;邓扬晨等;《飞机设计》;20050331(第1期);第14-16页 * |
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