CN104913901B - A kind of auxiliary tank of aircraft flutter model - Google Patents
A kind of auxiliary tank of aircraft flutter model Download PDFInfo
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- CN104913901B CN104913901B CN201510350395.2A CN201510350395A CN104913901B CN 104913901 B CN104913901 B CN 104913901B CN 201510350395 A CN201510350395 A CN 201510350395A CN 104913901 B CN104913901 B CN 104913901B
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Abstract
The present invention relates to Aviation Test field, and in particular to a kind of auxiliary tank of aircraft flutter model, can at least solve the problem of current flutter model has pitching and driftage modal coupling is difficult identification, stiffness tuning is inconvenient.In the auxiliary tank of aircraft flutter model of the present invention, three directional stiffness of auxiliary fuel tank model are decoupled, are easy to carry out in test flat side, driftage and the identification of three mode of pitching；Also, flat auxiliary fuel tank side, three modal frequencies of pitching and driftage are simulated respectively by three replaceable spring leafs being correspondingly arranged；The frequency of a certain mode of auxiliary fuel tank model can also be adjusted by changing spring leaf, be easy in test enter line frequency regulation for auxiliary fuel tank model, save experiment funds and time.
Description
Technical field
The present invention relates to Aviation Test field, and in particular to a kind of auxiliary tank of aircraft flutter model.
Background technology
In order to extend the flight time, aircraft can usually hang auxiliary fuel tank under the wings of an airplane, but, and the setting of auxiliary fuel tank can be to flying
The buffet characteristic of machine is produced a very large impact；Therefore, it is currently to use wind-tunnel in order to study the influence that auxiliary fuel tank is produced on the ground
Test method, and be to simulate auxiliary fuel tank with auxiliary fuel tank flutter model；When carrying out such plane flutter model design, according to
Demand may require that flat simulation auxiliary fuel tank side, three mode of pitching and driftage.
It was the rigidity in these three directions of form simulation auxiliary fuel tank for taking combination roof beam structure in the past, and can has pitching and driftage mould
The problems such as state coupling is difficult identification, stiffness tuning is inconvenient.Also, auxiliary fuel tank flutter model only simulates auxiliary fuel tank using counterweight
Quality and Inertia Characteristics, fuel oil rocks the influence to airplane flutter characteristic in consideration auxiliary fuel tank, often leads to result of the test
Accuracy.
The content of the invention
The invention aims to solve at least one above-mentioned technical problem, there is provided a kind of auxiliary tank of aircraft flutter mould
Type.
The technical scheme is that：
A kind of auxiliary tank of aircraft flutter model, including：
General hanger beam, edge has respectively perpendicular to the general hanger beam axis direction at the top surface of its two ends end
Prominent the first fixed part and the second fixed part, the remote general hanger beam of first fixed part and the second fixed part
One end is respectively hinged at the bottom of wing model, and the axis of the rotation axis of two pin joints with the general hanger beam is put down
OK, and the rotation axis of described two pin joints extended line overlap；
Side coach spring piece, it is plate-like, between first fixed part and the second fixed part, with first fixed part
Parallel with the second fixed part, described side coach spring piece one end is removably attached on the general hanger beam, and the other end is removable
It is fixed on the bottom of the wing model with unloading；
Special hanging is set a roof beam in place, with general hanger Liangping row；
Rotating arm, including first connecting portion and second connecting portion, the first connecting portion are hinged on the hanging rack special
Back portion centre position, axis and institute that the rotation axis of the first connecting portion pin joint is set a roof beam in place also cross the Special hanging
The axis of general hanger beam, and the axis set a roof beam in place perpendicular to the Special hanging are stated, the second connecting portion is hinged on described general
Hanger beam bottom, the rotation axis of the second connecting portion pin joint is perpendicular to the axis of the general hanger beam and described special
The plane that the axis of hanger beam is constituted；
Driftage spring leaf, plate-like, one end is removably attached to being fixed with described first for the general hanger beam
One end end in portion, the other end of the driftage spring leaf is removably attached in connection sheet, the axle of the driftage spring leaf
The diameter parallel of line and the general hanger beam, and projection of the axis on the Special hanging is set a roof beam in place of the driftage spring leaf with
The axis that the Special hanging is set a roof beam in place is overlapped；
Pitching spring leaf, takes the shape of the letter U, including parallel the first shell fragment and the second shell fragment, and the bottom of first shell fragment can
Releasably it is fixed in the connection sheet, second shell fragment is removably attached on the Special hanging sets a roof beam in place, and described
One shell fragment and general hanger Liangping row；
Auxiliary fuel tank model, is fixedly installed on the Special hanging by first support arm and second support arm and sets a roof beam in place bottom, the pair
The axis that projection of the axis of tank model on the Special hanging is set a roof beam in place is set a roof beam in place with the Special hanging is overlapped, and the auxiliary fuel tank
There is fuel chamber, the side of the auxiliary fuel tank model has the through hole connected with the fuel chamber inside model, for oiling or
Oil extraction.
