CN113252285A - Vertical wind tunnel model pitching-rolling test device and use method - Google Patents
Vertical wind tunnel model pitching-rolling test device and use method Download PDFInfo
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Abstract
The invention is suitable for the technical field of wind tunnel tests and provides a vertical wind tunnel model pitch-roll test device and a using method thereof, wherein the test device comprises: the base is fixedly arranged on a tunnel wall platform of the vertical wind tunnel test section; the bottom end of the upright post is fixedly connected with the base; the supporting rod is positioned between the upright post and the abdomen supporting bent rod, one end of the supporting rod is fixedly connected with the top end of the upright post, the other end of the supporting rod is connected with one end of the abdomen supporting bent rod through a rotating assembly, and the rotating assembly is arranged at one end of the supporting rod, which is far away from the upright post; the abdomen bracing bent rod is fixedly connected with the mounting seat at one end far away from the rotating assembly, and the mounting seat is fixedly mounted on the abdomen of the aircraft model. The aircraft model can freely pitch/roll under the action of aerodynamic force, and has the advantages of simple structure, small mechanism rotational damping, small interference, high precision, and simple and reliable installation.
Description
Technical Field
The invention relates to the field of wind tunnel tests of aircrafts, in particular to a vertical wind tunnel model pitching-rolling test device and a using method thereof.
Background
The pitching characteristic of the aircraft is an important index for evaluating the operation performance and the air performance of the aircraft, and the research on the pitching characteristic of the aircraft carried out through the wind tunnel test has the advantages of low cost, low risk, high precision and the like.
The aircraft pitching test device is classified according to a constraint mode and mainly comprises a pitching forced oscillation test device and a free pitching forced oscillation test device. The model supporting mode mainly has four types, and the four types are respectively: abdominal bracing, tail bracing, wingtip bracing and back bracing. In the wind tunnel test, the supporting device plays a supporting or driving role in pitching motion of the airplane model and is used for carrying out a large attack angle unsteady test, a dynamic derivative test and the like.
In the prior art, a wind tunnel test system for researching the pitching characteristic of an aircraft is mainly established in a conventional horizontal wind tunnel aiming at an aircraft with a conventional layout, and although the wind tunnel test system can meet conventional tests such as a dynamic derivative test and a large attack angle unsteady test, the wind tunnel test system still faces some problems: 1) the traditional horizontal wind tunnel has inherent defects in a rotary flight test, and the problems of balance in model rotation and weight component of a rotary part are difficult to solve because the gravity direction of the model is vertical to the axis of a wind tunnel test section; 2) the free pitching/rolling wind tunnel test technology is still a blank of national research, and as the flying wing type aircraft is easy to enter a dangerous out-of-control rolling state during flying, the mechanism and improvement measures of the phenomenon need to be deeply researched in the wind tunnel, so that the test requirement of the free pitching/rolling characteristic of the flying wing type aircraft is increased suddenly, and the existing wind tunnel test system cannot well meet the test requirement of the flying wing type aircraft and other unconventional layouts; 3) the existing free pitching/rolling device usually adopts a wingtip supporting mode penetrating through a fuselage, the supporting mode not only greatly damages the aerodynamic appearance of the flying wing type aircraft, but also seriously influences the accuracy and reliability of a test result, and even obtains a completely opposite test result; 4) the wingtip supporting mode makes the adjustment of the model rotation center position very difficult, the vertical plate is installed at the wingtip to seriously interfere the development of wingtip vortexes, the accuracy of a test result is influenced, and the adaptability of the supporting device to different models is poor.
Disclosure of Invention
The invention aims to provide a vertical wind tunnel model pitch-roll test device to solve the existing technical problems, wherein the device comprises:
the base is fixedly arranged on a tunnel wall platform of the vertical wind tunnel test section;
the bottom end of the upright post is fixedly connected with the base;
the supporting rod is positioned between the upright post and the abdomen supporting bent rod, one end of the supporting rod is fixedly connected with the top end of the upright post, the other end of the supporting rod is connected with one end of the abdomen supporting bent rod through a rotating assembly, and the axis of the supporting rod is parallel to the diameter direction of the wind tunnel test section;
the rotating assembly is arranged at one end of the supporting rod, which is far away from the upright post;
the installation seat is fixedly connected with one end of the web bracing bent rod, which is far away from the rotating assembly, the rotating axis of the web bracing bent rod is vertical to the incoming flow direction in the vertical wind tunnel, and the rotating axis of the web bracing bent rod is parallel to the rotating axis of the aircraft model;
the mounting seat is fixedly mounted on the belly of the aircraft model, the rotation axis of the aircraft model is intersected with the central axis of the vertical wind tunnel at the central point, and the central point is coincided with the mass center of the aircraft model.
