CN107458623A - A kind of T tails aircraft vertical fin spar testpieces design method - Google Patents

A kind of T tails aircraft vertical fin spar testpieces design method Download PDF

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Publication number
CN107458623A
CN107458623A CN201710661314.XA CN201710661314A CN107458623A CN 107458623 A CN107458623 A CN 107458623A CN 201710661314 A CN201710661314 A CN 201710661314A CN 107458623 A CN107458623 A CN 107458623A
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msub
spar
mrow
mfrac
flange
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CN107458623B (en
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侯瑞
王远芳
杨杰
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Xian Aircraft Design and Research Institute of AVIC
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Xian Aircraft Design and Research Institute of AVIC
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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
    • B64F5/60—Testing or inspecting aircraft components or systems

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The present invention relates to a kind of T tails aircraft vertical fin spar testpieces design method, belong to technical field of aircraft structure design, the T tails aircraft vertical fin spar testpieces design method is used for the size for determining spar testpieces, the spar testpieces includes spar web, spar flange and edge strip crimp, and the size includes the width b of spar webwWith thickness tw, spar flange width bfWith thickness tfAnd the width b of edge strip crimpLWith thickness tL, step is obtains the size of spar web first, afterwards according to the size of spar web board size calculating spar flange, according to the size of the Size calculation edge strip crimp of spar flange.The T tail aircraft vertical fin spar testpieces design methods of the present invention can be very good to simulate support of the covering to spar, and the design of short form test part is final to reduce experiment difficulty, saves experimentation cost.

