CN107036781B - Low-damping three-degree-of-freedom supporting device based on virtual flight test model - Google Patents
Low-damping three-degree-of-freedom supporting device based on virtual flight test model Download PDFInfo
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- CN107036781B CN107036781B CN201710425609.7A CN201710425609A CN107036781B CN 107036781 B CN107036781 B CN 107036781B CN 201710425609 A CN201710425609 A CN 201710425609A CN 107036781 B CN107036781 B CN 107036781B
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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
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Abstract
The invention relates to a low damping three-degree-of-freedom supporting device based on a virtual flight test model, which can enable the model to realize free coupling rotation in three directions of pitching, rolling and yawing by being fixedly connected with the virtual flight test model. In addition, the three-degree-of-freedom two-by-two locking can also realize the single-degree-of-freedom motion function of the model. The device mainly comprises a free rolling kinematic pair, a free pitching kinematic pair and a free yawing kinematic pair. And each kinematic pair is connected through a bearing assembly, so that the free rotation of the model attitude angle is realized. The invention has the advantages of small motion damping, small interference to the wind tunnel flow field, adjustable motion range, light weight, convenient operation and maintenance and the like.
Description
Technical Field
The invention relates to a low-damping three-degree-of-freedom supporting device based on a virtual flight test model.
Background
The wind tunnel virtual flight test technology is an advanced wind tunnel test and evaluation technology which is put forward in the last U.S. of the last century, and the technology provides a method for evaluating and verifying the flight control system design in the wind tunnel, so that the control system design and the aerodynamic characteristic research are developed in parallel, and the problems of the control system are found out in the initial stage of the research, thereby greatly reducing the risk of the flight test and shortening the research and development period. The technique can safely and effectively evaluate the influence of unsteady aerodynamic force on the flight quality and the flight control system of the aircraft, and is called as a bridge between wind tunnel tests and flight tests.
The virtual flight test requires the model to generate aerodynamic force through the action of the control surface in an angle free state, controls the model posture to move according to the requirement, and aims to establish a research means of aerodynamic/movement/control integration, and the test system can be used for identifying aerodynamic parameters of the model, verifying a flight control law, verifying various maneuvering movement forms and the like.
The wind tunnel virtual flight test is independent of a supporting system, and the supporting system is a foundation and a key for guaranteeing the reliability of test results. The test requires that the aircraft model is mounted on a special supporting device with a rotational degree of freedom so as to realize free pitching, yawing and rolling, and the dynamic movement process of the aircraft is simulated more realistically so as to realize virtual flying.
The traditional wind tunnel test model supporting device usually adopts a series mechanism, the number of the degrees of freedom of the mechanism depends on the number of corresponding movable shafts and rotating shafts, the weight is large, the movement range is difficult to adjust, and the damping is large.
Disclosure of Invention
Based on the defects, the low-damping three-degree-of-freedom supporting device based on the virtual flight test model provided by the invention enables the virtual flight test model to realize free coupling rotation in three directions of pitching, rolling and yawing, thereby ensuring the test data precision of the virtual flight wind tunnel.