Further, the rotating assembly includes: the device comprises an electromagnetic brake, a magnetic grid assembly, a deep groove ball bearing, a main shaft and a support rod torque balancing device, wherein the electromagnetic brake, the magnetic grid assembly, the deep groove ball bearing and the support rod torque balancing device are sequentially arranged on the main shaft along the direction from a support rod to a web-brace bent rod.
Further, the strut moment balancing device includes: heavy pole, counter weight, set nut, the counter weight passes through set nut installs on heavy pole.
Further, the device also comprises a balance 8, wherein one end of the balance 8 is fixedly arranged on the support rod 3, and the other end of the balance 8 is fixedly arranged at one end of the main shaft 44 far away from the belly brace bent rod 5.
Further, the support rod comprises a support part and a rotating part, the support part is fixedly arranged on one side of the rotating part, and the rotating part is connected with the upright post.
Further, the upright post is in a hollow structure and is in a round table shape.
Further, the cross section of the abdominal supporting bent rod is circular.
Furthermore, the support rods and the upright posts are made of 45 steel, and the web-bracing bent rods are made of T700 carbon fibers.
Further, the cross-sectional shape of the supporting part is a hollow structure NACA0009 airfoil, and the shape of the rotating part is cylindrical.
The invention also provides a use method of the vertical wind tunnel model pitch-roll test device, which comprises the following use steps:
step S10: installing a base on a tunnel wall platform of a vertical wind tunnel test section, and adjusting the direction and the levelness of the base;
step S20: mounting an upright column on the base, and adjusting the direction and the verticality of the base;
step S30: inserting a rotating part of a supporting rod into the top end of the upright post, and rotating the supporting rod to the position above the ground so that the supporting rod is positioned outside the wind tunnel test;
step S40: mounting a rotating assembly at the front end of the support part; sequentially installing an electromagnetic brake, a magnetic grid assembly, a deep groove ball bearing and a support rod moment balancing device on a main shaft along the direction from the support rod to the web bracing bent rod;
step S50: mounting a belly brace bent rod at the front end of the main shaft;
step S60: mounting a mounting seat at one end of the abdomen stay bent rod far away from the rotating assembly, and adjusting the levelness and direction of the mounting seat;
step S70: installing the aircraft model on the mounting seat, and adjusting the aircraft model to ensure that the mass center of the aircraft model coincides with the intersection point of the rotating axis and the wind tunnel test section axis
Step S80: and the supporting rod enters the wind tunnel test section through rotation of the rotating part, and the axis of the supporting part is adjusted to be parallel to the diameter direction of the test section and fixed.
The invention has the following beneficial effects:
(1) in the prior art, when an aircraft pitching test is carried out in a traditional wind tunnel, the gravity direction of an aircraft model is vertical to the incoming air flow direction, the aircraft model faces the self balance in the pitching process and the weight of a rotating device influences the test result in the test.
(2) The vertical wind tunnel model pitching-rolling test device has the advantages of simple structure, convenience in installation, good economy, no need of adaptive structural modification on a wind tunnel test section, high rigidity, high rotation precision and high simulation precision on the kinematics of an aircraft model.
(3) According to the invention, the pitch angle related information of the aircraft model can be measured and transmitted in real time through the rotating assembly, so that the free pitch and rolling characteristics of the aircraft model can be accurately obtained.
(4) The belly brace bent rod is connected with the belly of the aircraft model, the pneumatic appearance of the model is slightly influenced by adopting a belly brace mode, then the aircraft model can realize free rolling motion under the action of pneumatic force through the rotating assembly, the rotating axis of the belly brace bent rod is parallel to the rotating axis of the aircraft, so that the rolling axis of the aircraft model passes through the mass center of the aircraft model, and the aircraft model can be pitched and rolled for 360 degrees.
