CN103093082B - 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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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 of aircraft transonic flutter model and method for designing thereof.
Background technology
Flutter is a kind of destructive structure vibration occurred after ram compression exceedes critical value of flying in aircraft flight, and it is the autovibration under aerodynamic force, elastic force and inertial force interact.
In transonic speed region, due to the impact of air compressing, airplane aerodynamic sharply changes, and airplane flutter ram compression can be made to occur significantly declining, and the wind tunnel test of aircraft transonic flutter model is the important means of research aircraft transonic flutter characteristic variations.
Traditional transonic flutter model crossbeam design adopts solid metal beam or composite material beam, as shown in Figure 1, traditional solid beam has that design difficulty is little, the simple feature of processing technology, but because the weight of solid beam is larger, higher relative to the weight accounting of flutter model, cause the mass property simulation difficulty of flutter model large, model " density ratio " is larger.In addition, although composite material beam has advantage in Weight control, the discreteness of compound substance can cause the stiffness simulation of composite material beam to there is instability, increases the difficulty of modelling.
Summary of the invention
In order to solve the 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 of reduction, beam part by weight in a model can be reduced, reduce " density ratio " during flutter model design, be more 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 multiple hollow beam section, and described hollow beam section is made up of metal material, and the section of multiple hollow beam section reduces gradually along a direction.
Wherein, described hollow beam section is interconnected 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-shaped 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, a kind of method for designing of hollow beam of aircraft transonic flutter model is provided, comprises step:
1) rigidity data of each section of aircraft components is determined, according to the design profile of aircraft transonic flutter model scale Confirming model single-beam and the rigidity of each section;
2) according to the parameter of single-beam material therefor, the design object moments of inertia of each section of single-beam is determined;
3) the Section Design form of initial option single-beam, the design object moments of inertia according to each section carrys out reference section size;
4) according to each section size data calculated, single-beam is designed;
5) weight of single-beam and the weight accounting to overall flutter model is assessed, 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, redesign single-beam, until the weight accounting of single-beam and strength level reach designing requirement;
7) according to the mode that is linked and packed of the profile type determination single-beam of single-beam;
8) the integrated connection assembling of single-beam.
Wherein, in described step (3), accounting equation number is less than sectional parameter quantity, and Size calculation is separates more, can obtain organizing section size more, needs to select suitable section size according to design.
The single-beam design that the present invention proposes can overcome the deficiency of conventional model crossbeam, and tool has the following advantages:
1) adopt single-beam can reduce the weight of beam self, thus beam part by weight in a model can be reduced, reduce " density ratio " during flutter model design, be more conducive to the hazardous flight state of simulated aircraft transonic flutter;
2) adopt the single-beam of metal material can ensure 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.
Accompanying drawing explanation
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-shaped section of single-beam;
Fig. 7 is the schematic diagram of a kind of form of the π shape section of single-beam;
Fig. 8 is the schematic diagram of the 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 of the method for designing of single-beam according to 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
The preferred embodiments of the present invention are described in detail below in conjunction with accompanying drawing.Should be appreciated that discussed preferred embodiment only exemplarily illustrates implement and use ad hoc fashion of the present invention, but not limit the scope of the invention.
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 along its exhibition to being change, according to rigidity requirement of similarity, flutter model crossbeam is generally variation rigidity and becomes section size crossbeam.Due to the limitation of processing technology, the disposable processing of hollow metal beam becoming section size cannot complete, and the method connected again after adopting 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; Two parts or many parts of independent processing can also be designed to, be directly linked and packed by rivet (or bolt).
Mode one: the design of multistage beam section refers to that hollow crossbeam is made up 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 is through the hole 4 in hollow beam section 1, as shown in figs. 10-11, self-plugging rivet 3 plays transmitting force.Self-plugging rivet has the advantage 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 fit-up gap.The quantity of beam section and length can according to actual design need determine.
Mode two: when overall single-beam is designed to two parts or many parts, each several part is independently processed, and then is directly assembled in docking area by standard component (as rivet), and does not need other web member.Two-part interface smears metal-to-metal adhesive or the multiple material glued membrane of paving carries out hot setting connection, improves the efficiency that upper and lower two parts power is transmitted.
The section of single-beam can adopt various ways: cross rectangle (see Fig. 3), rectangle (see Fig. 4), double-U-shaped (see Fig. 5), U-shaped (see 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 efficiency in rigidity Design is different.
As shown in Figure 3, cross rectangular section single-beam is applicable to adopting the section hollow beam section designs such as multistage and carrying out rivet interlacement by web member, and bonding pad is upper and lower sidewall and limit wing.The effect of limit wing has 2 points, and one is to provide section stiffness, and two is connect power transmission.
