CN105784314A - Low-speed wind tunnel virtual flying experimental support device - Google Patents
Low-speed wind tunnel virtual flying experimental support device Download PDFInfo
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- CN105784314A CN105784314A CN201610122608.0A CN201610122608A CN105784314A CN 105784314 A CN105784314 A CN 105784314A CN 201610122608 A CN201610122608 A CN 201610122608A CN 105784314 A CN105784314 A CN 105784314A
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Abstract
The present invention discloses a low-speed wind tunnel virtual flying experimental support device which comprises a base, an airfoil support seat, a pre-bent support rod and a three-degree-of-freedom joint. The base is fixedly installed at the center position of a wind tunnel test section basic platform. The bottom end of the airfoil support seat is vertical and is fixedly installed on the base. The cross section of the airfoil support seat is parallel to a wind tunnel flow coming direction. One end of the pre-bent support rod is connected to the top end of the airfoil support seat, the other end of the pre-bent support rod is connected to the three-degree-of-freedom joint, and the cross section of the pre-bent support rod is parallel to the wind tunnel flow coming direction. The rotation center of the three-degree-of-freedom joint is in an axis in a wind tunnel and is hinged to an aircraft model. The hinged position is provided with a fine burning device which allows the mass center of the aircraft model coincides with the rotation center of the three-degree-of-freedom joint. According to the invention, the large range three-axis attitude free support of the aircraft model in a virtual flying experiment can be realized, the structure is simple, the interference is small, the accuracy is high, and the installation and adjustment methods are simple.
Description
Technical field
The invention belongs to wind tunnel experiment device technique field, particularly relate to a kind of low-speed wind tunnel virtual flight experiment support arrangement.
Background technology
In low-speed wind tunnel virtual flight is tested, support arrangement is used for supporting model aircraft, constraint three-shaft displacement freedom of motion and providing three-axis attitude freedom of motion, the requirement that a support arrangement must is fulfilled for that angle range is big, support interferences and frictional force etc. be can not ignore.
Existing virtual flight experiment support arrangement is divided into bracing cable formula and movable joint overlapped in series formula two kinds support arrangement design principle.
Hanging brace device adopts 8 bracing cables that one collar is fixed on test chamber, and the collar is connected by two-freedom sports ring with model aircraft.Although the interference for flight experiment of the support of hanging brace device is less, but still have the disadvantages that one is to realize yaw angle degree of freedom；Two is that attainable pitching, roll freedom range of movement are little；Three is that structure is complicated, installs and debugging difficulty.
It is three cradle heads of arranged in series on pole that movable joint overlapped in series formula props up support arrangement, and three joints are mutually orthogonal, and intersection point is positioned at the link position of model aircraft.Although this support device structure is simple, but having the disadvantages that one is that normal alignment between the rotating shaft of joint exists error, model aircraft barycenter is relatively big with the alignment error of rotating shaft intersection point, thus causing a support arrangement to affect bigger on the dynamics of model aircraft；Two is that the part body that this kind props up in support arrangement can move with model aircraft, causes a support arrangement that the interference effect of flight experiment is bigger；Three is that the frictional force in joint is relatively big, and the impact of virtual flight experiment is bigger.
Summary of the invention
In order to solve the problems referred to above, the present invention proposes a kind of low-speed wind tunnel virtual flight experiment support arrangement, it is possible to realizes the three-axis attitude free support on a large scale of model aircraft, simple in construction in virtual flight experiment, disturbs little and precision is high, installs and method of adjustment is simple.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of low-speed wind tunnel virtual flight experiment support arrangement, including test chamber basic platform, model aircraft and a support arrangement, described support arrangement includes base, aerofoil profile bearing, pre-bent sting and Three Degree Of Freedom joint；The center that described base is fixedly mounted in test chamber basic platform；The bottom of described aerofoil profile bearing vertically and is fixedly installed on described base, and it is parallel that the section of aerofoil profile bearing carrys out flow path direction with wind-tunnel；Described pre-bent sting one end is connected with described aerofoil profile holder top, and the other end of described pre-bent sting is connected with described Three Degree Of Freedom joint, and it is parallel that the section of pre-bent sting carrys out flow path direction with wind-tunnel；The center of rotation in described Three Degree Of Freedom joint is positioned on wind-tunnel axis, and Three Degree Of Freedom joint and model aircraft are hinged, and hinged place is provided with micromatic setting makes the barycenter of model aircraft overlap with the center of rotation in Three Degree Of Freedom joint.