(5) The invention is applied in a vertical wind tunnel test, the test device in a wind tunnel test section is subjected to aerodynamic force in the direction opposite to the gravity, and in order to eliminate the influence of the aerodynamic moment on the web-strut bent rod on the model motion, the invention adopts a strut aerodynamic moment balancing device, balances the aerodynamic moment of the web-strut bent rod through calculation, has the characteristics of convenient installation and adjustment and scientific and reliable principle in the test, and improves the accuracy of the test result.
(6) The invention aims to better research the pitching and rolling motions of the aircraft model under the action of aerodynamic force, so that no other constraint exists in the test device.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of the structure of a test apparatus in an embodiment of the present invention;
FIG. 2 is a schematic top view of the test apparatus in an embodiment of the present invention;
FIG. 3 is a schematic view showing a partial structure of a connection between a pillar and a support rod in an embodiment of the present invention;
FIG. 4 is a schematic view of a rotating assembly in an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a support rod according to an embodiment of the present invention;
FIG. 6 is a schematic cross-sectional view of a support portion of a brace in an embodiment of the invention;
FIG. 7 is a schematic structural view of a web brace bending bar in an embodiment of the invention;
FIG. 8 is a perspective view of the structure of the present invention in an installed position;
FIG. 9 is an enlarged schematic view of the structure of a balance according to an embodiment of the present invention
FIG. 10 is a flow chart of a method of using the test device in an embodiment of the present invention.
The method comprises the following steps of 1-base, 2-upright post, 3-support rod, 31-support part, 32-rotating part, 4-rotating component, 41-electromagnetic brake, 42-magnetic grid component, 43-deep groove ball bearing, 44-main shaft, 45-support rod moment balancing device, 45-1-heavy rod, 45-2-counterweight, 45-3-positioning nut, 5-web support bent rod, 6-mounting seat, 7-aircraft model and 8-balance.
Detailed Description
The following description provides many different embodiments, or examples, for implementing different features of the invention. The particular examples set forth below are illustrative only and are not intended to be limiting.
Example 1:
the embodiment 1 of the invention provides a vertical wind tunnel model pitch-roll test device, wherein the test device comprises:
the base 1 is fixedly arranged on a tunnel wall platform of the vertical wind tunnel test section;
the bottom end of the upright column 2 is fixedly connected with the base 1;
the supporting rod 3 is positioned between the upright post 2 and the abdomen brace bending rod 5, one end of the supporting rod 3 is fixedly connected with the top end of the upright post 2, the other end of the supporting rod 3 is connected with one end of the abdomen brace bending rod 5 through a rotating assembly 4, and the axis of the supporting rod 3 is parallel to the diameter direction of the wind tunnel test section;
the rotating assembly 4 is arranged at one end of the support rod 3 far away from the upright post 2;
the end, far away from the rotating assembly 4, of the web-bracing bent rod 5 is fixedly connected with the mounting base 6, the rotating axis of the web-bracing bent rod 5 is perpendicular to the incoming flow direction in the vertical wind tunnel, and the rotating axis of the web-bracing bent rod 5 is parallel to the rotating axis of the aircraft model 7;
the mounting seat 6 is fixedly mounted on the belly of the aircraft model 7, the rotation axis of the aircraft model 7 is intersected with the central axis of the vertical wind tunnel at a central point, and the central point is coincided with the mass center of the aircraft model 7.
As shown in fig. 1, fig. 2 and fig. 3, the base 1 is fixedly installed on a tunnel wall platform of a vertical wind tunnel test section, and can be installed by using an original through hole on the surface of the tunnel wall platform, without performing adaptive transformation on the wind tunnel test section, and can also be fixed on the surface of the tunnel wall platform by welding and other modes.
The bottom of stand 2 with the upper surface of base 1 can adopt the mode of welding or screw thread screw to carry out fixed connection, and this scheme can also have a deformation mode, base 1 with stand 2 is integrated into one piece, and the axis of stand 2 sets up with the surface vertical of base 1 during the installation moreover, and the purpose is: 1) the aircraft model 7 is prevented from deviating from the axis of the wind tunnel test section during the test, so that the accuracy of the test result is prevented from being influenced; 2) because the aircraft model 7 needs to be rolled in the test process, and the weight of the aircraft model 7 is larger than that of the upright post, if the upright post 2 is obliquely arranged, the gravity center of the device is farther away from the wind tunnel wall, so that bolts at the joint of the base 1 and the upright post 2 are subjected to larger tensile stress and shearing stress, and the structural stability is poor; 3) since the invention aims to research the pitch-roll characteristics of the flying wing type aircraft, the device needs to ensure that the sideslip angle of the aircraft model is zero, and the rotation axis of the aircraft model 7 is parallel to the ground.
