CN103093082A - Single beam of transonic flutter model of airplane and design method thereof - Google Patents
Single beam of transonic flutter model of airplane and design method thereof Download PDFInfo
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- CN103093082A CN103093082A CN2012105728196A CN201210572819A CN103093082A CN 103093082 A CN103093082 A CN 103093082A CN 2012105728196 A CN2012105728196 A CN 2012105728196A CN 201210572819 A CN201210572819 A CN 201210572819A CN 103093082 A CN103093082 A CN 103093082A
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Abstract
The invention provides a single beam of an aircraft transonic flutter model and a design method thereof. Compared with the existing solid beam and composite beam, the single beam of the invention not only has stable rigidity, but also can reduce the weight of the beam, thereby reducing the weight proportion of the beam in the model, reducing the density ratio during the design of the flutter model, and being more beneficial to simulating the dangerous flight state of the aircraft with transonic flutter.
Description
Technical field
The present invention relates to a kind of single-beam, particularly a kind of single-beam and method for designing thereof of aircraft transonic flutter model.
Background technology
Flutter is that in aircraft flight, the flight ram compression surpasses a kind of destructive structure vibration that occurs after critical value, and it is the autovibration under aerodynamic force, elastic force and inertial force interact.
In the transonic speed zone, due to the impact of air compressing, aircraft aerodynamic force sharply changes, and can make the airplane flutter ram compression occur significantly descending, and the wind tunnel test of aircraft transonic flutter model is the important means of research aircraft transonic flutter characteristic variations.
Solid metal beam or composite material beam are adopted in traditional transonic flutter model crossbeam design, as shown in Figure 1, the tradition solid beam has that design difficulty is little, the simple characteristics of processing technology, but because the weight of solid beam is larger, weight accounting with respect to flutter model is higher, cause the mass property simulation difficulty of flutter model large, model " density ratio " is larger.In addition, although composite material beam has advantage on Weight control, the discreteness of compound substance can cause the stiffness simulation of composite material beam to have instability, increases the difficulty of modelling.
Summary of the invention
In order to address the above problem, the invention provides a kind of single-beam and method for designing thereof of aircraft transonic flutter model, this single-beam has the weight that reduces, can reduce the part by weight of beam in model, " density ratio " when reducing the flutter model design more is conducive to the hazardous flight state of simulated aircraft transonic flutter.
According to a first aspect of the invention, provide a kind of single-beam of aircraft transonic flutter model, described single-beam is interconnected to form by a plurality of hollow beam sections, and described hollow beam section is made by metal material, and the section of a plurality of hollow beam sections reduces gradually along a direction.
Wherein, described hollow beam section interconnects by rivet or bolt.
Wherein, adjacent hollow beam section interface is provided with metal-to-metal adhesive or multiple material glued membrane.
Wherein, the section of described hollow beam section is rectangle, U font or π shape.
Wherein, the section of described hollow beam section is cross rectangle or double-U-shaped.
According to another aspect of the present invention, provide a kind of method for designing of hollow beam of aircraft transonic flutter model, comprise step:
1) determine the rigidity data of each section of aircraft components, determine the rigidity of design profile He each section of model single-beam according to aircraft transonic flutter model scale;
2) according to the parameter of single-beam material therefor, determine the design object moments of inertia of each section of single-beam;
3) the Section Design form of initial option single-beam is come the reference section size according to the design object moments of inertia of each section;
4) according to each section size data that calculate, design single-beam;
5) weight of assessment single-beam reaches the weight accounting to whole flutter model, the strength level of assessment single-beam;
6) if the weight accounting of single-beam is unreasonable or strength level does not reach designing requirement, change Section Design form or section size, the redesign single-beam is until weight accounting and the strength level of single-beam reach designing requirement;
7) determine the mode that is linked and packed of single-beam according to the profile type of single-beam;
8) integrated connection of single-beam assembling.
Wherein, in described step (3), the Square number of passes is less than sectional parameter quantity, and size is calculated as separate more, can obtain many group section sizes, selects suitable section size according to the design needs.
