CN106525388A - Rotor type aircraft water landing model test method - Google Patents
Rotor type aircraft water landing model test method Download PDFInfo
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- CN106525388A CN106525388A CN201610970051.6A CN201610970051A CN106525388A CN 106525388 A CN106525388 A CN 106525388A CN 201610970051 A CN201610970051 A CN 201610970051A CN 106525388 A CN106525388 A CN 106525388A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M10/00—Hydrodynamic testing; Arrangements in or on ship-testing tanks or water tunnels
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Abstract
The invention provides a rotor type aircraft water landing model test method. Firstly, a test device is installed, and electrical signal connection and test are completed. Then, a hydrodynamic high speed test trailer moves in an orbit and drives a model to move, when the speed of the model reaches the running speed required by the test and is stable, data acquisition equipment is started, after the normal working of the data acquisition equipment is determined, a model connection component is controlled to loosen the model, and the model freely separates and goes into water to slide. After the model goes into the water, the hydrodynamic high speed test trailer brakes and slows down until parking. After the test process is ended, the effectiveness of collected test data is analyzed, valid test parameters are recorded, and the valid test parameters comprises model weight, center of gravity, forward speed and sinking speed at the instant of going into water, a pitch angle, a roll angle and a yaw angle in a model initial state, and a pitch angle, a roll angle and a yaw angle, overload of center of gravity, cockpit overload, bottom pressure of the model after the model goes into the water. According to the method, a reliable basis is provided for effectively evaluating the water landing performance of a rotor type aircraft.
Description
Technical field
The present invention relates to rotor class aircraft testing technical field, specially a kind of rotor class aircraft ditching model test
Method.
Background technology
Rotor class aircraft usually completes takeoff and landing by land, however, pushing away with rotor class aircraft utilization scope
Extensively, it is more and more come the situation gone on patrol, rescue using rotor class aircraft at sea.When rotor class aircraft breaks down, just need
Ditching to be carried out on sea.、
Ditching behavior is one of important hydrodynamic(al) performance of rotor class aircraft, directly affects rotor class aircraft ditching
Safety afterwards.When helicopter is met an urgent need force-lands water, the shock loading of generation can cause the dynamic response of aircaft configuration, mainly deposit
It is three aspects：On the one hand make shock zone bear huge pressure, partial structurtes may be caused to destroy；On the other hand will draw
The violent tremor of whole fuselage is played, larger moment of flexure is produced, when which is superimposed with low frequency wave bending moment, fuselage may be caused always to indulge
The forfeiture of intensity；The third aspect is that excessive vertical acceleration and violent pitching can bring serious life to crew
, there is the phenomenons such as dizzy, vomiting, reduce the escape ability of crew and occupant after ditching in the discomfort in reason.In order to comment
Sentence the ditching behavior of rotor class aircraft, most credible, effective method is water test to be carried out using the scale model of real machine,
Measure the parameter such as the angle of pitch of model, roll angle, yaw angle, center of gravity overload, driving cabin overload, base pressure during water
Changing value.
There is presently no a kind of rotor class aircraft ditching model test method of practicality.
The content of the invention
For the problem that prior art is present, the present invention proposes a kind of rotor class aircraft ditching model test side
Method.
The technical scheme is that：
A kind of rotor class aircraft ditching model test method, it is characterised in that：Comprise the following steps：
Step 1：Installation test device simultaneously completes electric signal connection and test；
The assay device include rotor class model aircraft (1), hydrodynamic force high-speed test (HST) trailer (13), survey bridge (12), three
Degree of freedom deflection component, model connection member and sensing system；
Three Degree Of Freedom deflection component is fixed on the survey bridge below hydrodynamic force high-speed test (HST) trailer (13) by pipe fitting (11)
(12) on；Model connection member is rigidly fixed and is connected to below Three Degree Of Freedom deflection component；Rotor class model aircraft (1) is rigidly solid
It is scheduled on below model connection member, and model connection member controlled can releases rotor class model aircraft (1)；
Sensing system includes gyroscope (15), acceleration transducer (16) and pressure transducer (17)；Gyroscope (15)
It is fixed on the center of gravity of rotor class model aircraft (1)；Acceleration transducer (16) is fixed in rotor class model aircraft (1)；Pressure
Force transducer (17) is arranged in rotor class model aircraft (1) fuselage lower surface；
Step 2：Rotor class model aircraft (1) motion is driven when hydrodynamic force high-speed test (HST) trailer (13) is moved in orbit,
When rotor class model aircraft (1) speed to test requirements document the speed of service and it is stable after, log-on data collecting device determines number
According to collecting device it is working properly after, Controlling model connection member releases rotor class model aircraft (1), rotor class model aircraft (1)
Freely depart from and be incorporated to neatly row；After model water, hydrodynamic force high-speed test (HST) trailer (13) brake deceleration is until stop；
Step 3：The test data effectiveness of collection after process of the test terminates, is analyzed, invalid data is rejected, then record has
The test parameterss of effect, including model weight, position of centre of gravity, the forward flight speed and subsidence velocity of instant water, model primitive
Under the angle of pitch, roll angle, yaw angle, the angle of pitch of model after water, roll angle, yaw angle, center of gravity overload, driving cabin mistake
Load, base pressure.