Description

A kind of T tails aircraft vertical fin spar testpieces design method
Technical field
The invention belongs to aircraft tail structure design field, more particularly to a kind of T tails aircraft vertical fin spar testpieces Design method.
Background technology
Airplane tail group is generally divided into two kinds：One kind is horizontal tail, and a kind of is the T-shaped vertical fin being made up of vertical fin and horizontal tail.For T Tail (i.e. T-shaped vertical fin) aircraft, because horizontal tail height is placed in vertical fin wing tip, vertical fin spar is except bearing asymmetric motor-driven caused shearing Load, symmetrical motor-driven caused Tensile or Compressive Loading is still suffered from, this is different from traditional low-set-tail aircraft.And spar bears load Complexity bring difficulty to the design of spar testpieces.The design of traditional spar testpieces frequently with diagonal stretch plate or Single cantilever beam method, this two kinds of testpieces are designed for shear-type load, can not consider shadow of the Tensile or Compressive Loading to spar Ring.
If intercepting spar typical segment, spar compressive load experiment is directly carried out, due to lacking covering to spar flange Support, spar flange end free, edge strip can shift to an earlier date unstable failure, and the actual stand under load of this and spar on aircraft is not inconsistent.
And in the prior art, if desired for support of the simulation covering to spar flange, it is necessary to carry out box section experiment in experiment, The experiment of part level is risen into component level experiment, test class improves one-level, and testpieces production and the expense tested greatly increase.
The content of the invention
It is an object of the invention to provide a kind of T tails aircraft vertical fin spar testpieces design method, for solving setting at present When counting T-shaped aircraft vertical fin spar, without the problem of effectively simulation covering is to the testpieces of the support of spar.
To reach above-mentioned purpose, the technical solution adopted by the present invention is：A kind of T tails aircraft vertical fin spar testpieces design side Method, the T tails aircraft vertical fin spar testpieces design method are used for the size for determining spar testpieces, the spar testpieces bag Spar web, spar flange and edge strip crimp are included, the size includes the width b of spar webwWith thickness tw, spar flange Width bfWith thickness tfAnd the width b of edge strip crimpLWith thickness tL, step is
The size of spar web is obtained first, the size of spar flange is calculated according to spar web board size afterwards, according to the wing The size of the Size calculation edge strip crimp of beam edge strip.
Further, the dimension process of acquisition spar web is：The width b of spar webwWith thickness twWith former spar web The parameter of plate is identical.
Further, the dimension process for calculating spar flange is：
A, the thickness t of spar flangefIt is identical with the thickness of former spar flange and the thickness sum of former covering；
B, the width b of spar flangefWith effective carrying width b' of former coveringmIt is identical, i.e.,
t'mFor the thickness of former covering, E'mThe modulus of elasticity of former covering, E'fFor the modulus of elasticity of original spar flange, σ 'co For the unstability stress of former covering.
Further, the dimension process of calculating edge strip crimp is：
The inertia of edge strip crimp with area away from needing to meet following formula：
Wherein, ILIt is the moment of inertia of edge strip crimp, ALIt is the area that edge strip crimp contacts with former covering；
And the Instability load of edge strip crimp have to be larger than the Instability load equal to spar flange, i.e.,
Wherein, NLIt is edge strip crimp Instability load, NfIt is spar flange Instability load, DL66Turned round for edge strip crimp Turn rigidity, Df22For bending stiffness of the spar flange on parallel to spar flange direction, Df11It is spar flange parallel to the wing Bending stiffness on web direction, Df12The coupling bending stiffness for being spar flange on above-mentioned two direction, Df66For spar Edge strip torsional rigidity, DL66For spar web torsional rigidity.
The T tail aircraft vertical fin spar testpieces design methods of the present invention can be very good to simulate support of the covering to spar, The design of short form test part, it is final to reduce experiment difficulty, save experimentation cost.
Brief description of the drawings
Accompanying drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention Example, and for explaining principle of the invention together with specification.
Fig. 1 is the spar testpieces structural representation of prior art.
Fig. 2 is the spar testpieces shaft side figure of prior art.
Fig. 3 is the spar testpieces structural representation of the present invention.
Fig. 4 is the spar testpieces shaft side figure of the present invention.
Reference：
