CN116046330B - Three-degree-of-freedom virtual flight test device capable of ventilating - Google Patents
Three-degree-of-freedom virtual flight test device capable of ventilating Download PDFInfo
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- CN116046330B CN116046330B CN202310325515.8A CN202310325515A CN116046330B CN 116046330 B CN116046330 B CN 116046330B CN 202310325515 A CN202310325515 A CN 202310325515A CN 116046330 B CN116046330 B CN 116046330B
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention relates to a three-degree-of-freedom virtual flight test device capable of ventilating, belongs to the field of special test equipment for wind tunnels, and solves the problem that airflow flow in a model area is influenced by an air supply pipeline. The invention flows high-pressure air into the pitch axis direction from an external air source end through the yaw axis direction and then flows into the roll axis direction, finally flows out of the air outlet hose, provides stable high-pressure air for a model in the free rotation process, and the encoders and the brakes are all arranged on respective angle shafts, and brakes and unlock the rotation angles by feeding back the rotation angles of the device in real time.
Description
Technical Field
The invention relates to the field of wind tunnel test equipment, in particular to a three-degree-of-freedom virtual flight test device capable of ventilating.
Background
The wind tunnel virtual flight test is an important means for evaluating the stability characteristics of the aircraft, and the wind tunnel virtual flight test utilizes the three-degree-of-freedom supporting device to realize the free motion of the aircraft model around three degrees of freedom of pitching, rolling and yawing. With the development of advanced aircrafts, new requirements are put forward on the simulation capability and the authenticity of a wind tunnel virtual flight test, and high-pressure gas needs to be supplied into a virtual flight test model, so that the virtual flight test model has the capability of verifying advanced control measures such as thrust vectors, jet control and the like. The existing three-degree-of-freedom virtual flight test mechanism does not have the condition of high-pressure air supply, so that the high-pressure air supply scheme widely adopted at present is external, namely, an interface connected with an external high-pressure pipeline is arranged at the back of the virtual flight test model, so that the airflow flowing characteristic of a flight test model area is influenced by the high-pressure air supply pipeline, meanwhile, the movement angle range of the three-degree-of-freedom virtual flight test device is limited by the interface at the back of the model and the external high-pressure pipeline, and the reality of model movement characteristic simulation is reduced.
Disclosure of Invention
Aiming at the problems, the invention provides the ventilated three-degree-of-freedom virtual flight test device, which solves the problem that the airflow flow characteristic of a flight test model area is influenced by a high-pressure air supply pipeline, and simultaneously solves the problem that a back interface of the flight test model and an external high-pressure pipeline limit the movement angle range of the three-degree-of-freedom virtual flight test device.
The technical scheme adopted by the invention is as follows: the three-degree-of-freedom virtual flight test device comprises an air outlet hose, an air outlet rotary joint, a joint fixing seat, a model mounting seat, a rolling shaft seat, an air outlet hard tube, an air outlet shaft, a rolling encoder, a rolling brake, a rolling angle shaft, a yaw shaft seat, a yaw encoder, a yaw brake, an air inlet rotary joint, an air inlet hose, a transition supporting rod, a pitching encoder, a pitching brake, a pitching shaft and an L-shaped air outlet rotary joint, wherein the air outlet hose is arranged at the inner side of an aircraft model and is relatively fixed with the position of the aircraft model, the air outlet rotary joint is fixed in an inner hole at the outer side of a front blanking cover through the joint fixing seat, and the front blanking cover is fixedly connected with the outer end face of a front inner hole of the model mounting seat; the inner ring of the front low-damping rolling bearing is sleeved on the shaft neck of the front blanking cover, and the front end rotating ring of the rolling shaft seat is arranged on the outer ring of the front low-damping rolling bearing; the inner ring of the rear low-damping rolling bearing is sleeved on the shaft neck of the rear blanking cover, the rear end rotating ring of the rolling shaft seat is arranged on the outer ring of the rear low-damping rolling bearing, the front end of the rolling angle shaft penetrates through the central hole of the rear blanking cover, the rear end of the rolling angle shaft is fixedly connected with the outer side end face of the rear blanking cover, the rear blanking cover is fixedly connected with the outer side end face of the rear inner hole of the model mounting seat, the rolling axis of the rolling shaft seat is coincident with the rolling axis of the model mounting seat, and the aircraft model is mounted on the model mounting seat, so that free rolling motion of the aircraft model is realized; the internal braking hole of the rolling brake is sleeved on the rolling angle shaft, the rolling brake is fixedly connected with the end face of the rear end rotating ring of the rolling shaft seat, the rolling encoder is fixed at the rear end of the rolling shaft seat through the rolling encoder mounting seat, the internal ring of the rolling encoder is sleeved on the other end of the rolling angle shaft, the rolling encoder feeds back the rolling angle of the aircraft model in real time, and the rolling brake can brake and unlock the rolling angle of the aircraft model.