The single-beam design that the present invention proposes can overcome the deficiency of conventional model crossbeam, has following advantage:
1) adopt single-beam can reduce the weight of beam self, thereby can reduce the part by weight of beam in model, " density ratio " when reducing the flutter model design more is conducive to the hazardous flight state of simulated aircraft transonic flutter;
2) adopt the single-beam of metal material can guarantee the stability that rigidity of model designs, improve the precision of rigidity Design;
3) beams of metal can adopt mechanical digital control processing, and processing technology is simple, and machining precision is high.
Description of drawings
Fig. 1 is the structural representation of traditional solid beam;
Fig. 2 is the structural representation according to single-beam of the present invention;
Fig. 3 is the schematic diagram of the cruciform section of single-beam;
Fig. 4 is the schematic diagram of the rectangular section of single-beam;
Fig. 5 is the schematic diagram of the double-U-shaped section of single-beam;
Fig. 6 is the schematic diagram of the U i section of single-beam;
Fig. 7 is a kind of schematic diagram of form of the π shape section of single-beam;
Fig. 8 is the schematic diagram of another kind of form of the π shape section of single-beam;
Fig. 9 is the schematic diagram of another form of the π shape section of single-beam;
Figure 10 is the schematic diagram of the type of attachment of hollow beam section;
Figure 11 is the schematic diagram of the section rib of hollow beam section;
Figure 12 is the process flow diagram according to the method for designing of the single-beam of aircraft transonic flutter model of the present invention; And
Figure 13 shows the slow test strain curve according to single-beam of the present invention.
Embodiment
Describe the preferred embodiments of the present invention in detail below in conjunction with accompanying drawing.Should be appreciated that the preferred embodiment of discussing only exemplarily illustrates enforcement and uses ad hoc fashion of the present invention, but not limit the scope of the invention.
The flutter model crossbeam is used for simulating the rigidity of the aircraft components such as wing, horizontal tail, vertical fin, and because the rigidity of aircraft load parts is opened up to changing along it, according to the rigidity requirement of similarity, the flutter model crossbeam is generally and becomes rigidity change section size crossbeam.Due to the limitation of processing technology, the disposable processing of hollow metal beam that becomes section size can't be completed, and adopts the method that connects again after segmental machining just can complete.
Fig. 2 shows the schematic diagram according to single-beam of the present invention.Single-beam can be designed to be assembled by web member 2 by multistage hollow beam section 1; Can also be designed to two parts or many parts of independent processing, directly be linked and packed by rivet (or bolt).
Mode one: the design of multistage beam section refers to that hollow crossbeam is comprised of multistage hollow beam section 1, two adjacent hollow beams are intersegmental to be connected by web member 2, beam section and web member adopt self-plugging rivet 3 to be connected and fixed, self-plugging rivet 3 passes the hole 4 on hollow beam section 1, as shown in Figure 10-11, self-plugging rivet 3 works the power of transmitting.Self-plugging rivet has advantages of that assembling is simple, assembly precision is high.During the assembling of beam section, the surface of contact of hollow beam section and web member is provided with metal-to-metal adhesive or multiple material glued membrane, eliminates the fit-up gap.The quantity of beam section and length can be determined according to the needs of actual design.
Mode two: when whole single-beam was designed to two parts or many parts, each several part was independently processed, and then directly assembled in the docking area by standard component (as rivet), and did not need other web member.Two-part interface smears metal-to-metal adhesive or the multiple material glued membrane of paving carries out the hot setting connection, improves the efficient that upper and lower two parts power is transmitted.
The section of single-beam can adopt various ways: and cross rectangle (seeing Fig. 3), rectangle (seeing Fig. 4), double-U-shaped (seeing Fig. 5), U font (seeing Fig. 6), π shape section (Fig. 7-Fig. 9).Select suitable profile type according to the actual needs of modelling, different profile type functions is the same, but the efficient on rigidity Design is different.
As shown in Figure 3, the section hollow beam sections such as the suitable employing of cross rectangular section single-beam multistage design and carry out rivet by web member and connect, and the bonding pad is upper and lower sidewall and limit wing.The effect of limit wing has 2 points, and one is to provide part rigidity, and the 2nd, connect power transmission.
As shown in Figure 4, the rectangular section single-beam also be fit to adopt the section beam section design such as multistage and connects by web member, and the bonding pad is upper and lower sidewall.