As shown in Figure 4, rectangular section single-beam is also applicable to adopting the section beam section designs such as multistage and being connected by web member, and bonding pad is upper and lower sidewall.
As seen in figs. 5-6, double-U-shaped and U-shaped section single-beam are applicable to being designed to upper and lower two parts, are more directly connected by rivet.
For the supercritical wing aerofoil profile that civil aircraft is conventional, because its aerofoil profile is thinner, π shape curve profile can be adopted, improve the service efficiency of aerofoil profile when crossbeam Section Design.
π shape section has multiple design form, and as Figure 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 applicable to being designed to upper and lower two parts and is directly connected by rivet, and bonding pad is limit wing.
π shape section 2 and π shape section 3 single-beam are applicable to adopting the section beam section designs such as multistage and being connected by web member, and bonding pad is limit wing.
Two kinds of designs of single-beam are selected according to design needs, and do not have dividing of quality, from the angle of processing technology, the design that many parts directly connect is relatively simple in processing technology.
When single-beam Section Design, when wall thickness relatively little (T < H/10, t < W/10) and beam section is longer time, need the stability considering hollow thin-wall structure, single-beam needs design profile rib 5, play the effect improving overall 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 not design profile rib.
As shown in the process flow diagram in Figure 12, comprise step below according to the method for designing of single-beam of the present invention:
1) on the rigidity data basis of each section of known aircraft components, according to design profile and each cross sectional stiffness of flutter model design proportion chi (scale of length, rigidity engineer's scale) Confirming model crossbeam;
2) according to the parameter of crossbeam material therefor, the design object moments of inertia of each section of crossbeam is determined;
3) the Section Design form of initial option crossbeam, 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 single depth of 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 entirety.
Accounting equation number is less than sectional parameter quantity, and Size calculation is separates more, can obtain organizing section size more, needs to select suitable section size according to design.
4) according to each section size data calculated, single-beam is designed;
5) weight of single-beam and the weight accounting to overall flutter model is assessed, 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, redesigns single-beam, until single-beam weight accounting and strength level can reach designing requirement;
7) according to the mode that is linked and packed (mode one or mode two) of the profile type determination beam of single-beam;
8) the integrated connection assembling of single-beam.
In one embodiment, the target design rigidity of the transonic flutter model crossbeam of aircraft wing is in table 1, and beam section adopts hollow cross rectangle, and crossbeam material is plow-steel.Crossbeam adopts the design of the section size hollow beam sections such as multistage, and 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 beam section.The section size of each hollow beam section is in table 2, and the weight accounting having designed the relative flutter model of rear 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)
Resonance test and single-beam slow test is carried out according to the flutter model that above method design completes.The trial value of flutter model vibration characteristics compares in table 3 with design load, and from test findings, the stiffness simulation precision of single-beam is better.
Table 3 flutter model resonance test compares with design load
Figure 13 shows the strain curve of the slow test according to 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, 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 used for limiting practical range of the present invention.Namely all equivalences done according to the content of the present patent application the scope of the claims change and modify, and all belong to protection scope of the present invention.
Claims (6)
1. the method for designing of the single-beam of aircraft transonic flutter model, described single-beam is interconnected to form by multiple hollow beam section, and described hollow beam section is made up of metal material, and the section of multiple hollow beam section reduces gradually along a direction, it is characterized in that, described method for designing comprises step:
1) rigidity data of each section of aircraft components is determined, according to the design profile of aircraft transonic flutter model scale Confirming model single-beam and the rigidity of each section;
2) according to the parameter of single-beam material therefor, the design object moments of inertia of each section of single-beam is determined;
3) the Section Design form of initial option single-beam, the design object moments of inertia according to each section carrys out reference section size;
4) according to each section size data calculated, single-beam is designed;
5) weight of single-beam and the weight accounting to overall flutter model is assessed, 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, redesign single-beam, until the weight accounting of single-beam and strength level reach designing requirement;
7) according to the mode that is linked and packed of the profile type determination single-beam of single-beam;
8) the integrated connection assembling of single-beam.
2. the method for designing of single-beam according to claim 1, is characterized in that, in described step 3) in, accounting equation number is less than sectional parameter quantity, Size calculation is separates more, can obtain organizing section size more, needs to select suitable section size according to design.
3. the method for designing of single-beam according to claim 1, is characterized in that, described hollow beam section is interconnected by rivet or bolt.
4. the method for designing of single-beam 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.
5. the method for designing of the single-beam according to any one of claim 1 to 4, is characterized in that, the section of described hollow beam section is rectangle, U-shaped or π shape.
6. the method for designing of the single-beam according to any one of claim 1 to 4, is characterized in that, the section of described hollow beam section is cross rectangle or double-U-shaped.
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| 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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| 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 |
| 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 |
| 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 |
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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 |
| 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 |
| 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 |
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