The one end of bracing piece 3 with can be connected through internal thread and external screw thread complex mode between the top of stand 2, also can adopt the mode of screw, joint to connect, the axis of bracing piece 3 is perpendicular with the axis of stand 2.
As shown in fig. 4, the rotating assembly 4 is located below the other end of the support rod 3, a mounting hole is provided below the other end of the support rod 3, one end of the rotating assembly 4 penetrates through the mounting hole to be connected with the web-supporting bent rod 5, and the web-supporting bent rod 5 is respectively connected with the rotating assembly 4 and the mounting base 6 through threads.
The belly of aircraft model 7 has seted up the entrance to a cave, belly brace curved bar 5 and mount pad 6 carry out in the belly of aircraft model 7 through the entrance to a cave, with aircraft model 7 in inner beam fixed connection, aircraft model 7 can carry out 360 rolling tests.
In the prior art, when a pitching test is performed in a traditional wind tunnel, the gravity direction of an aircraft model 7 is vertical to the incoming air flow direction, the aircraft model 7 faces the self balance in the pitching process and the rotational inertia of a rotating device in the test to influence the test result, the aircraft model can only pitch and cannot realize a 360-degree rolling test.
The vertical wind tunnel model pitching-rolling test device has the advantages of simple structure, convenience in installation, good economy, no need of adaptive structural modification on a wind tunnel test section, high rigidity, high rotation precision and high simulation precision on the kinematics of an aircraft model.
In the prior art, usually, the web-bracing bent rod 5 is installed at the tail part of the aircraft model 7 or right below the abdomen and the nose of the aircraft model 7, so that the effective pitching motion angle of the aircraft model 7 is not more than +/-40 degrees, and in the invention, the web-bracing bent rod 5 is fixedly connected with a cross beam at the abdomen of the aircraft model 7, and the influence on the aerodynamic shape of the model is small by adopting a web-bracing mode, then the aircraft model can realize free pitching and rolling motions under the action of the pneumatic force through the rotating component 4, wherein the rotating axis of the web-bracing bent rod is parallel to the rotating axis of the aircraft, so that the rolling axis of the aircraft model passes through the mass center of the aircraft model, and the aircraft model can be pitched at 360 degrees. The prior art is developed aiming at a conventional layout aircraft in a horizontal wind tunnel, and can not meet the special test requirements of free pitching-rolling of a flying wing aircraft in a vertical wind tunnel; the device in the prior art has large rotational damping, so that the measured angle data can not well reflect the pitching characteristic of the aircraft model, and the device adopts the special high-rotating-speed mixed ceramic bearing, the rotational damping of which is less than or equal to 0.002, thereby greatly reducing the influence on the data accuracy.
In order to better research the rolling motion of the aircraft model under the action of aerodynamic force, no other external constraint is set in the test device.
According to the embodiment 1 of the invention, the influence of Reynolds number, initial attack angle of the model, rotational inertia of the model and model state (deflection angle of a control plane) on the large pitch and rolling characteristics of the flying wing aircraft can be researched, the research on the reason of the aircraft generating out-of-control rolling in actual flight is facilitated, and a countermeasure for avoiding the generation of the out-of-control rolling is provided.
Further, the rotating assembly 4 includes: the device comprises an electromagnetic brake 41, a magnetic grid assembly 42, a deep groove ball bearing 43, a main shaft 44 and a support rod moment balancing device 45, wherein the electromagnetic brake 41, the magnetic grid assembly 42, the deep groove ball bearing 43 and the support rod moment balancing device 45 are sequentially arranged on the main shaft 44 along the direction from the support rod 3 to the web bracing bent rod 5.