The ventilation shaft comprises a pitching shaft seat and a yawing shaft which are of an integral structure, the pitching shaft seat is positioned at the upper end of the yawing shaft, a boss structure is arranged at the transition part of the pitching shaft seat and the yawing shaft, and the central shaft of the pitching shaft seat and the central shaft of the yawing shaft are mutually perpendicular and intersected; the left inner hole side wall of the pitching shaft seat is fixedly connected with the outer ring of the left low-damping pitching bearing, the right inner hole side wall of the pitching shaft seat is fixedly connected with the outer ring of the right low-damping pitching bearing, the left blanking cover and the right blanking cover are both provided with central holes, the left blanking cover is fixedly connected with the inner ring of the left low-damping pitching bearing, the right blanking cover is fixedly connected with the inner ring of the right low-damping pitching bearing, the left rotating ring of the rolling shaft seat is sleeved on the left blanking cover and is fixedly connected with the left blanking cover, and the right rotating ring of the rolling shaft seat is sleeved on the right blanking cover and is fixedly connected with the right blanking cover; one end of the pitching shaft penetrates through the center hole of the left blanking cover and is fixedly connected with the center of the left end face of the pitching shaft seat, and the pitching axis of the pitching shaft seat, the pitching axis of the rolling shaft seat and the pitching axis of the model mounting seat are overlapped, so that free pitching motion of the aircraft model is realized; the side surface of the pitching brake is fixedly connected with the inner hole boss of the left blanking cover, and the braking hole of the pitching brake is sleeved on the pitching shaft, so that the pitching angle of the aircraft model can be braked and unlocked according to test requirements; the pitching encoder is fixedly connected with the outer side end face of the left blanking cover through a pitching encoder mounting seat, an inner ring of the pitching encoder is sleeved on the other end of the pitching shaft, and the pitching encoder feeds back the pitching angle of the aircraft model in real time.
The upper section of the yaw shaft is arranged in an inner hole of the yaw shaft seat through a pair of low-damping yaw bearings, the lower plane of the boss structure is contacted with the upper end face of the yaw shaft seat, a locking unit is sleeved between the upper section and the middle section of the yaw shaft, and the yaw shaft seat are axially locked through the locking unit and the boss structure, so that free yaw movement of the aircraft model is realized; the transition support rod is sleeved outside the yaw shaft seat and fixedly connected with the yaw shaft seat, and the tail end of the transition support rod is fixedly connected with the support rod through a flange; the yaw brake is positioned at the tail end of the inner hole of the transition supporting rod, the outer ring of the yaw brake is fixedly connected with the stepped inner wall of the tail end of the inner hole of the transition supporting rod, the braking hole in the yaw brake is sleeved at the lower section of the yaw shaft, and the yaw brake brakes and unlocks the yaw angle of the aircraft model; the yaw encoder is located in the inner hole of the transition supporting rod, the inner ring of the yaw encoder is sleeved on the lower section of the yaw shaft, the outer ring of the yaw encoder is fixedly connected with the inner wall of the transition supporting rod, and the yaw encoder feeds back the yaw angle of the aircraft model in real time.