Described base plays location and fixation, is installed on test chamber basic platform immediate vicinity；Described aerofoil profile bearing plays load and guide functions, bears the effect of the gravity of model aircraft, aerodynamic force and shock loading, and the position keeping the model aircraft strong point is constant all the time, guides gas flow smooth by reducing support interferences impact；The described pre-bent sting preset effect of pattern drawing angle, provides certain established angle for described Three Degree Of Freedom joint, it is thus achieved that experiment needs the angular range of model aircraft；Degree of freedom constraint and release action are played in described Three Degree Of Freedom joint, limit three axis shift degree of freedom, discharge yaw freedom, it is possible to realize release pitching and roll freedom in a big way.
Further, being provided with level(l)ing device in described base, make base be adjusted to horizontal level, the direction by controlling wind tunnel experiment section basic platform rotation adjusting base is consistent to carrying out flow path direction with wind-tunnel.
Further, described aerofoil profile bearing includes column and aerofoil profile cover, and described column is positioned at the inside of aerofoil profile cover, and column and aerofoil profile cover are fixed and connected.
Further, described column adopts thin-wall steel tube, can alleviator weight under meeting the premise of structural strength and rigidity requirement；Described aerofoil profile cover adopts NACA0009 symmetrical airfoil structure.
It is further, described pre-bent sting enters inside model aircraft through described model aircraft lower surface, the external diameter value of described pre-bent sting is at 5-10mm, pre-bent sting is made to reduce the aperture area of model aircraft lower surface while meeting support strength and rigidity, thus reducing the support arrangement interference to experiment.
Further, wrap up plastic pad on described pre-bent sting surface, to slow down the impact that interference and collision brings, the interference and collision between model aircraft and described pre-bent sting when model aircraft attitude angle exceedes allowed band.
Further, described Three Degree Of Freedom joint adopts Structure deformation type to rotate ball pivot, and described Structure deformation type rotates yaw angle scope ± 180 ° of ball pivot, and described Structure deformation type rotates pitching and roll angle scope ± 45 ° of ball pivot.
It is further, described Structure deformation type rotates ball pivot and includes pedestal, retainer, planet ball, sun ball and threaded rod, wherein said pedestal is connected with model aircraft, described threaded rod is connected with described pre-bent sting, described retainer is positioned at planet ball described in base internal support, and described planet bag is rolled in around described sun ball and is connected with the rolling of sun ball.
Further, having three axle rotational freedoms between described sun ball and pedestal, between sun ball and pedestal, relative motion passes through planet ball indirect transfer, thus significantly reducing contact area and reducing frictional resistance.
Based on same inventive principle, present invention also offers the using method of a kind of low-speed wind tunnel virtual flight experiment support arrangement, including step:
A., described base is installed in the center of test chamber basic platform, and the levelness of adjusting base；B. described aerofoil profile bearing is arranged on base, and regulates vertically degree and the direction of described aerofoil profile bearing；C. described pre-bent sting is arranged on aerofoil profile bearing, and regulates the direction of pre-bent sting；D. described Three Degree Of Freedom joint is arranged on described pre-bent sting；E. described model aircraft is arranged on Three Degree Of Freedom joint, regulates the barycenter of model aircraft and the registration at described Three Degree Of Freedom articulation center.
A kind of low-speed wind tunnel virtual flight experiment support arrangement proposed by the invention, adopts the beneficial effect of the technical program:
The present invention adopts Three Degree Of Freedom joint to realize low-speed wind tunnel virtual flight test model and supports, have the advantage that simple in construction, easy for installation and good economy performance, test chamber need not be carried out adaptability structure of modification, it is not required that carry out the relative position close adjustment between movable joint；Model aircraft kinematic Simulation precision is high, and directly by a joint implementation model three-axis attitude degree of freedom simulation, model aircraft kinematical equation does not call for any correction about a support arrangement；The impact of model aircraft dynamics is little.