1 '-former spar web, 2 '-former spar flange, 3 '-former covering, 4 '-stringer；
1- spar webs, 2- spar flanges, 3- edge strip crimps.
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 Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.
To distinguish the difference of the spar testpieces of the present invention and former spar testpieces, in former spar testpieces structure is represented Numbering or mark in add " ' " be distinguish between.
It is former spar structure of the prior art as depicted in figs. 1 and 2, former spar is included by former spar web 1 ' and original Former spar testpieces, the former covering 3 ' fixed with former spar flange 2 ' and the length for being supported in former covering 3 ' that spar flange 2 ' is formed Purlin 4 '.It is former because former spar flange 2 ' lacks the support of former covering 3 ' in spar compression test for former spar testpieces Spar flange 2 ' can shift to an earlier date stress in unstability, with real structure and not meet, and also can not just verify the intensity of spar.
And the present invention then proposes a kind of T tails aircraft vertical fin spar testpieces design method, the experiment of T tail aircraft vertical fins spar Part design method is used for the size for determining the spar testpieces of checking spar intensity, as shown in Figure 3 and Figure 4, spar testpieces bag Spar web 1, spar flange 2 and edge strip crimp 3 are included, and spar testpieces size then includes the width b of spar web 1wAnd thickness Spend tw, spar flange 2 width bfWith thickness tfAnd the width b of edge strip crimp 3LWith thickness tL, specific design method step For：
The size of spar web 1, the width b of spar web 1 are obtained firstwWith thickness twWith the ginseng of former spar web 1 ' Number is identical.
Afterwards according to the size of the Size calculation spar flange 2 of spar web 1, the size of spar flange 2 is calculated in the present invention Process is：
A, the thickness t of spar flange 2fIt is identical with the thickness of former spar flange 2 ' and the thickness sum of former covering 3 '；
B, the width b of spar flange 2fWith effective carrying width b' of former covering 3 'mIt is identical, i.e.,
t'mFor the thickness of former covering, E'mThe modulus of elasticity of former covering, E'fFor the modulus of elasticity of original spar flange, σ 'co For the unstability stress (also known as broken Zernike annular polynomial) of former covering.
Finally, according to the size of the Size calculation edge strip crimp 3 of spar flange 2, the dimension process of calculating edge strip crimp 3 For：
The inertia of edge strip crimp 3 with area away from needing to meet following formula, i.e.,
Wherein, ILIt is the moment of inertia of edge strip crimp, ALIt is the area that edge strip crimp contacts with former covering；And edge strip crimp (3) Instability load have to be larger than the Instability load equal to spar flange (2), i.e.,
Wherein, NLIt is edge strip crimp Instability load, NfIt is spar flange Instability load, DL66Turned round for edge strip crimp Turn rigidity, Df22It is spar flange parallel to spar flange direction (bending stiffness in reference picture 4 on the b) of direction, Df11For the wing Beam edge strip is parallel to spar web direction (bending stiffness in reference picture 4 on a) of direction, Df12It is spar flange above-mentioned two Coupling bending stiffness on individual direction, Df66For spar flange torsional rigidity, DL66For spar web torsional rigidity.
Above-mentioned design method is described further by taking the design parameter of aircraft vertical fin spar testpieces as an example.In original In beginning spar structure, original spar parameter has：
The former width b' of spar web 1 'w=380mm, thickness t'w=3.014mm,
The former width of spar flange 2 ' b'f=40mm, thickness t'f=4.016mm,
Former covering 3 ' effectively carrying broadband b'm=40mm, thickness t'm=3.712mm, the elastic model E' of former coveringm= 54002MPa, the elastic modulus E of former spar flange 'f=49829MPa, former covering unstability stress σ 'co=49829MPa, Df11= 212111MPa, Df22=104260MPa, Df12=60743MPa, Df66=82101MPa, DL66=82101MPa.
According to above-mentioned design method, it may be determined that the parameter of central spar testpieces of the present invention has spar web width bwAnd thickness Spend tw, spar flange width bfWith thickness tfAnd edge strip crimp width bLWith thickness tL, i.e.,
bw=b'w=380mm, tw=t'w=3.014mm；
And simultaneous following four equation：
Finally try to achieve bf, tf, bL, tL：
bf=49.7mm, tf=4.55mm, bL=18.19mm, tL=4.59mm.
The T tail aircraft vertical fin spar testpieces design methods of the present invention can be very good to simulate support of the covering to spar, The design of short form test part, it is final to reduce experiment difficulty, save experimentation cost.
It is described above, it is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto, Any one skilled in the art the invention discloses technical scope in, the change or replacement that can readily occur in, It should all be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim Enclose and be defined.