As shown in fig. 4, when the aircraft model 7 is being tested, the electromagnetic brake assembly 41 in the rotating assembly 4 may not generate friction when not braking, and when the aircraft model 7 needs to be braked and an operator sets an attack angle of the aircraft model 7, the electromagnetic brake assembly may ensure that the aircraft model 7 is stationary.
According to the invention, the rotation angle of the pitch angle of the aircraft model can be measured and transmitted in real time in a non-contact manner through the magnetic grid assembly 42 in the rotating assembly 4, and no additional friction force is generated, so that the free pitch characteristic of the aircraft model can be accurately and timely obtained in the test process.
Further, the strut moment balancing device 45 includes: the weight rod 45-1, the counterweight 45-2 and the positioning nut 45-3, wherein the counterweight 45-2 is installed on the weight rod 45-1 through the positioning nut 45-3.
Further, the device also comprises a balance 8, wherein one end of the balance 8 is fixedly arranged on the support rod 3, and the other end of the balance 8 is fixedly arranged at one end of the main shaft 44 far away from the belly brace bent rod 5.
As shown in fig. 4, 8 and 9, the heavy rod 45-1 is mounted on the main shaft 44, and in order to eliminate the influence of the web-supporting bent rod 5 on the test, in the embodiment of the invention, the balance 8 is used to measure the pneumatic load of the web-supporting bent rod 5 and the moment generated around the main shaft 44 at different incoming air flow wind speeds, and then through the calculation of stress analysis, the required position and the required weight of the counterweight 45-2 on the main shaft are set, so as to reduce the influence of the web-supporting bent rod 5 on the test result.
The invention is applied in a vertical wind tunnel test, the test device is subjected to aerodynamic force in the direction opposite to the gravity, in order to eliminate the influence of the aerodynamic moment on the motion of the model by the web-strut bent rod, the invention adopts a strut aerodynamic moment balancing device, and balances the aerodynamic load of the web-strut bent rod by calculation, thereby having the characteristics of convenient installation and adjustment, scientific and reliable principle and improving the accuracy of the test result in the test.
Further, the support rod 3 comprises a support portion 31 and a rotating portion 32, the support portion 31 is fixedly mounted on one side of the rotating portion 32, and the rotating portion 32 is connected with the upright 2.
Further, the upright post 2 is in a hollow circular truncated cone shape.
The stand column 2 is in a circular truncated cone shape, and is internally of a hollow structure, so that the stability is ensured, and the weight of the structure is reduced.
The wing section supporting rod 3 is inserted into the top end of the upright post 2 through a rotating column at the rear end and is in loose fit, operation can be carried out on the ground when the device is assembled and a model is installed, the model can enter a vertical wind tunnel test section through rotation of the wing section supporting rod 3, and the device is simple and convenient to operate and high in safety.
As shown in fig. 5, the support rod 3 is composed of a two-part support part 31 and a rotation part 32, before the test is not started, the rotation part 32 is inserted into the top end of the upright post 2, at the moment, the two parts are loosely connected, the support rod 3 can rotate relative to the upright post 2, the operation can be performed on the ground and the wind tunnel test section is performed, the operation is simple, and the safety is high.
Further, the cross section of the abdomen stay rod 5 is circular.
As shown in fig. 7, the diameter of the web brace curved rod 5 is gradually reduced along the direction of the airplane model 7, and the structural size of the web brace curved rod can ensure that the centroid of the model coincides with the intersection point of the device rotation axis and the wind tunnel test section axis.
Wherein, the distance H between the axis of the long straight end of the web-brace curved bar 5 and the rotation axis of the aircraft model 7 is determined by considering three factors: a. the interference of the web-bracing bent rod 5 on a cross beam support of the aircraft model 7 is reduced as much as possible to ensure the accuracy of the test result; b. the moment of inertia of the web-brace curved bar 5 is as small as possible so as to reduce the influence on the model rotation; c. the rigidity of the web-bracing bent rod is as large as possible so as to ensure the accuracy of the motion of the aircraft model, and the optimal size of the web-bracing bent pipe 5 can be determined by balancing the three factors.
Further, the material of the support rod 3 and the upright post 2 is 45 steel, and the material of the web-brace bent rod 5 is T700 carbon fiber.
Further, the cross-sectional shape of the support part 31 is a hollow structure NACA0009 airfoil, and the shape of the rotating part 32 is a cylinder.