The aerofoil profile bearing adopted in the present invention and pre-bent sting, portable construction, installation and method of adjustment are simple and support interferences is little.
The Three Degree Of Freedom articulation structure adopted in the present invention is compact and angle range is big.
The support arrangement versatility that the present invention proposes is good, it is possible to for carrying out the virtual flight experimentation of different model aircraft；The using method flow process simple specification proposed, strong operability, it is possible to be generalized in other openings or closed type low-speed wind tunnel, there is good future in engineering applications.
Accompanying drawing explanation
Fig. 1 is the structure diagram of a kind of low-speed wind tunnel virtual flight experiment support arrangement of the present invention；
Fig. 2 is the structural representation of a kind of low-speed wind tunnel virtual flight experiment support arrangement of the present invention；
Fig. 3 is the structural representation of aerofoil profile bearing in the embodiment of the present invention；
Fig. 4 is the structural representation that in the embodiment of the present invention, Structure deformation type rotates ball pivot；
Fig. 5 is a kind of low-speed wind tunnel virtual flight experiment support arrangement using method flow chart of the present invention；
Fig. 6 is the fundamental diagram of a kind of low-speed wind tunnel virtual flight experiment support arrangement using method of the present invention.
Detailed description of the invention
In order to make the object, technical solutions and advantages of the present invention clearly, below in conjunction with accompanying drawing, the present invention is further elaborated.
nullIn embodiment one，Referring to shown in Fig. 1 and Fig. 2，The present invention proposes a kind of low-speed wind tunnel virtual flight experiment support arrangement，Including test chamber basic platform、Model aircraft 1 and a support arrangement，Described support arrangement includes base 2、Aerofoil profile bearing 3、Pre-bent sting 4 and Three Degree Of Freedom joint 5，The center that described base 2 is fixedly mounted in test chamber basic platform，The bottom of described aerofoil profile bearing 3 vertically and is fixedly installed on described base 2，Described pre-bent sting 4 one end is connected with described aerofoil profile bearing 3 top，The other end of described pre-bent sting 4 is connected with described Three Degree Of Freedom joint 5，The center of rotation in described Three Degree Of Freedom joint 5 is positioned on wind-tunnel axis，Three Degree Of Freedom joint 5 and model aircraft 1 are hinged，Hinged place is provided with micromatic setting makes the barycenter of model aircraft 1 overlap with the center of rotation in Three Degree Of Freedom joint 5.
Described base 2 location and fixation, be installed on test chamber basic platform immediate vicinity；3 loads of described aerofoil profile bearing and guide functions, bear the effect of the gravity of model aircraft 1, aerodynamic force and shock loading, and the position keeping model aircraft 1 strong point is constant all the time, guides gas flow smooth by reducing support interferences impact；Described pre-bent sting 4 plays the model aircraft 1 preset effect of angle, provides certain established angle for described Three Degree Of Freedom joint 5, it is thus achieved that experiment needs the angular range of model aircraft 1；The degree of freedom constraint of 5, described Three Degree Of Freedom joint and release action, limit three axis shift degree of freedom, discharge yaw freedom, it is possible to realizes release pitching and roll freedom in a big way.
In embodiment two, on the basis of embodiment one, being provided with level(l)ing device in described base 2, make base 2 be adjusted to horizontal level, the direction by controlling wind tunnel experiment section basic platform rotation adjusting base 2 is consistent to carrying out flow path direction with wind-tunnel.
In embodiment three, on the basis of embodiment one, shown in Figure 3, described aerofoil profile bearing 3 includes column 31 and aerofoil profile cover 32, and described column 31 is positioned at the inside of aerofoil profile cover 32, and column 31 and aerofoil profile cover 32 are fixed and connected.
Wherein, described column 31 adopts thin-wall steel tube, can alleviator weight under meeting the premise of structural strength and rigidity requirement；Described aerofoil profile cover 32 adopts NACA0009 symmetrical airfoil structure.