Alternatively, the bottom of the wing model is fixedly installed two bearings, described the first of the general hanger beam
Fixed part and the second fixed part are respectively hinged on described two bearings.
Alternatively, the second connecting portion of the rotating arm the general hanger beam bottom position of articulating point, positioned at institute
State on the general hanger beam between the first fixed part and the side coach spring piece.
Alternatively, the second shell fragment of the pitching spring leaf is removably attached to the hanging rack special by spring arms
Liang Shang.
Alternatively, the U-shaped opening of the pitching spring leaf is towards the rotating arm.
Alternatively, tie point position of the second shell fragment of the pitching spring leaf on the Special hanging is set a roof beam in place and described
Position of articulating point of the first connecting portion of rotating arm on the Special hanging is set a roof beam in place, is respectively positioned on the first support arm and described
Between tie point position of two support arms on the Special hanging is set a roof beam in place.
Alternatively, the auxiliary fuel tank model includes the axle of the nested shell and interior case installed, the shell and the interior case
Line is overlapped, and the fuel chamber is located in the interior case；
Two snap rings are provided between the shell and the interior case, two snap rings, which are fixed, is set in the interior case outer ring surface
On, the first support arm and second support arm are fixedly connected with described two snap rings respectively after running through the shell, and described outer
The part being in contact between shell and the first support arm and second support arm is fixedly connected.
Alternatively, the side through hole of the auxiliary fuel tank model runs through the shell, and is provided with lid and is sealed.
Beneficial effects of the present invention：
In the auxiliary tank of aircraft flutter model of the present invention, by the way that three directional stiffness of auxiliary fuel tank model are decoupled, just
In carrying out in test side flat, driftage and the identification of three mode of pitching；Also, it is also replaceable by three be correspondingly arranged
Spring leaf simulate auxiliary fuel tank side flat, three modal frequencies of pitching and driftage respectively, pair can be adjusted by changing spring leaf
The frequency of a certain mode of tank model, is easy in test enter line frequency regulation for auxiliary fuel tank model, saves experiment funds
And the time.
Brief description of the drawings
Fig. 1 is the structural representation for the auxiliary tank of aircraft flutter model that the present invention is not provided with auxiliary fuel tank model；
Fig. 2 is the structural representation of auxiliary tank of aircraft flutter model of the present invention；
Fig. 3 is the structural representation of the auxiliary fuel tank model of an embodiment of the present invention.
Embodiment
Here exemplary embodiment will be illustrated in detail, its example is illustrated in the accompanying drawings.Following description is related to
During accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawings represent same or analogous key element.
As depicted in figs. 1 and 2, the auxiliary tank of aircraft flutter model that the present invention is provided, including general hanger beam 1, Special hanging
Set a roof beam in place 3, auxiliary fuel tank model 8 and the side coach spring piece 2 that is disposed there between, rotating arm 4, driftage and are bowed at spring leaf 5
Face upward the grade part of spring leaf 7.