As shown in fig. 6, the supporting portion 31 is configured as an airfoil shape, so that the airflow can be guided to smoothly pass through the supporting portion 31, and the influence on the test is reduced.
Example 2:
the embodiment 2 of the invention also provides a use method of the vertical wind tunnel model pitch-roll test device, as shown in fig. 10, the use steps are as follows:
step S10: installing a base 1 on a tunnel wall platform of a vertical wind tunnel test section, and adjusting the direction and the levelness of the base 1;
step S20: installing an upright post 2 on the base 1, and adjusting the direction and the vertical degree of the base 1;
step S30: inserting a rotating part 32 of a support rod 3 into the top end of the upright post 2, adding lubricating grease between the rotating part 32 and the contact surface of the upright post 2, reducing friction, and rotating the support rod 3 to the upper part of the ground to enable the support rod 3 to be positioned outside a wind tunnel test;
step S40: mounting the rotating assembly 4 at the front end of the support portion 31; the electromagnetic brake 41, the magnetic grid assembly 42, the deep groove ball bearing 43 and the support rod moment balancing device 45 are sequentially arranged on the main shaft 44 along the direction from the support rod 3 to the web-brace bent rod 5; the axis of the main shaft 44 is parallel to the ground.
Step S50: the abdomen brace curved rod 5 is arranged at the front end of the main shaft 44, and when the abdomen brace curved rod is used, the abdomen brace curved rod 5 needs to be ensured to rotate flexibly without damping and clamping stagnation and cannot shake in the radial direction and the axial direction.
Step S60: mounting a mounting seat 6 at one end of the web-strut bent rod 5 far away from the rotating assembly 4, and adjusting the levelness and direction of the mounting seat 6;
step S70: and (3) installing the aircraft model 7 on the installation seat 6, and adjusting the aircraft model 7 to ensure that the mass center of the aircraft model 7 coincides with the intersection point of the rotating axis and the wind tunnel test section axis.
Step S80: and (3) enabling the support rod 3 to rotate through the rotating part 32 to enter a wind tunnel test section, adjusting the axis of the support part 31 to be parallel to the diameter direction of the test section, and fixing.
As shown in fig. 8-9, after the whole test device is installed, before the support rod 3 enters the wind tunnel test section, the installation position and weight of the support rod moment balancing device 45 need to be set, and the specific steps are as follows: firstly, one end of a balance 8 is arranged on a supporting part 31, the other end of the balance is connected with a main shaft 44 through a connecting piece, the pneumatic load of a web-bracing bent rod 5 and the moment generated around the main shaft 44 under different wind speeds and different rotating angles in a test section are measured, then the position of a required counterweight 45-2 on the main shaft and the required weight are set through stress analysis and calculation, and further the influence of the web-bracing bent rod 5 on a test result is reduced; the balance 8 is then removed and the support bar 3 is rotated into the wind tunnel test section to begin the test, as shown in figure 1.
The test device provided by the invention has good universality, can be used for carrying out free pitching/rolling test research on aircrafts of different models (particularly flying wing layout aircrafts), and has good engineering application prospect.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. The utility model provides a vertical wind tunnel model every single move-roll test device which characterized in that, test device includes:
the base (1), the said base (1) is fixedly mounted on test section tunnel wall platform of the vertical wind tunnel;
the bottom end of the upright post (2) is fixedly connected with the base (1);
the supporting rod (3) is positioned between the upright post (2) and the abdomen supporting bent rod (5), one end of the supporting rod (3) is fixedly connected with the top end of the upright post (2), the other end of the supporting rod is connected with one end of the abdomen supporting bent rod (5) through a rotating assembly (4), and the axis of the supporting rod (3) is parallel to the diameter direction of the wind tunnel test section;
the rotating assembly (4) is arranged at one end of the supporting rod (3) far away from the upright post (2);
the end, far away from the rotating assembly (4), of the web-bracing bent rod (5) is fixedly connected with the mounting seat (6), the rotating axis of the web-bracing bent rod (5) is perpendicular to the incoming flow direction in the vertical wind tunnel, and the rotating axis of the web-bracing bent rod (5) is parallel to the rotating axis of the aircraft model (7);
the mounting seat (6) is fixedly mounted on the belly of the aircraft model (7), the rotating axis of the aircraft model (7) is intersected with the central axis of the vertical wind tunnel at a central point, and the central point is coincided with the mass center of the aircraft model (7).