The air inlet hose provides stable high-pressure air flow input for the flight test device, an air inlet cavity is formed in the air inlet shaft from top to bottom, an opening at one end of the air inlet cavity is located at the center of the right inner hole end face of the pitching shaft seat, an opening at the other end of the air inlet hose is located at the center of the tail end face of the yawing shaft, one end of the air inlet rotary joint is connected with the air inlet hose through an air inlet rotary joint flange, the other end of the air inlet rotary joint is connected with the tail end face of the yawing shaft, high-pressure air flow is introduced to the yawing shaft direction from outside, one end of the L-shaped air inlet rotary joint is connected with the right inner hole end face of the pitching shaft seat, the other end of the L-shaped air inlet rotary joint is connected with one end of the air inlet hard tube, high-pressure air flow is introduced to the pitching shaft direction from the yawing shaft direction, and the other end of the air inlet hard tube is connected with the air outlet hose through the air outlet rotary joint, and high-pressure air flow is introduced into the aircraft model from the pitching shaft direction.
Further, the yaw shaft comprises an air inlet rotary joint stop sleeve, wherein the air inlet rotary joint stop sleeve is positioned in an inner hole of the supporting rod, the outer ring of the air inlet rotary joint stop sleeve is fixedly connected with the inner wall of the supporting rod, and the inner ring of the air inlet rotary joint stop sleeve is fixedly connected with the air inlet rotary joint to limit the air inlet rotary joint to rotate along with the yaw shaft.
Further, still including rotary joint stop ring and the L type rotary joint brake sleeve that ventilates of giving vent to anger, rotary joint stop ring and the outside terminal surface fixed connection of the front end rotation circle of the spin base of giving vent to anger, the interior terminal surface of rotary joint stop ring of giving vent to anger block rotary joint, the outside terminal surface fixed connection of L type rotary joint brake sleeve and right blanking cover that ventilates, L type rotary joint brake sleeve that ventilates block L type rotary joint that ventilates to avoid ventilating hard tube in the free rotation in-process of aircraft model receive torsion effect and damage.
Furthermore, the front side and the rear side of the upper plane of the boss structure are provided with pitching hard limiting parts for limiting the pitching angle of the aircraft model.
Furthermore, the bottoms of the front end rotating ring and the rear end rotating ring of the rolling shaft seat are provided with rolling hard limiting plates for limiting the rolling angle of the aircraft model.
Further, the rolling axis of the model mounting seat, the pitching axis and the yaw axis of the ventilation shaft are intersected at a point, and the point coincides with the mass center of the aircraft model, so that extra additional moment interference generated by the flight test device on the aircraft model in the test process is avoided.
The invention has the advantages and beneficial effects that: the air outlet hose and the aircraft are fixed in relative positions, so that the problem that an air supply pipeline is wound and knotted when the air supply pipeline rotates freely in the test process is avoided, and the high-pressure air source is ensured to stably enter the interior of the model through the three-degree-of-freedom virtual flight test device in the virtual flight test process. Meanwhile, according to the structural characteristics of the device, the encoder and the brake are designed on each rotating shaft, the running angle of the flight test device can be fed back in real time, and the running angle of the flight test device can be automatically braked and unlocked, so that the test efficiency is greatly improved. The flight test device can effectively inhibit the interference of aerodynamic characteristics caused by the damage of the flight test device to the aerodynamic structure of the aircraft model, and provides more real and stable data for the development of the aircraft, so that the virtual flight test model has the capability of verifying advanced control measures such as thrust vectors, jet control and the like; the encoder, the brake and the rotary joint of each shaft are integrally arranged in the flight test device, and the flight test device has the advantages of small volume, compact structure, small occupied internal space of a model and convenience and quickness in installation.