In embodiment four, on the basis of embodiment one, it is internal that described pre-bent sting 4 enters model aircraft 1 through described model aircraft 1 lower surface, make the external diameter value of pre-bent sting 4 at 5-10mm, described pre-bent sting 4 reduces the aperture area of model aircraft 1 lower surface while meeting support strength and rigidity, thus reducing the support arrangement interference to experiment.
Wherein, plastic pad is wrapped up on described pre-bent sting 4 surface to slow down the impact that interference and collision brings, the interference and collision between model aircraft 1 and described pre-bent sting 4 when model aircraft 1 attitude angle exceedes allowed band.
In embodiment five, on the basis of embodiment one, described Three Degree Of Freedom joint 5 adopts Structure deformation type to rotate ball pivot, and described Structure deformation type rotates yaw angle scope ± 180 ° of ball pivot, and described Structure deformation type rotates pitching and roll angle scope ± 45 ° of ball pivot.
Wherein, shown in Figure 4, described Structure deformation type rotates ball pivot and includes pedestal 51, retainer 52, planet ball 53, sun ball 54 and threaded rod 55, wherein said pedestal 51 is connected with model aircraft 1, described threaded rod 55 is connected with described pre-bent sting 4, described retainer 52 is positioned at planet ball 53 described in pedestal 51 inner support, and described planet ball 53 is wrapped in around described sun ball 54 and is connected with sun ball 54 rolling.
Wherein, having three axle rotational freedoms between described sun ball 54 and pedestal 51, between sun ball 54 and pedestal 51, relative motion passes through planet ball 53 indirect transfer, thus significantly reducing contact area and reducing frictional resistance.
For coordinating the present invention to prop up the use of support arrangement, based on identical inventive concept, shown in Figure 5, present invention also offers the using method of a kind of low-speed wind tunnel virtual flight experiment support arrangement, including step:
A., described base 2 is installed in the center of test chamber basic platform, and the levelness of adjusting base 2；B. described aerofoil profile bearing 3 is arranged on base 2, and regulates vertically degree and the direction of described aerofoil profile bearing 3；C. described pre-bent sting 4 is arranged on aerofoil profile bearing 3, and regulates the direction of pre-bent sting 4；D. described Three Degree Of Freedom joint 5 is arranged on described pre-bent sting 4；E. described model aircraft 1 is arranged on Three Degree Of Freedom joint 5, regulates the barycenter of model aircraft 1 and the registration of described Three Degree Of Freedom joint 5 center of rotation.
In order to be better understood from the present invention, below the operation principle of the present invention is done once complete description:
As shown in Figure 6, specific implementation process: select pre-bent sting 4 according to model aircraft 1 angle-of-attack range that experimental state requires；Mounting seat 2 also debugs levelness；Aerofoil profile bearing 3 it is installed and is adjusted to vertical degree, controlling test chamber basic platform and rotate, make aerofoil profile carry out flow path direction with wind-tunnel parallel；Installing pre-bent sting 4, adjustment direction is parallel to carrying out flow path direction with wind-tunnel；Three Degree Of Freedom joint 5 is installed；Model aircraft 1 is installed, adjusts installation site, until to carry out flow path direction with wind-tunnel substantially parallel the attitude of model aircraft 1 basic horizontal in its natural state and direction；Carry out the experiment of wind-tunnel virtual flight；Current pre-bent sting 4 provides experiment content in angle-of-attack range to complete, it may be judged whether needs to change pre-bent sting 4 and continues experiment, if being judged as YES, then first dismantles model aircraft 1 and pre-bent sting 4, then reinstalls；If being judged as NO, then experiment terminates.
The ultimate principle of the present invention and principal character and advantages of the present invention have more than been shown and described.Skilled person will appreciate that of the industry; the present invention is not restricted to the described embodiments; described in above-described embodiment and description is that principles of the invention is described; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements both fall within the claimed scope of the invention.The invention of this reality claims scope and is defined by appending claims and equivalent thereof.