Claims (4)

  1. A kind of 1. T tails aircraft vertical fin spar testpieces design method, it is characterised in that the T tails aircraft vertical fin spar testpieces Design method is used to determining the size of spar testpieces, the spar testpieces include spar web (1), spar flange (2) and Edge strip crimp (3), the size include the width b of spar web (1)wWith thickness tw, spar flange (2) width bfAnd thickness tfAnd the width b of edge strip crimp (3)LWith thickness tL, step is
    The size of spar web (1) is obtained first, afterwards according to the size of spar web (1) Size calculation spar flange (2), root According to the size of the Size calculation edge strip crimp (3) of spar flange (2).
  2. 2. T tails aircraft vertical fin spar testpieces design method according to claim 1, it is characterised in that obtain spar web The dimension process of plate (1) is：The width b of spar web (1)wWith thickness twIt is identical with the parameter of former spar web (1 ').
  3. 3. T tails aircraft vertical fin spar testpieces design method according to claim 2, it is characterised in that calculate spar edge The dimension process of bar (2) is：
    A, the thickness t of spar flange (2)fIt is identical with the thickness of former spar flange (2 ') and the thickness sum of former covering (3 ')；
    B, the width b of spar flange (2)fWith effective carrying width b' of former covering (3 ')mIt is identical, i.e.,
    <mrow> <msub> <mi>b</mi> <mi>f</mi> </msub> <mo>=</mo> <msubsup> <mi>b</mi> <mi>m</mi> <mo>&amp;prime;</mo> </msubsup> <mo>=</mo> <mn>0.85</mn> <msubsup> <mi>t</mi> <mi>m</mi> <mo>&amp;prime;</mo> </msubsup> <mfrac> <msubsup> <mi>E</mi> <mi>m</mi> <mo>&amp;prime;</mo> </msubsup> <msubsup> <mi>E</mi> <mi>f</mi> <mo>&amp;prime;</mo> </msubsup> </mfrac> <msqrt> <mfrac> <msubsup> <mi>E</mi> <mi>f</mi> <mo>&amp;prime;</mo> </msubsup> <msubsup> <mi>&amp;sigma;</mi> <mrow> <mi>c</mi> <mi>o</mi> </mrow> <mo>&amp;prime;</mo> </msubsup> </mfrac> </msqrt> </mrow>
    t'mFor the thickness of former covering, E'mThe modulus of elasticity of former covering, E'fFor the modulus of elasticity of original spar flange, σ 'coFor original The unstability stress of covering.
  4. 4. T tails aircraft vertical fin spar testpieces design method according to claim 3, it is characterised in that it is curved to calculate edge strip The dimension process on side (3) is：
    The inertia of edge strip crimp (3) with area away from needing to meet following formula：
    <mfenced open = "{" close = ""> <mtable> <mtr> <mtd> <mn>2.73</mn> <mfrac> <msub> <mi>I</mi> <mi>L</mi> </msub> <mrow> <msub> <mi>b</mi> <mi>f</mi> </msub> <msup> <msub> <mi>t</mi> <mi>f</mi> </msub> <mn>3</mn> </msup> </mrow> </mfrac> <mo>-</mo> <mfrac> <msub> <mi>A</mi> <mi>L</mi> </msub> <mrow> <msub> <mi>b</mi> <mi>f</mi> </msub> <msub> <mi>t</mi> <mi>f</mi> </msub> </mrow> </mfrac> <mo>&amp;GreaterEqual;</mo> <mn>5</mn> </mtd> </mtr> <mtr> <mtd> <msub> <mi>I</mi> <mi>L</mi> </msub> <mo>=</mo> <mfrac> <msub> <mi>t</mi> <mi>L</mi> </msub> <mn>3</mn> </mfrac> <msup> <msub> <mi>b</mi> <mi>L</mi> </msub> <mn>3</mn> </msup> </mtd> </mtr> <mtr> <mtd> <mrow> <msub> <mi>A</mi> <mi>L</mi> </msub> <mo>=</mo> <msub> <mi>t</mi> <mi>L</mi> </msub> <msub> <mi>b</mi> <mi>L</mi> </msub> </mrow> </mtd> </mtr> </mtable> </mfenced>
    Wherein, ILIt is the moment of inertia of edge strip crimp, ALIt is the area that edge strip crimp contacts with former covering；
    And the Instability load of edge strip crimp (3) have to be larger than the Instability load equal to spar flange (2), i.e.,
    <mfenced open = "{" close = ""> <mtable> <mtr> <mtd> <msub> <mi>N</mi> <mi>L</mi> </msub> <mo>&amp;GreaterEqual;</mo> <msub> <mi>N</mi> <mi>f</mi> </msub> </mtd> </mtr> <mtr> <mtd> <mrow> <msub> <mi>N</mi> <mi>L</mi> </msub> <mo>=</mo> <mfrac> <mrow> <mn>12</mn> <msub> <mi>D</mi> <mrow> <mi>L</mi> <mn>66</mn> </mrow> </msub> </mrow> <mrow> <msup> <msub> <mi>b</mi> <mi>L</mi> </msub> <mn>2</mn> </msup> </mrow> </mfrac> </mrow> </mtd> </mtr> <mtr> <mtd> <mrow> <msub> <mi>N</mi> <mi>f</mi> </msub> <mo>=</mo> <mfrac> <mrow> <mn>2</mn> <msup> <mi>&amp;pi;</mi> <mn>2</mn> </msup> <msub> <mi>D</mi> <mrow> <mi>f</mi> <mn>22</mn> </mrow> </msub> </mrow> <mrow> <msup> <msub> <mi>b</mi> <mi>f</mi> </msub> <mn>2</mn> </msup> </mrow> </mfrac> <mo>&amp;lsqb;</mo> <msqrt> <mfrac> <msub> <mi>D</mi> <mrow> <mi>f</mi> <mn>11</mn> </mrow> </msub> <msub> <mi>D</mi> <mrow> <mi>f</mi> <mn>22</mn> </mrow> </msub> </mfrac> </msqrt> <mo>+</mo> <mfrac> <mrow> <mo>(</mo> <msub> <mi>D</mi> <mrow> <mi>f</mi> <mn>12</mn> </mrow> </msub> <mo>+</mo> <mn>2</mn> <msub> <mi>D</mi> <mrow> <mi>f</mi> <mn>66</mn> </mrow> </msub> <mo>)</mo> </mrow> <msub> <mi>D</mi> <mrow> <mi>f</mi> <mn>22</mn> </mrow> </msub> </mfrac> <mo>&amp;rsqb;</mo> </mrow> </mtd> </mtr> </mtable> </mfenced>
    Wherein, NLIt is edge strip crimp Instability load, NfIt is spar flange Instability load, DL66Reversed for edge strip crimp firm Degree, Df22For bending stiffness of the spar flange on parallel to spar flange direction, Df11It is spar flange parallel to spar web Bending stiffness on plate direction, Df12The coupling bending stiffness for being spar flange on above-mentioned two direction, Df66For spar flange Torsional rigidity, DL66For spar web torsional rigidity.
CN201710661314.XA 2017-08-04 2017-08-04 Design method for vertical tail wing beam test piece of T-tail aircraft Active CN107458623B (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111144049A (en) * 2019-12-24 2020-05-12 中国航空工业集团公司西安飞机设计研究所 Composite material perforated spar safety margin calculation method