2. The vertical wind tunnel model pitch-roll test device according to claim 1, wherein the rotating assembly (4) comprises: electromagnetic braking ware (41), magnetic grid subassembly (42), deep groove ball bearing (43), main shaft (44), branch moment balancing unit (45), electromagnetic braking ware (41), magnetic grid subassembly (42), deep groove ball bearing (43), branch moment balancing unit (45) are followed bracing piece (3) are installed on main shaft (44) to the direction order of web-bracing curved bar (5).
3. A vertical wind tunnel model pitch-roll test apparatus according to claim 2, wherein the strut moment balancing means (45) comprises: the weight rod (45-1), the counterweight (45-2) and the positioning nut (45-3), wherein the counterweight (45-2) is installed on the weight rod (45-1) through the positioning nut (45-3).
4. The vertical wind tunnel model pitch-roll test device according to claim 2, further comprising a balance (8), wherein one end of the balance (8) is fixedly installed on the support rod (3), and the other end of the balance is fixedly installed at one end of the main shaft (44) far away from the web-brace bending rod (5).
5. The vertical wind tunnel model pitch-roll test device according to claim 1, wherein the support rod (3) comprises a support portion (31) and a rotating portion (32), the support portion (31) is fixedly installed on one side of the rotating portion (32), and the rotating portion (32) is connected with the upright column (2).
6. The vertical wind tunnel model pitch-roll test device according to claim 1, wherein the upright column (2) is in a hollow circular truncated cone shape.
7. The vertical wind tunnel model pitch-roll test device according to claim 1, wherein the cross section of the web brace rod (5) is circular.
8. The vertical wind tunnel model pitch-roll test device according to claim 1, wherein the support rods (3) and the upright posts (2) are made of 45# steel, and the web brace bending rods (5) are made of T700 carbon fibers.
9. The vertical wind tunnel model pitch-roll test device according to claim 5, wherein the cross-sectional shape of the support part (31) is a hollow structure of NACA0009 airfoil profile, and the shape of the rotating part (32) is a cylinder.
10. A use method of a vertical wind tunnel model pitch-roll test device is characterized by comprising the following steps:
step S10: installing a base (1) on a vertical wind tunnel test section tunnel wall platform, and adjusting the direction and the levelness of the base (1);
step S20: installing an upright post (2) on the base (1), and adjusting the direction and the verticality of the base (1);
step S30: inserting a rotating part (32) of a support rod (3) into the top end of the upright post (2), and rotating the support rod (3) to the upper part of the ground to enable the support rod (3) to be positioned outside a wind tunnel test;
step S40: mounting the rotating assembly (4) at the front end of the support part (31); sequentially installing an electromagnetic brake (41), a magnetic grid assembly (42), a deep groove ball bearing (43) and a support rod moment balancing device (45) on a main shaft (44) along the direction from the support rod (3) to the web brace bent rod (5);
step S50: mounting a belly brace bent rod (5) at the front end of the main shaft (44);
step S60: mounting a mounting seat (6) at one end of the abdomen stay bent rod (5) far away from the rotating assembly (4), and adjusting the levelness and direction of the mounting seat (6);
step S70: installing an aircraft model (7) on the installation seat (6), and adjusting the aircraft model (7) to enable the mass center of the aircraft model (7) to be superposed with the intersection point of the rotating axis and the axis of the wind tunnel test section;
step S80: and (3) enabling the support rod (3) to rotate through the rotating part (32) to enter a wind tunnel test section, adjusting the axis of the support part (31) to be parallel to the diameter direction of the test section, and fixing.
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| CN115508038A (en) * | 2022-08-30 | 2022-12-23 | 中国航天空气动力技术研究院 | Test device for high-speed wind tunnel ultra-large attack angle pitching and rolling double-freedom-degree motion |
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| CN115508038A (en) * | 2022-08-30 | 2022-12-23 | 中国航天空气动力技术研究院 | Test device for high-speed wind tunnel ultra-large attack angle pitching and rolling double-freedom-degree motion |
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| CN116242575A (en) * | 2023-05-08 | 2023-06-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual flight test device of low-speed wind tunnel |
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