Further preferred version, a kind of rotor class aircraft ditching model test method, it is characterised in that：Examination
In experiment device Three Degree Of Freedom deflection component include yaw angle adjusting means (10), angle of pitch adjusting means (9), upper junction plate (8),
Roll angle adjusting means (7)；Yaw angle adjusting means (10) is affixed with pipe fitting (11)；Yaw angle adjusting means (10) and the angle of pitch
Adjusting means (9) connects, and angle of pitch adjusting means (9) is fixedly connected with upper junction plate (8), and upper junction plate (8) is adjusted with roll angle
Regulating device (7) is fixedly connected；Roll angle adjusting means (7) is fixedly connected model connection member.
Further preferred version, a kind of rotor class aircraft ditching model test method, it is characterised in that：Examination
In experiment device model connection member include middle connecting plate (6), lower connecting plate (2), two positioning seats (3), two pieces of location-plates (5) and
Flexible attachment components；
Lower connecting plate (2) is rigidly fixed with model and is connected；Middle connecting plate (6) is fixed with roll angle adjusting means (7) lower end
Connection；
Two positioning seats are fixedly mounted on the upper surface of lower connecting plate (2), and V-groove, two V-types are provided with two positioning seats
Groove is mutually perpendicular to, and a V-groove is along model longitudinal direction；There is the V-type projection that can coordinate with V-groove location-plate lower end, and two pieces fixed
Position plate upper end is fixed on middle connecting plate (6), the V-groove corresponding matching that lower end can respectively with two positioning seats；
Flexible attachment components include suspension ring, detacher, regulating bolt and guide finger；Suspension ring are fixedly mounted on lower connecting plate
(2) upper surface, detacher can coordinate lifting, detacher upper end and the regulation spiral shell being arranged on middle connecting plate (6) with suspension ring
Tether and connect, and can coordinate with the guide finger being fixed on middle connecting plate (6).
Further preferred version, a kind of rotor class aircraft ditching model test method, it is characterised in that：Partially
Boat angle adjusting means (10) is including yaw rotation plate and pinboard；Yaw rotation plate upper surface can be with pipe fitting secure fit；Turn
Fishplate bar is fixed by orthogonal upper board and lower panel and is constituted；Pinboard upper board pastes merga pass first with yaw rotation plate
Rotating shaft connects, and pinboard upper board can be rotated relative to yaw rotation plate around first rotating shaft, and can be fixed by locking mechanism
Rotational angle；Graduation mark of the labelling around first rotating shaft rotational angle is carved with yaw rotation plate and/or pinboard upper board；
Angle of pitch adjusting means (9) is including pitch rotation plate；Pitch rotation plate is by orthogonal upper board and lower panel
Fixed composition；Pitch rotation plate upper board is connected with patch the second rotating shaft of merga pass of pinboard lower panel, pitch rotation plate top
Plate can be rotated relative to pinboard lower panel around the second rotating shaft, and can fix rotational angle by locking mechanism；Pitch rotation
Graduation mark of the labelling around the second axis of rotation angle is carved with plate upper board and/or pinboard lower panel；
Pitch rotation plate lower panel is fixedly connected with upper junction plate (8)；
Roll angle adjusting means (7) rotates outer panel including rolling and rolling rotates interior plate；
Upper junction plate (8) rotates outer panel with rolling and is mutually perpendicular to and is fixedly connected；Rolling rotates interior plate and middle connection
Plate (6) is fixedly connected；Rolling is rotated outer panel and is connected with rolling rotation interior plate patch the 3rd rotating shaft of merga pass, and rolling rotates interior
Side plate can rotate outer panel around the 3rd rotating shaft relative rolling and rotate, and can fix rotational angle by locking mechanism；Rolling
Rotate outer panel and/or rolling to be rotated and graduation mark of the labelling around the 3rd axis of rotation angle is carved with interior plate.