General hanger beam 1 can use a variety of suitable structures, and along perpendicular to the axis direction of general hanger beam 1 at it
There is prominent the first fixed part 11 and the second fixed part 12 respectively at the top surface of two ends end.Wherein, the He of the first fixed part 11
One end of the remote general hanger beam 1 of second fixed part 12 is respectively hinged at the bottom of wing model (not shown), and two are hinged
Diameter parallel of the rotation axis of point with general hanger beam 1, and the extended line coincidence of the rotation axis of two pin joints.Need
Illustrate, being hinged for being mentioned in the present invention can for example use bearing pin using a variety of known suitable structure types
The mode that (rotary shaft) is engaged with bearing, concrete structure is repeated no more；In addition, above-mentioned rotation axis refers to the axle of above-mentioned bearing pin
Line.
Further, two bearings 13 can also be fixedly installed in the bottom of wing model, the first of general hanger beam 1 consolidates
Determine the fixed part 12 of portion 11 and second to be respectively hinged on two bearings 13.
Side coach spring piece 2 is plate-like, between the first fixed part 11 and the second fixed part 12, with the first fixed part 11 and
Second fixed part 12 is parallel；The one end of side coach spring piece 2 be bolted etc. removably (subsequently mention " removably
It is fixed " structure all same) it is fixed on general hanger beam 1, the other end is equally the bottom for being removably attached to wing model.
Wherein, side coach spring piece 2 is mainly used in simulating the flat modal frequency in auxiliary fuel tank side, can be adjusted by more side change coach spring piece 2
The frequency of a certain mode of auxiliary fuel tank model 8, is easy in test enter line frequency regulation for auxiliary fuel tank model 8.
Special hanging set a roof beam in place 3 can use a variety of suitable structures, it is parallel with general hanger beam 1.
Rotating arm 4 includes first connecting portion 41 and second connecting portion 42, and first connecting portion 41 can be perpendicular to second
Connecting portion 42.First connecting portion 41 is hinged on Special hanging and set a roof beam in place 3 crown center positions, the rotary shaft of the pin joint of first connecting portion 41
Line is set a roof beam in place 3 axis and the axis of general hanger beam 1 also cross Special hanging, and set a roof beam in place perpendicular to Special hanging 3 axis.Second
Connecting portion 42 is hinged on the bottom of general hanger beam 1, and the rotation axis of the pin joint of second connecting portion 42 is perpendicular to general hanger beam 1
Axis and Special hanging set a roof beam in place 3 axis constitute plane.
In addition, position of articulating point of the second connecting portion 42 of rotating arm 4 in the bottom of general hanger beam 1, is fixed positioned at first
On general hanger beam 1 between portion 11 and side coach spring piece 2.
Going off course, spring leaf 5 is plate-like, and one end is removably attached to one with the first fixed part 11 of general hanger beam 1
End is held, the other end of driftage spring leaf 5 is removably attached in connection sheet 6；In addition, the axis of driftage spring leaf 5 is with leading to
With the diameter parallel of hanger beam 1, and driftage spring leaf 5 the projection set a roof beam in place on 3 in Special hanging of axis and Special hanging set a roof beam in place 3 axle
Line is overlapped.Wherein, driftage spring leaf 5 is mainly used in simulation auxiliary fuel tank driftage modal frequency, can be by changing driftage spring leaf 5
And the frequency of a certain mode of auxiliary fuel tank model 8 is adjusted, it is easy in test enter line frequency regulation for auxiliary fuel tank model 8.
Pitching spring leaf 7 takes the shape of the letter U, including parallel the first shell fragment 71 and the second shell fragment 72, the first shell fragment 71 and second
Shell fragment 72 is attached by U-shaped portion.The bottom of first shell fragment 71 is removably attached in connection sheet 6, and the second shell fragment 72 can
Special hanging is releasably fixed on to set a roof beam in place on 3, and the first shell fragment 71 is parallel with the general hanger beam 1；In addition, pitching spring leaf 7
U-shaped opening towards rotating arm 4.Wherein, connection sheet 6 can use a variety of suitable structures.Further, pitching spring leaf 7
The second shell fragment 72 be removably attached to Special hanging by spring arms 73 and set a roof beam in place on 3, and the liquid of spring arms 73 can be used
A variety of suitable structures.