As shown in Fig. 5-6, double-U-shaped and U i section single-beam are fit to be designed to upper and lower two parts, more directly connect by rivet.
For civil aircraft supercritical wing aerofoil profile commonly used, because its aerofoil profile is thinner, can adopt π shape curve profile, improve the service efficiency of aerofoil profile when the crossbeam Section Design.
π shape section has multiple design form, and as shown in Fig. 7-9, the π shape section of Fig. 7 is conventional design, and the π shape section of Fig. 8-9 is all curve profile.
The π shape section single-beam of Fig. 7 is fit to be designed to upper and lower two parts and directly connects by rivet, and the bonding pad is the limit wing.
Two kinds of designs of single-beam are selected according to the design needs, there is no dividing of quality, and from the angle of processing technology, the direct-connected design of many parts is relatively simple on processing technology.
When the single-beam Section Design, when the wall thickness less (when T＜H/10, t＜W/10) and beam section are longer, need to consider the stability of hollow thin-wall structure, single-beam needs design profile rib 5, play the effect that improves whole crossbeam stability, the quantity of section rib and position are determined according to beam section size and beam length.When wall thickness is relatively large, need consider suitably to reduce beam length when design profile rib not.
As shown in the process flow diagram in Figure 12, comprise following step according to the method for designing of single-beam of the present invention:
1) on the rigidity data basis of known each section of aircraft components, determine design profile and each cross sectional stiffness of model crossbeam according to flutter model design proportion chi (scale of length, rigidity engineer's scale);
2) according to the parameter of crossbeam material therefor, determine the design object moments of inertia of each section of crossbeam;
3) the Section Design form of initial option crossbeam is according to each section target moments of inertia reference section size;
The calculating method of stiffness of typical case's cross rectangular section is:
Vertical curve rigidity: computing formula:
EI
X＝E×[W×H
3/12-(W-2×t)×(H-2×T)
3/12+(L-W)×(B/2)
3/12]
Horizontal curvature rigidity: computing formula:
EI
Y＝E×[H×W
3/12-(H-2×T)×(W-2×t)
3/12+B×L
3/12-B×W
3/12]
Torsional rigidity: computing formula:
Wherein, E is the bending modulus of beam material; G is torsion modulus;
H is the height of single-beam; T is the thickness of single-beam upper wall;
T is the thickness of single-beam sidewall; B is the thickness of single-beam limit wing;
W is the width of single-beam hollow parts; L is the width of single-beam integral body.
The Square number of passes is less than sectional parameter quantity, and size is calculated as separate more, can obtain many group section sizes, selects suitable section size according to the design needs.
4) according to each section size data that calculate, design single-beam;
5) weight of assessment single-beam reaches the weight accounting to whole flutter model, the strength level of assessment single-beam;
6) as unreasonable in beam weight accounting or strength level does not reach designing requirement, changes Section Design form or section size, and the redesign single-beam is until single-beam weight accounting and strength level can reach designing requirement;
7) determine the mode that is linked and packed (mode one or mode two) of beam according to the profile type of single-beam;
8) integrated connection of single-beam assembling.
In one embodiment, the target design rigidity of the transonic flutter model crossbeam of aircraft wing sees Table 1, and the beam section adopts hollow cross rectangle, and the crossbeam material is plow-steel.Crossbeam adopts the design of the section size hollow beam sections such as multistage, and the hollow beam section is 8 sections, the intersegmental web member that is installed with of adjacent beams, and web member is connected by self-plugging rivet with the beam section.The section size of each hollow beam section sees Table 2, and after design is completed, the weight accounting of the relative flutter model of single-beam is 35%, meets design requirement.
Table 1 flutter model single-beam design rigidity
Table 2 flutter model single-beam section size (cross rectangle)
The flutter model of completing according to above method design carries out resonance test and single-beam slow test.The trial value of flutter model vibration characteristics and design load relatively see Table 3, and from test findings, the stiffness simulation precision of single-beam is better.
Table 3 flutter model resonance test and design load are relatively
Figure 13 shows the strain curve according to the slow test of single-beam of the present invention.From strain curve, the connection power transmission effect of single-beam is better.From the result of slow test as can be known, the intensity of single-beam also can meet design requirement.