Further preferred version, a kind of rotor class aircraft ditching model test method, it is characterised in that：Two
The rolling that group cooperates rotates outer panel and rolling rotates interior plate and is separately fixed at upper junction plate (8) along model longitudinal direction
Rear and front end, and two group of the 3rd rotating shaft is coaxial.
Beneficial effect
Using method of the invention, it is possible to effectively and accurately measuring angle of pitch during rotor class aircraft ditching, roll
The parameter such as angle, yaw angle, center of gravity overload, driving cabin overload, base pressure, is the ditching for effectively passing judgment on rotor class aircraft
Performance provides believable foundation.
The additional aspect and advantage of the present invention will be set forth in part in the description, and partly will become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become from the description with reference to accompanying drawings below to embodiment
It is substantially and easy to understand, wherein：
Fig. 1：The structural representation of the present invention；
Fig. 2：Assay device and helicopter model structural representation；
Fig. 3：Assay device structural representation.
Wherein：1st, rotor class model aircraft；2nd, lower connecting plate；3rd, positioning seat；4th, detacher；5th, location-plate；6th, middle connection
Plate；7th, roll angle adjusting means；8th, upper junction plate；9th, angle of pitch adjusting means；10th, yaw angle adjusting means；11st, pipe fitting；12、
Survey bridge；13rd, hydrodynamic force high-speed test (HST) trailer；15th, gyroscope；16th, acceleration transducer；17th, pressure transducer.
Specific embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from start to finish
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and be not considered as limiting the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", " length ", " width ",
" thickness ", " on ", D score, "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " is, based on orientation shown in the drawings or position relationship, to be for only for ease of
The description present invention and simplified description, rather than indicate or imply that the device or element of indication must have specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are only used for describing purpose, and it is not intended that indicating or implying relative importance
Or the implicit quantity for indicating indicated technical characteristic.Therefore, define " first ", the feature of " second " can express or
Implicitly include one or more this feature.In describing the invention, " multiple " are meant that two or more,
Unless otherwise expressly limited specifically.
The purpose of the present invention is to propose to a kind of rotor class aircraft ditching model test method, is to pass judgment on rotor class aircraft
Ditching behavior a kind of effective, believable means are provided.
The method is comprised the following steps：
Step 1：Installation test device simultaneously completes electric signal connection and test；
As shown in figure 1, the assay device includes rotor class model aircraft 1, hydrodynamic force high-speed test (HST) trailer 13, surveys bridge
12nd, Three Degree Of Freedom deflection component, model connection member and sensing system.
Three Degree Of Freedom deflection component is fixed on the survey bridge 12 below hydrodynamic force high-speed test (HST) trailer 13 by pipe fitting 11；Mould
Type connection member is rigidly fixed and is connected to below Three Degree Of Freedom deflection component；Rotor class model aircraft 1 is rigidly fixed in model company
Below relay part, and model connection member controlled can release rotor class model aircraft 1.
Three Degree Of Freedom deflection component in assay device includes yaw angle adjusting means 10, angle of pitch adjusting means 9, upper company
Fishplate bar 8, roll angle adjusting means 7；Yaw angle adjusting means 10 is affixed with pipe fitting 11；Yaw angle adjusting means 10 is adjusted with the angle of pitch
Regulating device 9 connects, and angle of pitch adjusting means 9 is fixedly connected with upper junction plate 8, and upper junction plate 8 is fixed with roll angle adjusting means 7
Connection；Roll angle adjusting means 7 is fixedly connected model connection member.