Drawings
FIG. 1 is a perspective view of the device of the present invention;
FIG. 2 is a top view of the device of the present invention;
FIG. 3 is a cross-sectional view taken along the direction A-A in FIG. 2;
fig. 4 is a cross-sectional view taken along the direction B-B in fig. 2.
Detailed Description
The invention is described in further detail below with reference to the accompanying examples of the specification.
Example 1
As shown in fig. 1 to 4, a three-degree-of-freedom virtual flight test apparatus capable of ventilation includes an air outlet hose 1, an air outlet rotary joint 2, a joint fixing seat 3, a model mounting seat 5, a rolling shaft seat 7, a ventilation hard pipe 10, a ventilation shaft, a rolling encoder 13, a rolling brake 15, a rolling angle shaft 16, a yaw shaft seat 18, a yaw encoder 23, a yaw brake 24, an air inlet rotary joint 25, an air inlet hose 28, a transition strut 20, a strut 29, a pitch encoder 30, a pitch brake 33, a pitch shaft 34 and an L-shaped ventilation rotary joint 36, and is characterized in that: the air outlet hose 1 is arranged on the inner side of the aircraft model and is fixed relative to the aircraft model in position, as shown in fig. 3, the air outlet rotary joint 2 is fixed in an inner hole on the outer side of the front blanking cover 4 through the joint fixing seat 3, and the front blanking cover 4 is fixedly connected with the outer end face of the front inner hole 51 of the model mounting seat 5; the inner ring of the front low-damping rolling bearing 6 is sleeved on the shaft neck of the front blanking cover 4, and the front end rotating ring 71 of the rolling shaft seat 7 is arranged on the outer ring of the front low-damping rolling bearing 6; the inner ring of the rear low-damping rolling bearing 39 is sleeved on the shaft neck of the rear blanking cover 17, the rear end rotating ring 72 of the rolling shaft seat 7 is arranged on the outer ring of the rear low-damping rolling bearing 39, the front end of the rolling angle shaft 16 penetrates through the central hole of the rear blanking cover 17, the rear end of the rolling angle shaft 16 is fixedly connected with the outer side end face of the rear blanking cover 17, the rear blanking cover 17 is fixedly connected with the outer side end face of the rear inner hole 52 of the model mounting seat 5, the rolling axis of the rolling shaft seat 7 coincides with the rolling axis of the model mounting seat 5, and the aircraft model is mounted on the model mounting seat 5, so that free rolling movement of the aircraft model is realized; the inside braking hole of the rolling brake 15 is sleeved on the rolling angle shaft 16, the rolling brake 15 is fixedly connected with the end face of the rear end rotating ring 72 of the rolling shaft seat 7, the rolling encoder 13 is fixed at the rear end of the rolling shaft seat 7 through the rolling encoder mounting seat 14, the inner ring of the rolling encoder 13 is sleeved on the other end of the rolling angle shaft 16, the rolling encoder 13 feeds back the rolling angle of the aircraft model in real time, and the rolling brake 15 can brake and unlock the rolling angle of the aircraft model.