Auxiliary fuel tank model 8 is used to simulate auxiliary tank of aircraft structure, can be using known a variety of suitable structures；Auxiliary fuel tank
Model 8 is to be fixedly installed on Special hanging by first support arm and second support arm 82 to set a roof beam in place 3 bottoms, and the axis of auxiliary fuel tank model 8 exists
Set a roof beam in place 3 axis of the projection that the Special hanging is set a roof beam in place on 3 and the Special hanging is overlapped.And the inside of auxiliary fuel tank model 8 has fuel oil
Chamber, the side of auxiliary fuel tank model 8 has the through hole connected with fuel chamber, for oiling or oil extraction.
Second shell fragment 72 of pitching spring leaf 7 sets a roof beam in place the first of tie point position on 3 and rotating arm 4 in Special hanging
Connecting portion 41 is set a roof beam in place the position of articulating point on 3 in Special hanging, is respectively positioned on first support arm and second support arm 82 and is set a roof beam in place in Special hanging on 3
Tie point position between.
Further, auxiliary fuel tank model 8 includes the axle of the nested shell 85 and interior case 83 installed, shell 85 and the interior case 83
Line is overlapped, and fuel chamber is located in interior case 83.
Two snap rings 84 are provided between shell 85 and interior case 83, two snap rings 84, which are fixed, is set in the interior outer ring surface of case 83
On；First support arm and second support arm 82 are fixedly connected with two snap rings 84 respectively after running through shell 85, and shell 85 and first
The part being in contact between support arm and second support arm 82 is fixedly connected.The side through hole of auxiliary fuel tank model 8 runs through shell 85,
And be provided with lid 86 and sealed, while the number of fuel oil can be adjusted to meet the demand of different tests state.
In addition, as shown in figure 3, in the outside of each snap ring 84 of the interior outer ring surface of case 83 snap ring 84 can also be set again respectively,
For example both sides respectively set one, that is, come to and be attached between four, and four snap rings 84 by ribs 87, and increase is stable
Performance.
In the auxiliary tank of aircraft flutter model of the present invention, whole experiment flutter model is fixed on wing model by bearing 13
On, general hanger beam 1 is hinged by the flat rotary shaft in side and bearing 13, and general hanger beam 1 can be around the flat rotary shaft rotation in side, simulation
The side flat-die state of auxiliary fuel tank, and provided using side coach spring piece 2 side square to rigidity；The upper end of rotating arm 4 passes through pitching
Rotary shaft is hinged with general hanger beam 1, and lower end is set a roof beam in place by go off course rotary shaft and Special hanging and 3 is hinged, so that by being revolved around driftage
Rotating shaft and the rotation of pitching the rotary shaft driftage of simulation auxiliary fuel tank and pitching mode respectively, it is corresponding spring leaf 5 and to be bowed using going off course
Spring leaf 7 is faced upward to provide the rigidity of driftage and pitch orientation.