Yaw angle adjusting means 10 includes yaw rotation plate and pinboard；Yaw rotation plate upper surface can be fixed with pipe fitting
Coordinate；Pinboard is fixed by orthogonal upper board and lower panel and is constituted；Pinboard upper board is fitted simultaneously with yaw rotation plate
Connected by first rotating shaft, pinboard upper board can be rotated relative to yaw rotation plate around first rotating shaft, and can be by locking
Rotational angle is fixed by mechanism；Quarter of the labelling around first rotating shaft rotational angle is carved with yaw rotation plate and/or pinboard upper board
Degree line.
In the present embodiment, when carrying out ditching and testing, first rotating shaft central axis crosses model center of gravity, pinboard it is upper
Portion's plate is rotated relative to yaw rotation plate around first rotating shaft, after the rotational angle for requiring is realized according to graduation mark, can be by fastening
The upper board of pinboard is fixed by bolt with yaw rotation plate, realizes yaw steering requirement.
Angle of pitch adjusting means 9 includes pitch rotation plate；Pitch rotation plate is solid by orthogonal upper board and lower panel
It is fixed to constitute；Pitch rotation plate upper board is connected with patch the second rotating shaft of merga pass of pinboard lower panel, pitch rotation plate upper board
Can rotate relative to pinboard lower panel around the second rotating shaft, and rotational angle can be fixed by locking mechanism；Pitch rotation plate
Graduation mark of the labelling around the second axis of rotation angle is carved with upper board and/or pinboard lower panel；
In the present embodiment, when ditching test is carried out, the second spindle central axis is hung down with first rotating shaft central axis
It is straight intersecting.Pitch rotation plate upper board is rotated relative to pinboard lower panel around the second rotating shaft, when what is required according to graduation mark realization
After rotational angle, locked by the second rotating shaft itself, pitch rotation plate upper board is fixed with pinboard lower panel, pitching is realized
Adjustment requirement.
Pitch rotation plate lower panel is fixedly connected with upper junction plate 8.
Roll angle adjusting means 7 includes that rolling rotates outer panel and rolling rotates interior plate；Upper junction plate 8 is rotated with rolling
Outer panel is mutually perpendicular to and is fixedly connected；Rolling is rotated interior plate and is fixedly connected with middle connecting plate 6；Rolling rotates outer panel with horizontal stroke
Rocking-turn dynamic interior plate patch merga pass the 3rd rotating shaft connection, rolling rotate interior plate and can rotate outer around the 3rd rotating shaft relative rolling
Side plate is rotated, and can fix rotational angle by locking mechanism；Rolling rotates outer panel and/or rolling is rotated
There is graduation mark of the labelling around the 3rd axis of rotation angle.
As shown in figure 3, rotating outer panel and rolling rotation inner side with two groups of rolling for cooperating in the present embodiment
Plate, two groups of structures are separately mounted to rear and front end of the upper junction plate 8 along model longitudinal direction, and the 3rd rotating shaft in two groups of structures is same
Axle.Rolling rotates interior plate and rotates outer panel rotation around the 3rd rotating shaft relative rolling, when the rotation for realizing requiring according to graduation mark
After angle, locked by the 3rd rotating shaft itself, rolling is rotated into interior plate and is fixed with rolling rotation outer panel, realize that rolling is adjusted
Require.
As shown in figure 3, the model connection member in assay device includes middle connecting plate 6,2, two positioning seats of lower connecting plate
3rd, two pieces of location-plates 5 and flexible attachment components.
Lower connecting plate 2 is rigidly fixed with model and is connected；Middle connecting plate 6 is fixedly connected with 7 lower end of roll angle adjusting means.
Two positioning seats are fixedly mounted on the upper surface of lower connecting plate 2, and V-groove, two V-grooves are provided with two positioning seats
It is mutually perpendicular to, and a V-groove is along model longitudinal direction；Location-plate lower end has the V-type that can coordinate with V-groove raised, two pieces of positioning
Plate upper end is fixed on middle connecting plate 6, the V-groove corresponding matching that lower end can respectively with two positioning seats.
Flexible attachment components include suspension ring, detacher, regulating bolt and guide finger；Suspension ring are fixedly mounted on lower connecting plate 2
Upper surface, detacher can with suspension ring coordinate lift, detacher upper end be arranged on middle connecting plate 6 on regulating bolt connect
Connect, and can coordinate with the guide finger being fixed on middle connecting plate 6.