Claims (10)
1. a low-speed wind tunnel virtual flight experiment support arrangement, including test chamber basic platform, model aircraft (1) and a support arrangement, it is characterized in that, described support arrangement includes base (2), aerofoil profile bearing (3), pre-bent sting (4) and Three Degree Of Freedom joint (5)；Described base (2) is fixedly mounted on the center of test chamber basic platform；The bottom of described aerofoil profile bearing (3) vertically and is fixedly installed on described base (2), and it is parallel that the section of aerofoil profile bearing (3) carrys out flow path direction with wind-tunnel；Described pre-bent sting (4) one end is connected with described aerofoil profile bearing (3) top, and the other end of described pre-bent sting (4) is connected with described Three Degree Of Freedom joint (5), and it is parallel that the section of pre-bent sting (4) carrys out flow path direction with wind-tunnel；The center of rotation of described Three Degree Of Freedom joint (5) is positioned on wind-tunnel axis, Three Degree Of Freedom joint (5) and model aircraft (1) are hinged, and hinged place is provided with micromatic setting makes the barycenter of model aircraft (1) overlap with the center of rotation of Three Degree Of Freedom joint (5).
2. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 1, it is characterized in that, described base is provided with level(l)ing device in (2), making base (2) be adjusted to horizontal level, the direction by controlling wind tunnel experiment section basic platform rotation adjusting base (2) is consistent to carrying out flow path direction with wind-tunnel.
3. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 1, it is characterized in that, described aerofoil profile bearing (3) includes column (31) and aerofoil profile cover (32), described column (31) is positioned at the inside of aerofoil profile cover (32), and column (31) and aerofoil profile cover (32) are fixed and connected.
4. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 3, it is characterised in that described column (31) adopts thin-wall steel tube, can alleviator weight under meeting the premise of structural strength and rigidity requirement；Described aerofoil profile cover (32) adopts NACA0009 symmetrical airfoil structure.
5. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 1, it is characterized in that, it is internal that described pre-bent sting (4) enters model aircraft (1) through described model aircraft (1) lower surface, the external diameter value of described pre-bent sting (4), at 5-10mm, makes pre-bent sting (4) reduce the aperture area of model aircraft (1) lower surface while meeting support strength and rigidity.
6. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 5, it is characterised in that wrap up plastic pad on described pre-bent sting (4) surface, to slow down the impact that interference and collision brings.
7. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 1, it is characterized in that, described Three Degree Of Freedom joint (5) adopts Structure deformation type to rotate ball pivot, described Structure deformation type rotates yaw angle scope ± 180 ° of ball pivot, and described Structure deformation type rotates pitching and roll angle scope ± 45 ° of ball pivot.
8. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 7, it is characterized in that, described Structure deformation type rotates ball pivot and includes pedestal (51), retainer (52), planet ball (53), sun ball (54) and threaded rod (55), wherein said pedestal (51) is connected with model aircraft (1), described threaded rod (55) is connected with described pre-bent sting (4), described retainer (52) is positioned at planet ball (53) described in pedestal (51) inner support, described planet ball (53) is wrapped in described sun ball (54) and is around connected with sun ball (54) rolling.
9. a kind of low-speed wind tunnel virtual flight experiment support arrangement according to claim 8, it is characterized in that, between described sun ball (54) and pedestal (51), there are three axle rotational freedoms, between sun ball (54) and pedestal (51), relative motion passes through planet ball (53) indirect transfer, thus significantly reducing contact area and reducing frictional resistance.
10. a low-speed wind tunnel virtual flight experiment support arrangement using method, it is characterised in that described method step includes:
A., described base (2) is installed in the center of test chamber basic platform, and the levelness of adjusting base (2)；
B. described aerofoil profile bearing (3) is arranged on base (2), and regulates vertically degree and the direction of described aerofoil profile bearing (3)；
C. described pre-bent sting (4) is arranged on aerofoil profile bearing (3), and regulates the direction of pre-bent sting (4)；
D. described Three Degree Of Freedom joint (5) is arranged on described pre-bent sting (4)；
E. described model aircraft (1) is arranged on Three Degree Of Freedom joint (5), regulates the barycenter of model aircraft (1) and the registration of described Three Degree Of Freedom joint (5) center of rotation.
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| CN107247839A (en) * | 2017-06-08 | 2017-10-13 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of low-speed wind tunnel virtual flight flight test vehicle design methods |
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