In the auxiliary tank of aircraft flutter model of the present invention, each pin joint of general hanger beam 1 is arranged on different positions, from
And decoupled 8 three directional stiffness of auxiliary fuel tank model, it is easy to carry out in test flat side, driftage and three mode of pitching
Identification；Also, also flat auxiliary fuel tank side, pitching and driftage three are simulated respectively by three replaceable spring leafs being correspondingly arranged
Individual modal frequency, can also adjust the frequency of a certain mode of auxiliary fuel tank model 8 by changing spring leaf, be easy in test pin
Efficiently frequency regulation is carried out to auxiliary fuel tank model 8, experiment funds and time is saved；Finally, moreover it is possible to by auxiliary fuel tank mould
Fuel oil is injected in type 8, to verify that auxiliary fuel tank fuel oil rocks the influence to airplane flutter characteristic so that the accuracy of result of the test is more
It is high.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (8)
1. a kind of auxiliary tank of aircraft flutter model, it is characterised in that including：
General hanger beam (1), edge has respectively perpendicular to general hanger beam (1) axis direction at the top surface of its two ends end
Have prominent the first fixed part (11) and the second fixed part (12), first fixed part (11) and the second fixed part (12) it is remote
One end from the general hanger beam (1) is respectively hinged at the bottom of wing model, and the rotation axis of two pin joints is and institute
The diameter parallel of general hanger beam (1) is stated, and the extended line of the rotation axis of described two pin joints is overlapped；
Side coach spring piece (2), it is plate-like, between first fixed part (11) and the second fixed part (12), with described
One fixed part (11) is parallel with the second fixed part (12), and described side coach spring piece (2) one end is removably attached to described general
On hanger beam (1), the other end is removably attached to the bottom of the wing model；
Special hanging is set a roof beam in place (3), parallel with the general hanger beam (1)；
Rotating arm (4), including first connecting portion (41) and second connecting portion (42), the first connecting portion (41) are hinged on institute
Special hanging is stated to set a roof beam in place (3) crown center position, the rotation axis of first connecting portion (41) pin joint also cross it is described specially
With the axis and the axis of the general hanger beam (1) of hanger beam (3), and the axis of (3) of setting a roof beam in place perpendicular to the Special hanging, institute
State second connecting portion (42) and be hinged on general hanger beam (1) bottom, the rotary shaft of second connecting portion (42) pin joint
Line perpendicular to the axis and the Special hanging of the general hanger beam (1) set a roof beam in place (3) axis constitute plane；
Driftage spring leaf (5), plate-like, one end is removably attached to consolidating with described first for the general hanger beam (1)
Determine one end end in portion (11), the other end of the driftage spring leaf (5) is removably attached in connection sheet (6), it is described inclined
The diameter parallel of the axis of bomb reed (5) and the general hanger beam (1), and the driftage spring leaf (5) axis in institute
Set a roof beam in place with the Special hanging axis of (3) of the projection that Special hanging sets a roof beam in place on (3) is stated to overlap；
Pitching spring leaf (7), takes the shape of the letter U, including parallel the first shell fragment (71) and the second shell fragment (72), first shell fragment
(71) bottom is removably attached in the connection sheet (6), and second shell fragment (72) is removably attached to described special
With on hanger beam (3), and first shell fragment (71) is parallel with the general hanger beam (1)；
Auxiliary fuel tank model (8), is fixedly installed on the Special hanging by first support arm and second support arm (82) and sets a roof beam in place (3) bottom,
The projection that the axis of the auxiliary fuel tank model (8) is set a roof beam in place on (3) in the Special hanging and the Special hanging are set a roof beam in place the axis weight of (3)
Close, and there is fuel chamber inside the auxiliary fuel tank model (8), the side of the auxiliary fuel tank model (8) has and the fuel chamber
The through hole of connection, for oiling or oil extraction.
2. auxiliary tank of aircraft flutter model according to claim 1, it is characterised in that the bottom of the wing model is fixed
Two bearings (13) are provided with, first fixed part (11) of the general hanger beam (1) and the second fixed part (12) are respectively
It is hinged on described two bearings (13).
3. auxiliary tank of aircraft flutter model according to claim 1 or 2, it is characterised in that the of the rotating arm (4)
Two connecting portions (42) general hanger beam (1) bottom position of articulating point, positioned at first fixed part (11) and the side
On the general hanger beam (1) between coach spring piece (2).
4. auxiliary tank of aircraft flutter model according to claim 3, it is characterised in that the of the pitching spring leaf (7)
Two shell fragments (72) are removably attached to the Special hanging by spring arms (73) and set a roof beam in place on (3).
5. auxiliary tank of aircraft flutter model according to claim 4, it is characterised in that the U-shaped of the pitching spring leaf (7)
It is open towards the rotating arm (4).