When ditching test is carried out, the space angle of model may insure by positioning seat, location-plate and guide finger
It is consistent with assay device space angle, reach regulation purpose.
Sensing system includes gyroscope 15, acceleration transducer 16 and pressure transducer 17；Gyroscope 15 is fixed on rotation
The center of gravity of wing class model aircraft 1；Acceleration transducer 16 is fixed in rotor class model aircraft 1；Pressure transducer 17 is arranged
In 1 fuselage lower surface of rotor class model aircraft.
Ensure that by said apparatus and adjust within the specific limits the angle of pitch of rotor class model aircraft, roll angle, partially
Boat angle and away from water surface elevation, and the test parameterss needed for obtaining can be measured.
Step 2：Hydrodynamic force high-speed test (HST) trailer 13 drives rotor class model aircraft 1 to move when moving in orbit, works as rotation
The speed of wing class model aircraft 1 to test requirements document the speed of service and it is stable after, log-on data collecting device determines data acquisition
After equipment is working properly, control detacher releases rotor class model aircraft 1, and rotor class model aircraft 1 freely departs from and is incorporated to neatly
OK；After model water, 13 brake deceleration of hydrodynamic force high-speed test (HST) trailer is until stop.
Step 3：The test data effectiveness of collection after process of the test terminates, is analyzed, invalid data is rejected, then record has
The test parameterss of effect, including model weight, position of centre of gravity, the forward flight speed and subsidence velocity of instant water, model primitive
Under the angle of pitch, roll angle, yaw angle, the angle of pitch of model after water, roll angle, yaw angle, center of gravity overload, driving cabin mistake
Load, base pressure.
This testing program is mainly controlled to model forward flight speed by trailer, subsidence velocity is entered by freely falling body
Row control, is controlled to model attitude angle by experiment installation apparatus, with detacher suspended model center of gravity, convenient to disengage.
Result of the test surface, the present invention can provide believable foundation for the ditching behavior for effectively passing judgment on rotor class aircraft.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is in the principle and objective without departing from the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (5)
1. a kind of rotor class aircraft ditching model test method, it is characterised in that：Comprise the following steps：
Step 1：Installation test device simultaneously completes electric signal connection and test；
The assay device includes rotor class model aircraft (1), hydrodynamic force high-speed test (HST) trailer (13), surveys bridge (12), three freedom
Degree deflection component, model connection member and sensing system；
Three Degree Of Freedom deflection component is fixed on the survey bridge (12) below hydrodynamic force high-speed test (HST) trailer (13) by pipe fitting (11)；
Model connection member is rigidly fixed and is connected to below Three Degree Of Freedom deflection component；Rotor class model aircraft (1) is rigidly fixed in mould
Below type connection member, and model connection member controlled can release rotor class model aircraft (1)；
Sensing system includes gyroscope (15), acceleration transducer (16) and pressure transducer (17)；Gyroscope (15) is fixed
In the center of gravity of rotor class model aircraft (1)；Acceleration transducer (16) is fixed in rotor class model aircraft (1)；Pressure is passed
Sensor (17) is arranged in rotor class model aircraft (1) fuselage lower surface；
Step 2：Rotor class model aircraft (1) motion is driven when hydrodynamic force high-speed test (HST) trailer (13) is moved in orbit, works as rotation
The speed of wing class model aircraft (1) to test requirements document the speed of service and it is stable after, log-on data collecting device determines that data are adopted
After collection equipment is working properly, Controlling model connection member releases rotor class model aircraft (1), and rotor class model aircraft (1) is freely
Disengaging is incorporated to neatly row；After model water, hydrodynamic force high-speed test (HST) trailer (13) brake deceleration is until stop；
Step 3：The test data effectiveness of collection after process of the test terminates, is analyzed, invalid data is rejected, then records effective
Test parameterss, including model weight, position of centre of gravity, the forward flight speed and subsidence velocity of instant water, under model primitive
The angle of pitch, roll angle, yaw angle, the angle of pitch of model after water, roll angle, yaw angle, center of gravity overload, driving cabin overload,
Base pressure.
