1/8 DESCRIPTION Title A Supporting System for High-Speed Wind Tunnel FIELD OF THE INVENTION The present invention generally relates to a supporting system for high-speed wind tunnel. BACKGROUND OF THE INVENTION The principles and processes of the wind tunnel test has been clearly described in Chinese patent application 201210387483.6 filed on October 12, 2012, herein incorporated by reference, in order to be understood by those skilled in the field, the following description is only be described as a background art that can not be regarded as prior art. An improved supporting structure for the entire aircraft has been described in that background document, for the purpose of providing stable support to the aircraft model in wind tunnel test. However, the supporting system of the background is difficult to apply to the high-speed wind tunnel experiment. Because in the high-speed wind tunnel, the air flow speed as well as the air tightness requirements are all very much high, and the requirements for supporting structure of the aircraft model is much higher than that of the low speed wind tunnel. Specifically, the supporting structure can not be too large, the airflow interference must meet the basic blocking requirements, that is, the space occupied by the supporting structure in the wind tunnel can not be too large, otherwise it will block the flow of high-speed air, and air velocity can not reach the high Mach number requirements of the wind tunnel experiments. In addition, besides the high requirements of the size of the supporting system for the high-speed wind tunnel, it also need to consider the multi-gesture adjustable supporting system that is suitable for high-speed wind tunnel model of the aircraft pitch angle, yaw angle, roll angle ability for flexible control. US4658635A disclosed a typical wind tunnel supporting system, the supporting system includes a rotating disk disposed on the floor in a wind tunnel, a curved support arm is provided on the rotating disc, the curved support arm can be controlled by the hydraulic mechanism for pitch change, a cantilever arm is rotatably support at the top of the curved support arm, the end of the cantilever arm is connected to the tail of the aircraft model. When rotating disc rotates, the entire aircraft model will rotate too, which can provide yaw angle 2/8 control; when the curved support arm pitch changed, the pitch angle control is provided; when the cantilever arm rotates, the roll angle can be also controlled. The defect of the US4658635A is that, the space occupation for the yaw angle adjusting of the rotation of the disc space is very large, even if the rotating disc is provided under the floor in a wind tunnel. Moreover, due to it is a rotary member, provided under the floor make the sealing be a big problem. In addition, if the aircraft model is to be with a larger size, then the curved support arm corresponding becomes large; otherwise it is difficult to provide a larger range of tilt angle adjustment range. The height and width of the wind tunnel usually quite limited, which limits the size of the curved support arm, thereby limiting the range of adjustment of the pitch angle. Similarly, US5020364A also disclosed a wind tunnel supporting system, which includes a rotating disc, disposed in a wind tunnel on the floor. On the rotating disc provided with a telescopic arm, at the top of the telescopic arm supported by a pitch cantilever arm, the end of the cantilever arm connected to the tail of the aircraft model. When rotating disc rotation, the entire aircraft model will rotate, thereby providing yaw angle control; when the pitch cantilever arm changed pitch, the pitch angle can be controlled. The defect of US5020364A is also the rotating disc. In addition, in order to provide a large range of tilt angle adjustment, the prior art provides a telescopic arm, but, under normal circumstances, the height and width of the wind tunnel is quite limited, when the aircraft model is much big, the amount of expansion and contraction of the telescopic arm will limit the adjustment range of the pitch angle. Therefore, it is necessary to provide a supporting system for high-speed wind tunnel, applicable to aircraft model to provide multi-gesture suitable for the adjustable multi-gesture support of the aircraft model in high speed wind tunnel. SUMMERY OF THE INVENTION The objects of present invention are to provide a supporting system for high-speed wind tunnel to avoid the above problem. In order to solve the above problem, the present invention disclosed a supporting system for high-speed wind tunnel for providing support to an aircraft model in a high-speed wind tunnel, wherein the said supporting system for high-speed wind tunnel include: a vertically disposed support column fixed connect with the floor and the ceiling of the said high-speed wind tunnel; a base removable fixed to the said support column; first folding arm, the said first folding arm is rotatably connected to the said base by a first shaft, and can be rotatably in 3/8 a horizontal plane about the first shaft parallel to the said support column; second folding arm, the said second folding arm is rotatably connected to the end of the said first folding arm by a second shaft, and can be rotatably in a horizontal plane about the said second shaft parallel to the said support column; third folding arm, the said third folding arm is rotatably connected to the end of the said second folding arm by a third shaft, and can be rotatably in a vertical plane about the third shaft perpendicular to the said support column; roll arm, the said roll arm is rotatably connected to the end of the said third folding arm by a fourth shaft, and can be rotatably in a vertical plane about the fourth shaft perpendicular to the said support column; the said aircraft model supported on the end of the said roll arm, and can be rotatably about the axis of the said roll arm. Preferably, the said support column has the same cross-section along air flow direction of the said high-speed wind tunnel; the said section is symmetrical on both sides of the streamlined spindle. Preferably, a plurality of reserved mounting holes is provided along the height direction of the said support column at equal intervals. Preferably, the said reserved mounting holes are provided with shelter nuts. Preferably, the said first folding arm, the second folding arm, the third folding arm and the rotation axis are all surrounded with protection cover. The supporting system for high-speed wind tunnel of the present invention can provide flexible control of the pitch angle, the yaw angle and the roll angle of the aircraft model, suitable for the adjustable multi-gesture support of the aircraft model in high speed wind tunnel. DESCRIPTION OF THE DRAWING The following drawing is only for the purpose of description and explanation but not for limitation, wherein: Figure 1 shows a schematic vertical sectional view of an embodiment of a supporting system for high-speed wind tunnel according to the present invention. Figure 2 is a schematic plan cross-sectional view of the supporting system for the high speed wind tunnel shown in Figure 1. DESCRIPTION OF PREFERRED EMBODIMENT In order that the present invention can be more readily understood, reference will now be made to the accompanying drawing to illustrate the embodiments of the present invention.