6. auxiliary tank of aircraft flutter model according to claim 5, it is characterised in that the of the pitching spring leaf (7)
Two shell fragments (72) are set a roof beam in place the tie point position on (3) and the first connecting portion of the rotating arm (4) in the Special hanging
(41) set a roof beam in place the position of articulating point on (3) in the Special hanging, be respectively positioned on the first support arm and set a roof beam in place in the Special hanging on (3)
Between the tie point position that tie point position and the second support arm (82) are set a roof beam in place in the Special hanging on (3).
7. auxiliary tank of aircraft flutter model according to claim 6, it is characterised in that the auxiliary fuel tank model (8) includes
The axis of shell (85) and interior case (83) that nesting is installed, the shell (85) and the interior case (83) is overlapped, the fuel chamber
In the interior case (83)；
Two snap rings (84) are provided between the shell (85) and the interior case (83), two snap ring (84) fixations are set in institute
State on interior case (83) outer ring surface, the first support arm and second support arm (82) are run through after the shell (85) respectively with described two
Individual snap ring (84) is fixedly connected, and the part being in contact between the shell (85) and the first support arm and second support arm (82)
It is fixedly connected.
8. auxiliary tank of aircraft flutter model according to claim 7, it is characterised in that the side of the auxiliary fuel tank model (8)
Through hole described in face runs through the shell (85), and is provided with lid (86) and is sealed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510350395.2A CN104913901B (en) | 2015-06-23 | 2015-06-23 | A kind of auxiliary tank of aircraft flutter model |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510350395.2A CN104913901B (en) | 2015-06-23 | 2015-06-23 | A kind of auxiliary tank of aircraft flutter model |
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| Publication Number | Publication Date |
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| CN104913901A CN104913901A (en) | 2015-09-16 |
| CN104913901B true CN104913901B (en) | 2017-11-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510350395.2A Active CN104913901B (en) | 2015-06-23 | 2015-06-23 | A kind of auxiliary tank of aircraft flutter model |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105509992A (en) * | 2015-11-27 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | External store model system excitation method for flutter wind tunnel test |
| CN106226025A (en) * | 2016-07-05 | 2016-12-14 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of wing store Combinations flutter wind tunnel analog |
| CN108681624A (en) * | 2018-04-19 | 2018-10-19 | 同济大学 | A kind of new construction fuel tank shaking emulation mode based on fluent softwares |
| CN113415432A (en) * | 2021-07-30 | 2021-09-21 | 天津爱思达新材料科技有限公司 | Plane auxiliary fuel tank stabilizing surface structure |
| CN113532785B (en) * | 2021-08-08 | 2022-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Dynamic control device for simulating suspension stiffness of external hanging object under flutter wind tunnel test wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4682494A (en) * | 1986-07-30 | 1987-07-28 | The United States Of America As Represented By The Administrator Of The National Aeronautics & Space Administration | Airfoil flutter model suspension system |
| CN101509825A (en) * | 2009-03-13 | 2009-08-19 | 西安交通大学 | Aeroplane buffet air tunnel model integration design and manufacturing method |
| CN104048809A (en) * | 2014-05-06 | 2014-09-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-freedom-degree simulation external store flutter model for wind tunnel test |
| CN204214631U (en) * | 2014-05-06 | 2015-03-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test Three Degree Of Freedom simulation store Combinations flutter model |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012078260A (en) * | 2010-10-04 | 2012-04-19 | Mitsubishi Heavy Ind Ltd | Wind tunnel test model and method for wind tunnel test |
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2015
- 2015-06-23 CN CN201510350395.2A patent/CN104913901B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4682494A (en) * | 1986-07-30 | 1987-07-28 | The United States Of America As Represented By The Administrator Of The National Aeronautics & Space Administration | Airfoil flutter model suspension system |
| CN101509825A (en) * | 2009-03-13 | 2009-08-19 | 西安交通大学 | Aeroplane buffet air tunnel model integration design and manufacturing method |
| CN104048809A (en) * | 2014-05-06 | 2014-09-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-freedom-degree simulation external store flutter model for wind tunnel test |
| CN204214631U (en) * | 2014-05-06 | 2015-03-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test Three Degree Of Freedom simulation store Combinations flutter model |
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| CN104913901A (en) | 2015-09-16 |
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