As shown in fig. 3-4, the ventilation shaft comprises a pitching shaft seat 12 and a yawing shaft 41 which are integrally formed, the pitching shaft seat 12 is positioned at the upper end of the yawing shaft 41, a boss structure is arranged at the transition part of the pitching shaft seat 12 and the yawing shaft 41, and the central axis of the pitching shaft seat 12 and the central axis of the yawing shaft 41 are mutually perpendicular and intersected; the left inner hole side wall of the pitching shaft seat 12 is fixedly connected with the outer ring of the left low damping pitching bearing 35, the right inner hole side wall of the pitching shaft seat 12 is fixedly connected with the outer ring of the right low damping pitching bearing 40, the left blanking cover 32 and the right blanking cover 37 are provided with central holes, the left blanking cover 32 is fixedly connected with the inner ring of the left low damping pitching bearing 35, the right blanking cover 37 is fixedly connected with the inner ring of the right low damping pitching bearing 40, the left rotating ring 73 of the rolling shaft seat 7 is sleeved on the left blanking cover 32 and fixedly connected with the left blanking cover, and the right rotating ring 74 of the rolling shaft seat 7 is sleeved on the right blanking cover 37 and fixedly connected with the right blanking cover 37; one end of the pitching shaft 34 passes through the central hole of the left blanking cover 32 and is fixedly connected with the center of the left end face of the pitching shaft seat 12, and the pitching axis of the pitching shaft seat 12, the pitching axis of the rolling shaft seat 7 and the pitching axis of the model mounting seat 5 are overlapped, so that the free pitching motion of the aircraft model is realized; the side surface of the pitching brake 33 is fixedly connected with an inner hole boss of the left blanking cover 32, and a braking hole of the pitching brake 33 is sleeved on the pitching shaft 34, so that the pitching angle of the aircraft model can be braked and unlocked according to test requirements; the pitching encoder 30 is fixedly connected with the outer side end face of the left blanking cover 32 through a pitching encoder mounting seat 31, an inner ring of the pitching encoder 30 is sleeved on the other end of the pitching shaft 34, and the pitching encoder 30 feeds back the pitching angle of the aircraft model in real time.
As shown in fig. 4, the upper section of the yaw shaft 41 is mounted in the inner hole of the yaw shaft seat 18 through a pair of low damping yaw bearings 19 coaxially arranged, the lower plane of the boss structure is in contact with the upper end face of the yaw shaft seat 18, a bearing pad sleeve 21 and a small round nut group 22 are sleeved between the upper section and the middle section of the yaw shaft 41, the bearing pad sleeve 21 is padded between the lower plane of the low damping yaw bearing 19 at the lower end and the small round nut group 22, and the yaw shaft 41 and the yaw shaft seat 18 are axially locked through the boss structure and the small round nut group 22, so that the free yaw motion of the aircraft model is realized; the transition support rod 20 is sleeved outside the yaw shaft seat 18 and fixedly connected with the yaw shaft seat, and the tail end of the transition support rod 20 is fixedly connected with the support rod 29 through a flange; the yaw brake 24 is positioned at the tail end of the inner hole of the transition strut 20, the outer ring of the yaw brake 24 is fixedly connected with the stepped inner wall of the tail end of the inner hole of the transition strut 20, the brake hole in the yaw brake 24 is sleeved at the lower section of the yaw shaft 41, and the yaw brake 24 brakes and unlocks the yaw angle of the aircraft model; the yaw encoder 23 is located in the inner hole of the transition strut 20, the inner ring of the yaw encoder 23 is sleeved on the lower section of the yaw shaft 41, the outer ring of the yaw encoder 23 is fixedly connected with the inner wall of the transition strut 20, and the yaw encoder 23 feeds back the yaw angle of the aircraft model in real time.
As shown in fig. 3-4, the air inlet hose 28 provides stable high-pressure air flow input for the flight test device, an air cavity is formed in the air cavity from top to bottom, an opening at one end of the air cavity is located at the center of the right inner hole end face of the pitching shaft seat 12, an opening at the other end of the air cavity is located at the center of the tail end face of the yawing shaft 41, one end of the air inlet rotary joint 25 is connected with the air inlet hose 28 through the air inlet rotary joint flange 27, the other end of the air inlet rotary joint 25 is connected with the tail end face of the yawing shaft 41, high-pressure air flow is introduced into the yawing shaft 41 from outside, one end of the L-shaped air inlet rotary joint 36 is connected with the right inner hole end face of the pitching shaft seat 12, the other end of the L-shaped air inlet rotary joint 36 is connected with one end of the hard air pipe 10, high-pressure air flow is introduced into the pitching shaft 34 from the direction of the yawing shaft 41, the other end of the hard air pipe 10 is connected with the air outlet hose 1 through the air outlet rotary joint 2, and high-pressure air flow is introduced into the aircraft model from the pitching shaft 34 direction.