4/8 Figure 1 shows a schematic vertical sectional view of an embodiment of a supporting system for high-speed wind tunnel according to the present invention; Figure 2 is a schematic plan cross-sectional view of the supporting system for the high-speed wind tunnel shown in Figure 1. As shown, the supporting system 1 can be used for providing support to an aircraft model 100 in a high-speed wind tunnel, for example, the supporting system 1 can be used in wind tunnel test to support the entire aircraft model 100 in the wind tunnel, in high-speed airflow environment by the various components of the pressure test equipment to measure the entire aircraft model 100 pressure distribution data in a specific flight conditions, in order to obtain the flow characteristics of the aircraft. Referring to Figure 1-2, for ease of explanation, it is providing the three-dimensional coordinate system, wherein, x-axis extending along the longitudinal direction of the high-speed wind tunnel, y-axis extending along the width of high-speed wind tunnel, the z-axis extending along the height of the high-speed wind tunnel. As shown, the embodiment of the supporting system 1 for high-speed wind tunnel includes a vertically disposed support columns 11, which is fixedly connected to the floor 200 and the ceiling 300 of the high-speed wind tunnel, and a base 12 removable fixed to the support column 11. The high-speed wind tunnel shown in Figures 1 and 2 is a traditional form of rectangular cross-section wind tunnel, which has a relatively limited height (z-axis direction in the figure) and width (y-axis direction), but has a relatively great length (x-axis direction), the figure for clear description only interception of the longitudinal direction of the partial structure. The skills in the art should understand that, as shown, the structure of the tunnel is a kind of tunnel applicable in the present invention, which has a relatively limited height and width, and having a relatively great length. The supporting system 1 for high-speed wind tunnel according to the present embodiment further includes a first folding arm 13, said first folding arm 13 is rotatably connected to the base 12 by a first shaft 131 and is rotatably in a horizontal plane (coordinate line in the x-y plane) about the first rotation shaft 131 parallel to the support column 11; the supporting system 1 for high-speed wind tunnel further includes a second folding arm 14, the said second folding arm 14 is rotatably connected to the end of the first folding arm 13 by a second shaft 141, and is rotatably in a horizontal plane (x-y plane) about the second shaft 141 parallel to the support column 11. Further, the supporting system 1 for high-speed wind tunnel further includes a third folding arm 15, said third folding arm 15 is rotatably connected to the end of the second folding arm 14 by the third shaft 151, and is rotatably in the vertical plane (coordinate system 5/8 x-z plane) about the third shaft 151 vertical to the support column 11; the supporting system 1 for high-speed wind tunnel further includes a roll arm 16, said roll arm 16 is rotatably connected to the end of the third folding arm 15 by the fourth shaft 161, and is rotatably in the vertical plane (coordinate system in the x-z plane) about the fourth shaft 161 vertical to the support column 11. Aircraft model 100 is supported at the end of the roll arm 16, and can rotate around the axis of the roll arm 16. That is, the roll arm 16 is rotatably about a rotation axis (x-axis direction in the coordinate system), which led the aircraft model 100 fixedly connected with the roll arm 16 to roll, and to flexibly control aircraft roll angle of the model 100. About the structure of the roll arm 16 can refer the structure of CN202547900U, in present application by reference, not described in detail. When we need to adjust the yaw angle of the aircraft model 100, the first folding arm 13 and the second folding arm 14 will be cooperated rotating in the horizontal plane, as shown in Figure 2. The benefits of providing two folding arms is that, when the width of the wind tunnel is limited, and when the yaw angle is adjusted by only one folding arm, the yaw angle will be limited by the length of the folding arm and the length of the aircraft model, as both of the total length is too long it will hit the wind tunnel wall, which cannot make large range of yaw angle wind tunnel experiment. However, the use of two folding arm, in the case of a folding arm reaches its horizontal rotation limit, the aircraft model 100 can be arranged in the middle of the wind tunnel by the second folding arm to avoid the wind tunnel width limit the yaw angle adjustable range, two folding arm with greater yaw angle adjustable range, this is especially suit for the situation for the wind tunnel with limited width but large length. When we need to adjust the pitch angle of the aircraft model 100, the third folding arm 15 and the roll arm 16 will be cooperated rotating in the vertical plane, as shown in Figure 1. The benefits of providing two arms is that, when the height of the wind tunnel is limited, and when the pitch angle is adjusted only by one folding arm, the pitch angle will be limited by the length of the folding arm and the length of the aircraft model, as both of the total length is too long it will hit the wind tunnel floor or roof, which cannot make large range of pitch angle wind tunnel experiment. However the use of two arms (folding arm and roll arm), in the case of one arm (folding arm or roll arm) reaches its vertical rotation limit, the aircraft model 100 can be arranged in the middle of the wind tunnel by the second arm (folding arm or roll arm) to avoid the wind tunnel height restrictions, with two arms (folding arm and roll arm) to provide greater pitch angle adjustable range, this is especially suit for the situation for the wind tunnel with the limited height but large length.