The technical scheme of the invention is as follows: the low damping three-degree-of-freedom supporting device based on the virtual flight test model comprises a free rolling kinematic pair, a free pitching kinematic pair and a free yawing kinematic pair, wherein the free rolling kinematic pair is connected with the two ends of the upper part of the free pitching kinematic pair in the axial direction through a pair of rolling deep groove ball bearings which are symmetrically arranged in the two ends of the free pitching kinematic pair, rolling bearing end covers and rolling bearing adjusting gaskets which are integrated with shafts are arranged at the two ends of the free rolling kinematic pair, and the free rolling kinematic pair is fixed by adopting screws so as to ensure the normal rotation of the rolling deep groove ball bearings when the model is in free rolling motion; the radial direction of the free pitching kinematic pair is connected with the free yawing kinematic pair through a pair of pitching deep groove ball bearings, the pair of pitching deep groove ball bearings are symmetrically arranged in grooves at the upper end of the free yawing kinematic pair, two ends of the free pitching kinematic pair are respectively provided with a pitching bearing end cover and a pitching bearing adjusting gasket which are integrated with a shaft, and the pitching deep groove ball bearings are fixed by screws so as to ensure the normal rotation of the pitching deep groove ball bearings when the model does free pitching motion; a pair of yaw deep groove ball bearings are axially arranged at the lower end of the free yaw kinematic pair, a shaft sleeve is arranged between the two yaw deep groove ball bearings, a yaw kinematic bearing mounting seat is sleeved outside the yaw deep groove ball bearings, the bottom end of the free yaw kinematic pair is in contact with a lock nut with a groove, an adjusting washer is arranged on the upper end ring of the lock nut in an alignment mode, the bottom is locked and fixed through screws, a yaw kinematic bearing end cover is sleeved outside the free yaw kinematic pair, the upper portion ring of the yaw kinematic bearing end cover is connected with the yaw kinematic bearing mounting seat through screws, and the lower end of the yaw kinematic bearing end cover is connected with a yaw strut through a straight port.
The invention also has the following technical characteristics:
1. four rolling limit screws for adjusting the rolling angle are symmetrically arranged at the four inner corners of the free rolling kinematic pair, and the maximum angle of the rolling motion can be adjusted or limited according to the actual test requirement.
2. Two pitching limiting screws for adjusting the pitching angle are symmetrically arranged at the lower end of the shaft sleeve of the free pitching kinematic pair in the radial direction, and the maximum pitching angle can be adjusted or limited according to actual test requirements.
3. A clearance is reserved between the lock nut connected with the free yaw kinematic pair and an external yaw kinematic bearing end cover, and meanwhile, two symmetrical bosses are arranged on the lock nut in the radial direction.
4. And three yaw limit screws are annularly arranged on the end cover of the yaw motion adjusting bearing, and the maximum angle for adjusting or limiting yaw motion is achieved through adjusting the three yaw limit screws.
The invention has important practical significance for the virtual flight wind tunnel test, is the key and the basis of the virtual flight wind tunnel test, and has very wide application prospect. By adopting the design scheme, the test model can realize free coupling rotation in three directions of pitching, rolling and yawing, and simultaneously three degrees of freedom can be locked two by two, so that the single degree of freedom motion function of the model can be realized, and small-angle limiting can be performed to facilitate the installation and debugging of the model. The free rotation in all directions is realized through a high-precision combined rolling bearing, so that the low motion damping of the bearing is ensured. Meanwhile, the device has small influence on the smoothness of the flow field in the wind tunnel, meets the requirement of supporting strength, and has the advantages of adjustable movement range, light weight, convenient operation and maintenance and the like.
Drawings
FIG. 1 is a front cross-sectional view of the superstructure of the device of the present invention;
FIG. 2 is a side cross-sectional view of the lower structure of the device of the present invention;
wherein, 1, a free rolling kinematic pair, 2, a free pitching kinematic pair, 3, a free yawing kinematic pair, 4, a screw, 5, a rolling bearing end cover, 6, a rolling bearing adjusting gasket, 7, a rolling deep groove ball bearing, 8, a pitching limiting screw, 9 and a pitching bearing end cover, 10, a pitching bearing adjusting gasket, 11, a pitching deep groove ball bearing, 12, a yawing deep groove ball bearing, 13 and a yawing motion bearing mounting seat, 14, shaft sleeves, 15, adjusting washers, 16, lock nuts, 17 and yaw motion bearing end caps, 18 are yaw struts.
Detailed Description
The following specific examples are set forth in connection with the drawings of the specification to further illustrate the technical scheme of the invention.