As shown in fig. 3-4, the embodiment further includes an air outlet rotary joint stop ring 8 and an L-shaped ventilation rotary joint brake sleeve 38, the air outlet rotary joint stop ring 8 is fixedly connected with the outer end face of the front end rotary ring 71 of the rolling shaft seat 7, the inner end face of the air outlet rotary joint stop ring 8 is clamped with the air outlet rotary joint 2, the L-shaped ventilation rotary joint brake sleeve 38 is fixedly connected with the outer end face of the right blanking cover 37, and the L-shaped ventilation rotary joint brake sleeve 38 is clamped with the L-shaped ventilation rotary joint 36, so that the ventilation hard tube 10 is prevented from being damaged by torsion in the free rotation process of the aircraft model.
As shown in fig. 3, pitch hard limits 11 are installed on the front and rear sides of the upper plane of the boss structure, for limiting the pitch angle of the aircraft model.
As shown in fig. 3, the bottom of the front end rotating ring 71 and the rear end rotating ring 72 of the rolling shaft seat 7 are respectively provided with a rolling hard limit 9 for limiting the rolling angle of the aircraft model.
As shown in fig. 4, the embodiment further includes an air intake rotary joint stop sleeve 26, where the air intake rotary joint stop sleeve 26 is located in the inner hole of the supporting rod 29, the outer ring of the air intake rotary joint stop sleeve is fixedly connected with the inner wall of the supporting rod 29, and the inner ring of the air intake rotary joint stop sleeve is fixedly connected with the air intake rotary joint 25, so as to limit the air intake rotary joint 25 to rotate along with the yaw shaft 41.
As shown in fig. 1-4, the rolling axis of the model mount 5, the pitch axis and the yaw axis of the ventilation shaft intersect at a point which coincides with the centroid of the aircraft model, thereby avoiding the additional moment interference to the aircraft model caused by the flight test device itself during the test.
The flight test device can effectively inhibit the interference of aerodynamic characteristics caused by the damage of the flight test device to the aerodynamic structure of the aircraft model, and provides more real and stable data for the development of the aircraft, so that the virtual flight test model has the capability of verifying advanced control measures such as thrust vectors, jet control and the like.
Claims (6)
1. The utility model provides a virtual flight test device of three degrees of freedom that can ventilate, including flexible pipe (1) of giving vent to anger, rotary joint (2) of giving vent to anger, connect fixing base (3), model mount pad (5), spin axle seat (7), hard tube of ventilating (10), the axle of ventilating, spin encoder (13), spin brake (15), spin angle axle (16), yaw axle seat (18), yaw encoder (23), yaw brake (24), rotary joint (25) admits air, flexible pipe (28) admits air, transition branch (20), branch (29), pitch encoder (30), pitch brake (33), pitch axle (34) and L rotary joint (36) of ventilating, its characterized in that: the air outlet hose (1) is arranged at the inner side of the aircraft model and is fixed relative to the aircraft model in position, the air outlet rotary joint (2) is fixed in an inner hole at the outer side of the front blanking cover (4) through the joint fixing seat (3), and the front blanking cover (4) is fixedly connected with the outer end face of the front inner hole (51) of the model mounting seat (5); the inner ring of the front low-damping rolling bearing (6) is sleeved on the shaft neck of the front blanking cover (4), and the front end rotating ring (71) of the rolling shaft seat (7) is arranged on the outer ring of the front low-damping rolling bearing (6); the inner ring of the rear low-damping rolling bearing (39) is sleeved on the shaft neck of the rear blanking cover (17), a rear end rotating ring (72) of the rolling shaft seat (7) is arranged on the outer ring of the rear low-damping rolling bearing (39), the front end of the rolling angle shaft (16) penetrates through a central hole of the rear blanking cover (17), the rear end of the rolling angle shaft (16) is fixedly connected with the outer side end face of the rear blanking cover (17), the rear blanking cover (17) is fixedly connected with the outer side end