Described in the present invention, concrete case study on implementation is only better case study on implementation of the present invention, is not to limit practical range of the present invention.Be that all equivalences of doing according to the content of the present patent application the scope of the claims change and modify, all belong to protection scope of the present invention.
Claims (7)
1. the single-beam of an aircraft transonic flutter model, is characterized in that, described single-beam is interconnected to form by a plurality of hollow beam sections, and described hollow beam section is made by metal material, and the section of a plurality of hollow beam sections reduces gradually along a direction.
2. the single-beam of aircraft transonic flutter model according to claim 1, is characterized in that, described hollow beam section interconnects by rivet or bolt.
3. the single-beam of aircraft transonic flutter model according to claim 1, is characterized in that, the interface of adjacent hollow beam section is provided with metal-to-metal adhesive or multiple material glued membrane.
4. the single-beam of the described aircraft transonic flutter of any one model in 3 according to claim 1, is characterized in that, the section of described hollow beam section is rectangle, U font or π shape.
5. the single-beam of the described aircraft transonic flutter of any one model in 3 according to claim 1, is characterized in that, the section of described hollow beam section is cross rectangle or double-U-shaped.
6. be used for according to claim 1 it is characterized in that to the method for designing of the single-beam of the 5 described aircraft transonic flutter of any one models, comprise step:
1) determine the rigidity data of each section of aircraft components, determine the rigidity of design profile He each section of model single-beam according to aircraft transonic flutter model scale;
2) according to the parameter of single-beam material therefor, determine the design object moments of inertia of each section of single-beam;
3) the Section Design form of initial option single-beam is come the reference section size according to the design object moments of inertia of each section;
4) according to each section size data that calculate, design single-beam;
5) weight of assessment single-beam reaches the weight accounting to whole flutter model, the strength level of assessment single-beam;
6) if the weight accounting of single-beam is unreasonable or strength level does not reach designing requirement, change Section Design form or section size, the redesign single-beam is until weight accounting and the strength level of single-beam reach designing requirement;
7) determine the mode that is linked and packed of single-beam according to the profile type of single-beam;
8) integrated connection of single-beam assembling.
7. the method for designing of single-beam according to claim 6, is characterized in that, in described step (3), the Square number of passes is less than sectional parameter quantity, size is calculated as separate more, can obtain many group section sizes, selects suitable section size according to the design needs.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
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| US3645481A (en) * | 1970-04-22 | 1972-02-29 | Lanier Ind Inc | Airfoil structure |
| US5973440A (en) * | 1997-07-07 | 1999-10-26 | Nitzsche; Fred | Structural component having means for actively varying its stiffness to control vibrations |
| CN102419163A (en) * | 2011-08-15 | 2012-04-18 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining section size of thin-wall rectangular hollow beam with lugs |
| CN102645317A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Hollow beam with four lugs for high-speed flutter model and fabrication method of hollow beam |
| CN102661730A (en) * | 2012-05-11 | 2012-09-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining hollow girder cross-section size of airplane high-speed vibration girder model |
| CN102661729A (en) * | 2012-05-11 | 2012-09-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for confirming sectional dimension of I-shaped hollow beam of high-speed fluttering model of airplane |
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- 2012-12-25 CN CN201210572819.6A patent/CN103093082B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3645481A (en) * | 1970-04-22 | 1972-02-29 | Lanier Ind Inc | Airfoil structure |
| US5973440A (en) * | 1997-07-07 | 1999-10-26 | Nitzsche; Fred | Structural component having means for actively varying its stiffness to control vibrations |
| CN102419163A (en) * | 2011-08-15 | 2012-04-18 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining section size of thin-wall rectangular hollow beam with lugs |
| CN102645317A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Hollow beam with four lugs for high-speed flutter model and fabrication method of hollow beam |
| CN102661730A (en) * | 2012-05-11 | 2012-09-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining hollow girder cross-section size of airplane high-speed vibration girder model |
| CN102661729A (en) * | 2012-05-11 | 2012-09-12 | 中国航空工业集团公司西安飞机设计研究所 | Method for confirming sectional dimension of I-shaped hollow beam of high-speed fluttering model of airplane |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
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