Example 1
1-2, a low-damping three-degree-of-freedom supporting device based on a virtual flight test model comprises a free rolling kinematic pair 1, a free pitching kinematic pair 2 and a free yawing kinematic pair 3, wherein a mounting screw hole connected with a virtual flight test model main body is reserved on the free rolling kinematic pair 3, the free rolling kinematic pair 1 is connected with two ends of the upper part of the free pitching kinematic pair 2 in the axial direction through a pair of rolling deep groove ball bearings 7, the rolling deep groove ball bearings 7 are symmetrically arranged in two ends of the free pitching kinematic pair 2, rolling bearing end covers 5 and rolling bearing adjusting gaskets 6 which are integrated with shafts are arranged at two ends of the free rolling kinematic pair 1, and the normal rotation of the rolling deep groove ball bearings 7 during free rolling motion of the model is ensured by adopting screw fixation; the radial direction of the free pitching kinematic pair 2 is connected with the free yawing kinematic pair 3 through a pair of pitching deep groove ball bearings 11, the pair of pitching deep groove ball bearings 11 are symmetrically arranged in grooves at the upper end of the free yawing kinematic pair 3, two ends of the free pitching kinematic pair 2 are respectively provided with a pitching bearing end cover 9 and a pitching bearing adjusting gasket 10 which are integrated with a shaft, and the two ends of the free pitching kinematic pair 2 are fixed by screws, so that the normal rotation of the pitching deep groove ball bearings 11 of the model in free pitching motion is ensured; the axial of the lower extreme of the free yaw kinematic pair 3 is equipped with a pair of driftage deep groove ball bearings 12, is furnished with axle sleeve 14 between two driftage deep groove ball bearings 12, and the outside cover has driftage kinematic bearing mount pad 13, contacts with the lock nut 16 that has the recess in the bottom of free yaw kinematic pair 3, and lock nut upper end hoop is furnished with adjustment washer 15, and the bottom adopts the screw locking to fix, and the outside cover has driftage kinematic bearing end cover 17, and the upper portion hoop of driftage kinematic bearing end cover 17 adopts the screw to link with driftage kinematic bearing mount pad 13, and the lower extreme is as straight mouth and yaw branch 18 hookup. Four rolling limit screws for adjusting the rolling angle are symmetrically arranged at four inner corners of the free rolling kinematic pair 1. Two pitching limiting screws 8 for adjusting the pitching angle are symmetrically arranged at the lower end of the shaft sleeve of the free pitching kinematic pair 2 in the radial direction. A clearance is left between the lock nut 16 connected with the free yaw motion pair 3 and the outer yaw motion bearing end cap 17, and the lock nut 16 is provided with two symmetrical bosses in the radial direction.
The free rolling kinematic pair is connected with the main body of the virtual flight test model, and is connected with the auxiliary shaft direction of the free pitching kinematic pair through a pair of high-precision deep groove ball bearings, when the model is free to roll in a wind tunnel, radial load and axial load can be borne at the same time, and the two pairs of deep groove ball bearings are symmetrically arranged, so that the normal rotation of the deep groove ball bearings during the free rolling motion of the model is ensured. Similarly, the radial direction of the free pitching kinematic pair is connected with the radial direction of the free yawing kinematic pair through a pair of high-precision deep groove ball bearings, and the two pairs of deep groove ball bearings are symmetrically arranged, so that the normal rotation of the deep groove ball bearings during free pitching motion of the model is ensured. The free yaw kinematic pair is connected with the yaw strut in the axial direction through a group of high-precision deep groove ball bearings, so that free yaw motion is realized. The model can bear radial load and axial load simultaneously when free rolling motion is carried out in the wind tunnel. And controlling the movement of the model by controlling the deflection of the control surface of the virtual flight test model, and finally realizing the simulation of the flight state of the wind tunnel test model.
Four rolling limit screws for adjusting the rolling angle are symmetrically arranged at four inner corners of the free rolling kinematic pair, and the positions of the screws can be adjusted according to actual needs so as to limit the rolling angle. Two pitching limiting screws for adjusting the pitching angle are symmetrically arranged at the lower end of the shaft sleeve of the free pitching kinematic pair in the radial direction, and the positions of the screws can be adjusted according to actual needs so as to adjust and limit the pitching angle. A clearance is reserved between a lock nut connected with the free yaw kinematic pair and an external yaw kinematic bearing end cover, and two symmetrical bosses are arranged in the radial direction. By adjusting three yaw limit screws circumferentially arranged on the yaw movement bearing end cover 17, the required maximum angle for adjusting or limiting yaw movement can be achieved.