6/8 As the driving structure on the connecting position of first folding arm 13, second folding arm 14, the third folding arm 15, and the roll arm 16, it can be used with the existing hydraulic structures (e.g. US5020364A), and can also be used with the existing electric joint structures, these driving structure is not the focus of the present invention, and therefore will not be described in detail. As seen from the above description, the significant difference between the supporting system 1 for high-speed wind tunnel of present invention and the prior art described in the technical background section is that, at least the supporting system 1 of the present invention has not arrange the rotating disc beneath the wind tunnel floor, which greatly simplifies the yaw angle adjustment mechanism, and is especially suit for the situation for the wind tunnel with limited width but large length. Also, the pitch angle regulating mechanic of the aircraft model of present invention is much simpler than the prior art is, and will not be restricted by the height limited of wind tunnel. In the present invention, due to the supporting structures of the aircraft model 100 are all located inside the wind tunnel, and the structures are relatively simple, just have a few folding arms, the space occupied in the wind tunnel is small, which easy to meet the requirements of the obstruction degree of high-speed wind tunnel. Further, since the support column 11 is fixed between the floor 200 and the ceiling 300, which is the basis for the entire supporting system, thus the entire supporting system 1 and the high-speed wind tunnel has no openings, which will not affect the of the wind tunnel, and is very much suitable for the requirements of high-speed wind tunnel experiments. Further, in a preferred embodiment, in order to adapt to the different experimental situations, the base 12 is detachably fixed to the support column 11, That is, based on the different experimental situations, the base 12 can be removed and be fixed to the support column 11 on different height positions. For the adaptation of the position adjustment of the base 12, a plurality of reserved mounting holes 112 can be arranged along the direction of the height (in the z-axis direction in FIG 1) of the support column 11, which can be used to fix the base 12 at the different height positions of reserved mounting holes 112 by a bolt 113, in order to avoid the base 12 to slide along the support column 11 in the high-speed flow field leading the damage to the laboratory equipment. To avoid unused reserved installation screw holes 112 affect the stability of the wind tunnel flow field in the assembly process, each reserved installation screw holes 112 are provided shelter nut (not shown), to sealed shielding the installation screw hole 112. When the 7/8 mounting base 12 is installed, the shielding nut on the installation position will be removed, the base 12 can be fixedly mounted on the support column 11 by means of bolts 113 by the corresponding mounting screw hole 112. Further, in a specific embodiment, in order to avoid the respective structure of the supporting system 1 affect the wind tunnel flow field, a protective cover 18 is provided around the first folding arm 13, the second folding arm 14, the third folding arm 15 and the axis of rotation 131,141, 151,161, as shown in dashed lines in Figure 1. For the sake of clarity, Figure 2 omitted the protective cover 18, which is shown in Figure 1. The protective cover 18 can provide shielding to the rotating member, to avoid affecting the stability of the wind tunnel flow field by the shape of the rotational member and the gaps between the connecting portions, and often it is needed to add the grease to the connection position of the rotating member, in the high-speed wind tunnel grease may airflow blown splash all over the place, so the cover is provide not only for the purpose of providing a streamlined aerodynamic shape, but also provides a blocking effect of the grease. Further, in a specific embodiment, the support column 11 along the gas flow direction of the high-speed wind tunnel having the same cross-sectional 111, said section 111 is symmetrical on both sides of the streamlined spindle. Such a structure of the support columns 11 can avoid large blocking surface in the direction of the gas flow, while the same section 111 is easy to keep the stability of the flow field, that is, if the support column 11 having a different cross-section 111 in the height direction, which will be difficult to predict and calculate the stability of the entire wind tunnel flow field in the height direction, and is not easy to obtain a stable experimental results. Of course, in order to avoid blocking the wind tunnel with reducing the cross-sectional area of the support column 11 will weaken the strength of the support column 11, so both sides of the middle of the sections 111 of the support column 11 are protruded with streamlined spindle, which are also easy to keep the stability of the flow field. In summary, the supporting system for high-speed wind tunnel of the present invention can provide flexible control of the pitch angle, the yaw angle and the roll angle of the aircraft model, suitable for the adjustable multi-gesture support of the aircraft model in high speed wind tunnel. Whilst the above has been given by way of illustrative examples of the present invention, many variations and modifications thereto will be apparent to those skilled in the art without departing from the broad ambit and scope of the invention as herein set forth in the following claims.