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CN102944211A (en) * 2012-11-12 2013-02-27 中国航空工业集团公司西安飞机设计研究所 Method for determining area of crack arrest rib of aircraft integral wing spar
CN202869905U (en) * 2012-07-06 2013-04-10 中国航空工业集团公司西安飞机设计研究所 Aircraft wing web curved scissor test device
CN203385600U (en) * 2013-01-05 2014-01-08 中国航空工业集团公司西安飞机设计研究所 Composite beam shearing test piece
CN105620718A (en) * 2014-10-28 2016-06-01 中国航空工业集团公司西安飞机设计研究所 Integrated spar crack resistant rib

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101561365A (en) * 2009-06-04 2009-10-21 中国航空工业集团公司西安飞机设计研究所 Damage-tolerance testing method for whole wing spar of airplane
CN202869905U (en) * 2012-07-06 2013-04-10 中国航空工业集团公司西安飞机设计研究所 Aircraft wing web curved scissor test device
CN102944211A (en) * 2012-11-12 2013-02-27 中国航空工业集团公司西安飞机设计研究所 Method for determining area of crack arrest rib of aircraft integral wing spar
CN203385600U (en) * 2013-01-05 2014-01-08 中国航空工业集团公司西安飞机设计研究所 Composite beam shearing test piece
CN105620718A (en) * 2014-10-28 2016-06-01 中国航空工业集团公司西安飞机设计研究所 Integrated spar crack resistant rib

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111144049A (en) * 2019-12-24 2020-05-12 中国航空工业集团公司西安飞机设计研究所 Composite material perforated spar safety margin calculation method
CN111144049B (en) * 2019-12-24 2023-06-23 中国航空工业集团公司西安飞机设计研究所 Composite material perforated spar safety margin calculation method

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