2. a kind of rotor class aircraft ditching model test method according to claim 1, it is characterised in that：Assay device
Middle Three Degree Of Freedom deflection component includes yaw angle adjusting means (10), angle of pitch adjusting means (9), upper junction plate (8), roll angle
Adjusting means (7)；Yaw angle adjusting means (10) is affixed with pipe fitting (11)；Yaw angle adjusting means (10) adjusts dress with the angle of pitch
(9) connection is put, angle of pitch adjusting means (9) is fixedly connected with upper junction plate (8), upper junction plate (8) and roll angle adjusting means
(7) it is fixedly connected；Roll angle adjusting means (7) is fixedly connected model connection member.
3. a kind of rotor class aircraft ditching model test method according to claim 1 or claim 2, it is characterised in that：
In assay device, model connection member includes middle connecting plate (6), lower connecting plate (2), two positioning seats (3), two pieces of positioning
Plate (5) and flexible attachment components；
Lower connecting plate (2) is rigidly fixed with model and is connected；Middle connecting plate (6) is fixedly connected with roll angle adjusting means (7) lower end；
Two positioning seats are fixedly mounted on the upper surface of lower connecting plate (2), and V-groove, two V-groove phases are provided with two positioning seats
It is mutually vertical, and a V-groove is along model longitudinal direction；Location-plate lower end has the V-type that can coordinate with V-groove raised, two pieces of location-plates
Upper end is fixed on middle connecting plate (6), the V-groove corresponding matching that lower end can respectively with two positioning seats；
Flexible attachment components include suspension ring, detacher, regulating bolt and guide finger；Suspension ring are fixedly mounted on lower connecting plate (2)
Upper surface, detacher can coordinate lifting, detacher upper end to connect with the regulating bolt being arranged on middle connecting plate (6) with suspension ring
Connect, and can coordinate with the guide finger being fixed on middle connecting plate (6).
4. a kind of rotor class aircraft ditching model test method according to claim 3, it is characterised in that：Yaw angle is adjusted
Regulating device (10) is including yaw rotation plate and pinboard；Yaw rotation plate upper surface can be with pipe fitting secure fit；Pinboard by
Orthogonal upper board and lower panel fix composition；Pinboard upper board is connected with yaw rotation plate patch merga pass first rotating shaft
Connect, pinboard upper board can be rotated relative to yaw rotation plate around first rotating shaft, and can fix angle of rotation by locking mechanism
Degree；Graduation mark of the labelling around first rotating shaft rotational angle is carved with yaw rotation plate and/or pinboard upper board；
Angle of pitch adjusting means (9) is including pitch rotation plate；Pitch rotation plate is fixed by orthogonal upper board and lower panel
Composition；Pitch rotation plate upper board is connected with patch the second rotating shaft of merga pass of pinboard lower panel, pitch rotation plate upper board energy
It is enough to rotate relative to pinboard lower panel around the second rotating shaft, and rotational angle can be fixed by locking mechanism；On pitch rotation plate
Graduation mark of the labelling around the second axis of rotation angle is carved with portion's plate and/or pinboard lower panel；
Pitch rotation plate lower panel is fixedly connected with upper junction plate (8)；
Roll angle adjusting means (7) rotates outer panel including rolling and rolling rotates interior plate；
Upper junction plate (8) rotates outer panel with rolling and is mutually perpendicular to and is fixedly connected；Rolling rotates interior plate and middle connecting plate (6)
It is fixedly connected；Rolling is rotated outer panel and is connected with rolling rotation interior plate patch the 3rd rotating shaft of merga pass, and rolling rotates interior plate
Outer panel can be rotated around the 3rd rotating shaft relative rolling to rotate, and rotational angle can be fixed by locking mechanism；Rolling is rotated
Outer panel and/or rolling to be rotated and be carved with graduation mark of the labelling around the 3rd axis of rotation angle on interior plate.
5. a kind of rotor class aircraft ditching model test method according to claim 4, it is characterised in that：Two groups mutual
The rolling of cooperation rotates outer panel and rolling rotates interior plate and is separately fixed at upper junction plate (8) along before and after model longitudinal direction two
End, and two group of the 3rd rotating shaft is coaxial.
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| CN201610970051.6A CN106525388B (en) | 2016-11-07 | 2016-11-07 | A kind of rotor class aircraft ditching model test method |
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