The three-degree-of-freedom supporting device of the embodiment has been successfully applied to a virtual flight wind tunnel test of an aircraft. The device has the advantages of low damping, small interference to the wind tunnel flow field, adjustable movement range and the like, is flexible to move when applied to a virtual flight wind tunnel test, and is convenient to install and detach.
Claims (5)
1. The utility model provides a low damping three degree of freedom strutting arrangement based on virtual flight test model, includes by free roll kinematic pair (1), free every single move kinematic pair (2) and free yaw kinematic pair (3), its characterized in that: the free rolling kinematic pair (1) is connected with the two ends of the upper part of the free pitching kinematic pair (2) in the axial direction through a pair of rolling deep groove ball bearings (7), the rolling deep groove ball bearings (7) are symmetrically arranged in the two ends of the free pitching kinematic pair (2), rolling bearing end covers (5) and rolling bearing adjusting gaskets (6) which are integrated with the shafts are arranged at the two ends of the free rolling kinematic pair (1), and the normal rotation of the rolling deep groove ball bearings (7) during the free rolling motion of the model is ensured by adopting screw fixation; the radial direction of the free pitching kinematic pair (2) is connected with the free yawing kinematic pair (3) through a pair of pitching deep groove ball bearings (11), the pair of pitching deep groove ball bearings (11) are symmetrically arranged in grooves at the upper end of the free yawing kinematic pair (3), two ends of the free pitching kinematic pair (2) are respectively provided with a pitching bearing end cover (9) and a pitching bearing adjusting gasket (10) which are integrated with a shaft, and the two ends of the free pitching kinematic pair are fixed by screws, so that the normal rotation of the pitching deep groove ball bearings (11) of the model in free pitching motion is ensured; a pair of yaw deep groove ball bearings (12) are axially arranged at the lower end of the free yaw kinematic pair (3), a shaft sleeve (14) is arranged between the two yaw deep groove ball bearings (12), a yaw kinematic bearing mounting seat (13) is sleeved outside, the bottom end of the free yaw kinematic pair (3) is contacted with a lock nut (16) with a groove, an adjusting washer (15) is arranged at the upper end of the lock nut in a circumferential direction, a screw is adopted for locking and fixing the bottom, an adjusting yaw kinematic bearing end cover (17) is sleeved outside, screws are adopted for connecting the upper circumferential direction of the adjusting yaw kinematic bearing end cover (17) with the yaw kinematic bearing mounting seat (13), and the lower end of the adjusting yaw kinematic bearing end cover is connected with a yaw strut (18) as a straight opening.
2. The low damping three degree of freedom support device based on a virtual flight test model of claim 1, wherein: four rolling limit screws for adjusting the rolling angle are symmetrically arranged at four inner corners of the free rolling kinematic pair (1).
3. The low damping three degree of freedom support device based on a virtual flight test model of claim 1, wherein: two pitching limiting screws (8) for adjusting the pitching angle are symmetrically arranged at the lower end of the shaft sleeve of the free pitching kinematic pair (2) in the radial direction.
4. The low damping three degree of freedom support device based on a virtual flight test model of claim 1, wherein: a gap is reserved between a lock nut (16) connected with the free yaw kinematic pair (3) and an end cover (17) of the yaw motion adjusting bearing, and meanwhile, the lock nut (16) is radially provided with two symmetrical bosses.
5. The low damping three degree of freedom support device based on a virtual flight test model of claim 1, wherein: three yaw limit screws are circumferentially arranged on the yaw motion adjusting bearing end cover (17), and the maximum angle for adjusting or limiting yaw motion is achieved through adjusting the three yaw limit screws.
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| CN201710425609.7A CN107036781B (en) | 2017-06-08 | 2017-06-08 | Low-damping three-degree-of-freedom supporting device based on virtual flight test model |
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| CN201710425609.7A CN107036781B (en) | 2017-06-08 | 2017-06-08 | Low-damping three-degree-of-freedom supporting device based on virtual flight test model |
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