face of a rear inner hole (52) of the model mounting seat (5), the rolling axis of the rolling shaft seat (7) coincides with the rolling axis of the model mounting seat (5), and the aircraft model is arranged on the model mounting seat (5), so that free rolling movement of the aircraft model is realized; the inner braking hole of the rolling brake (15) is sleeved on the rolling angle shaft (16), the rolling brake (15) is fixedly connected with the end face of the rear end rotating ring (72) of the rolling shaft seat (7), the rolling encoder (13) is fixed at the rear end of the rolling shaft seat (7) through the rolling encoder mounting seat (14), the inner ring of the rolling encoder (13) is sleeved on the other end of the rolling angle shaft (16), the rolling encoder (13) feeds back the rolling angle of the aircraft model in real time, and the rolling brake (15) can brake and unlock the rolling angle of the aircraft model;
the ventilation shaft comprises a pitching shaft seat (12) and a yawing shaft (41) which are of an integral structure, the pitching shaft seat (12) is positioned at the upper end of the yawing shaft (41), a boss structure is arranged at the transition part of the pitching shaft seat (12) and the yawing shaft (41), and the central shaft of the pitching shaft seat (12) and the central shaft of the yawing shaft (41) are mutually perpendicular and intersected; the left inner hole side wall of the pitching shaft seat (12) is fixedly connected with the outer ring of the left low damping pitching bearing (35), the right inner hole side wall of the pitching shaft seat (12) is fixedly connected with the outer ring of the right low damping pitching bearing (40), the left blanking cover (32) and the right blanking cover (37) are provided with central holes, the left blanking cover (32) is fixedly connected with the inner ring of the left low damping pitching bearing (35), the right blanking cover (37) is fixedly connected with the inner ring of the right low damping pitching bearing (40), the left rotating ring (73) of the rolling shaft seat (7) is sleeved on the left blanking cover (32) and fixedly connected with the left blanking cover, and the right rotating ring (74) of the rolling shaft seat (7) is sleeved on the right blanking cover (37) and fixedly connected with the right blanking cover; one end of the pitching shaft (34) penetrates through a central hole of the left blanking cover (32) and is fixedly connected with the center of the left end face of the pitching shaft seat (12), and the pitching axis of the pitching shaft seat (12), the pitching axis of the rolling shaft seat (7) and the pitching axis of the model mounting seat (5) are overlapped, so that free pitching movement of the aircraft model is realized; the side surface of the pitching brake (33) is fixedly connected with an inner hole boss of the left blanking cover (32), and a braking hole of the pitching brake (33) is sleeved on the pitching shaft (34) so as to brake and unlock the pitching angle of the aircraft model according to test requirements; the pitching encoder (30) is fixedly connected with the outer side end face of the left blanking cover (32) through a pitching encoder mounting seat (31), an inner ring of the pitching encoder (30) is sleeved on the other end of the pitching shaft (34), and the pitching encoder (30) feeds back the pitching angle of the aircraft model in real time;
the upper section of the yaw shaft (41) is arranged in an inner hole of the yaw shaft seat (18) through a pair of low-damping yaw bearings (19), the lower plane of the boss structure is in contact with the upper end face of the yaw shaft seat (18), a locking unit is sleeved between the upper section and the middle section of the yaw shaft (41), and the yaw shaft (41) and the yaw shaft seat (18) are axially locked through the locking unit and the boss structure, so that free yaw movement of an aircraft model is realized; the transition support rod (20) is sleeved outside the yaw shaft seat (18) and fixedly connected with the yaw shaft seat, and the tail end of the transition support rod (20) is fixedly connected with the support rod (29) through a flange; the yaw brake (24) is positioned at the tail end of the inner hole of the transition strut (20), the outer ring of the yaw brake (24) is fixedly connected with the stepped inner wall of the tail end of the inner hole of the transition strut (20), the brake hole in the yaw brake (24) is sleeved at the lower section of the yaw shaft (41), and the yaw brake (24) brakes and unlocks the yaw angle of the aircraft model; the yaw encoder (23) is positioned in an inner hole of the transition strut (20), an inner ring of the yaw encoder (23) is sleeved at the lower section of the yaw shaft (41), an outer ring of the yaw encoder (23) is fixedly connected with the inner wall of the transition strut (20), and the yaw encoder (23) feeds back the yaw angle of the aircraft model in real time;
the utility model is characterized in that the air inlet hose (28) provides stable high-pressure air flow input for the flight test device, the inside of the ventilation shaft is provided with a ventilation inner cavity from top to bottom, one end opening of the ventilation inner cavity is positioned at the center of the right inner hole end face of the ventilation hard tube (12), the other end opening of the ventilation inner cavity is positioned at the center of the tail end face of the yaw shaft (41), one end of the air inlet rotary joint (25) is connected with the air inlet hose (28) through the air inlet rotary joint flange (27), the other end of the air inlet rotary joint (25) is connected with the tail end face of the yaw shaft (41), high-pressure air flow is introduced into the direction of the yaw shaft (41) from outside, one end of the L-shaped ventilation rotary joint (36) is connected with the right inner hole end face of the pitch shaft seat (12), the other end of the L-shaped ventilation rotary joint (36) is connected with one end of the ventilation hard tube (10) to introduce high-pressure air flow into the direction of the pitch shaft (34) from the direction of the yaw shaft (41), the other end of the hard tube (10) is connected with the tail end face of the yaw shaft (41) through the air outlet rotary joint (2), and the air outlet rotary joint (1) to introduce high-pressure air flow into the direction of the air flow from inside of the inside model.
2. The breathable three-degree-of-freedom virtual flight test apparatus of claim 1, wherein: the wind turbine yaw shaft comprises a yaw shaft (41), and is characterized by further comprising a wind turbine rotor stop sleeve (26), wherein the wind turbine rotor stop sleeve (26) is positioned in an inner hole of the supporting rod (29), an outer ring of the wind turbine rotor stop sleeve is fixedly connected with the inner wall of the supporting rod (29), an inner ring of the wind turbine rotor stop sleeve is fixedly connected with the wind turbine rotor (25), and the wind turbine rotor (25) is limited to rotate along with the yaw shaft (41).
3. The breathable three-degree-of-freedom virtual flight test apparatus of claim 2, wherein: still including rotary joint stop collar (8) and L type rotary joint brake sleeve (38) that ventilates of giving vent to anger, rotary joint stop collar (8) with the outside terminal surface fixed connection of front end rotation circle (71) of spin base (7) give vent to anger, the interior terminal surface of rotary joint stop collar (8) block rotary joint (2) of giving vent to anger, L type rotary joint brake sleeve (38) and the outside terminal surface fixed connection of right blanking cover (37) that ventilate, L type rotary joint brake sleeve (38) block L type rotary joint (36) of ventilating.
4. A ventilated three degree of freedom virtual flying test device according to claim 3, wherein: pitching hard limit (11) is arranged on the front side and the rear side of the upper plane of the boss structure, and the pitching angle of the aircraft model is limited.
5. A ventilated three degree of freedom virtual flying test device according to claim 3, wherein: the bottoms of the front end rotating ring (71) and the rear end rotating ring (72) of the rolling shaft seat (7) are respectively provided with a rolling hard limit (9) for limiting the rolling angle of the aircraft model.
6. A ventilated three degree of freedom virtual flying test device according to any one of claims 1-5, wherein: the rolling axis, the pitching axis and the yawing axis of the ventilation shaft of the model mounting seat (5) intersect at a point which coincides with the mass center of the aircraft model.
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