CN109238622B - Device for testing free vibration dynamic derivative of short and blunt profile aircraft in pitching direction - Google Patents
Device for testing free vibration dynamic derivative of short and blunt profile aircraft in pitching direction Download PDFInfo
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- CN109238622B CN109238622B CN201810932942.1A CN201810932942A CN109238622B CN 109238622 B CN109238622 B CN 109238622B CN 201810932942 A CN201810932942 A CN 201810932942A CN 109238622 B CN109238622 B CN 109238622B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- 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
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Abstract
A device for testing the pitch direction free vibration dynamic derivative of a short blunt profile aircraft comprises: a pitching hinge (5), a motion transmission device, a supporting device and a driving device; the motion transmission device comprises a push rod (6), an upper poking needle (9), a lower poking needle (11) and a limiting block (13); the driving device is placed in the inner cavity of the supporting device, and the output end of the driving device is connected with one end of a push rod (6) placed in the inner cavity of the supporting device to drive the push rod (6) to move back and forth; one end of the pitching hinge (5) is fixedly connected with the supporting device, and the other end of the pitching hinge is connected with the short and blunt appearance test model; the limiting block (13) is arranged on the supporting device and limits the push rod (6) to only move back and forth; the lower shifting needle (11) is arranged on the push rod (6), and the upper shifting needle (9) is arranged on the short and blunt appearance test model; the movement of the pitching hinge is limited by the push rod (6) before and after the test; in the test process, the lower poking needle (11) drives the upper poking needle (9) to move upwards through the back-and-forth movement of the push rod, and then the short and blunt appearance model (1) is driven to do free vibration movement around the rotation center of the pitching hinge (5).
Description
Technical Field
The invention relates to a wind tunnel test device for acquiring a pitching direction dynamic derivative by adopting a free vibration dynamic derivative test method aiming at a short and blunt profile aircraft.
Background
Both the aerodynamic design of an aircraft and the design of a control system require the provision of derivative data for the dynamic stability of the aircraft under its flight conditions. When the aircraft performs attitude change actions or is disturbed by air flow, pitching, yawing or rolling vibration deviating from the balanced attitude can occur. The purpose of the dynamic stability study is to predict the damping trends and laws of these vibrations. For the aircraft with passive damping control, the dynamic flight quality and reliability requirements of the aircraft place extremely high requirements on the prediction of the dynamic stability of the aircraft. Too low dynamic stability tends to cause divergence of the angular movements of the aircraft, which, in this way, will seriously affect the attitude of the aircraft. Therefore, accurate prediction of the dynamic derivative is important.
The dynamic derivative, also known as the dynamic stability derivative, is used to describe the aerodynamic characteristics of the aircraft in a maneuver and in a disturbance. Are the essential aerodynamic parameters in the design of the aerodynamic performance of the aircraft, the control system and the overall design. The derivatives of dynamic stability are important to aircraft designers because they provide the natural stability, control surface efficiency and maneuverability of the aircraft, and they also make the geometry of the aircraft of particular importance in the initial design process.
The large blunt point of the blunted profile aircraft can meet the requirements of lift force and resistance required at various flight speeds during loading flight, so that the blunted profile aircraft can land safely and stably. One of the major jobs in aerodynamic design of short and blunt profile aircraft is the study of dynamic stability characteristics. Due to the appearance characteristic of the aircraft approaching to a spherical shape, the dynamic stability damping of the aircraft is very small in the subsonic and transonic stages, and the phenomenon of dynamic instability can also occur, so that the aircraft is confirmed to have good dynamic stability, the flight safety of the aircraft is ensured, and the final purpose of the research on the dynamic stability of the aircraft is achieved.
The dynamic stability characteristic of the short and blunt profile aircraft is researched, a main means is to obtain the dynamic stability derivative of the short and blunt profile aircraft, the current main methods comprise theoretical analysis, numerical calculation and wind tunnel test, and the wind tunnel test is the most intuitive method for obtaining the dynamic stability derivative of the short and blunt profile aircraft.
The conventional methods for wind tunnel dynamic stability derivative tests are a free vibration test method and a forced vibration test method, and the dynamic stability derivative is obtained by measuring aerodynamic force and moment acting on a model and measuring the motion parameters of the model. Because the forced vibration test method needs to measure the aerodynamic force and the angular displacement of the model at the same time, the internal space of the model in the front and back directions needs to be large, and the forced vibration test method is difficult to realize for the aircraft with the blunt body shape. The free vibration test method only needs to measure the angular displacement, can realize the measurement of the dynamic derivative of the short and blunt profile aircraft, and compared with the traditional free vibration test device, the free vibration dynamic derivative test of the aircraft needs to be further researched. Therefore, in order to obtain the dynamic stability derivative of the short and blunt profile aircraft, a set of free vibration dynamic derivative test device is designed for researching the dynamic stability characteristic of the short and blunt profile aircraft.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the device overcomes the defects of the prior art and provides the device for testing the free vibration dynamic derivative in the pitching direction of the short and blunt profile aircraft.
The technical solution of the invention is as follows: a device for testing the pitch direction free vibration dynamic derivative of a short blunt profile aircraft comprises: the device comprises a pitching hinge, a motion transmission device, a supporting device and a driving device; the motion transmission device comprises a push rod, an upper shifting needle, a lower shifting needle and a limiting block;
the driving device is arranged in the inner cavity of the supporting device, and the output end of the driving device is connected with one end of a push rod arranged in the inner cavity of the supporting device to drive the push rod to move back and forth; one end of the pitching hinge is fixedly connected with the supporting device, and the other end of the pitching hinge is connected with the short and blunt appearance test model; the limiting block is arranged on the supporting device and limits the push rod to only move back and forth; the lower shifting needle is arranged on the push rod, and the upper shifting needle is arranged on the short and blunt appearance test model; the movement of the pitching hinge is limited by the push rod before and after the test; in the test process, the lower poking needle drives the upper poking needle to move upwards through the back-and-forth movement of the push rod, and then the short and blunt appearance model is driven to do free vibration movement around the rotation center of the pitching hinge.
Furthermore, the driving device adopts an air cylinder capable of bearing air source pressure not lower than 5 Mpa.
Further, the thickness of the cylinder body of the cylinder is not less than 10mm, and the length of the sealing contact surface between the cylinder cover at the front end of the cylinder body and the cylinder body of the cylinder is not less than 40 mm; the screw thread matching length of the air inlet/outlet nozzle of the cylinder is not less than 20 mm.
Furthermore, the materials of other parts of the cylinder except the sealing gasket are made of steel.
Further, the output speed of the driving device is not less than 2 m/s.
Furthermore, the amplitude of the short and blunt shape test model is controlled by adjusting the distance difference between the vertexes of the upper dial needle and the lower dial needle.
Furthermore, the pitching hinge is of an integrated structure and comprises a model link cone, a support rod connecting surface, a cross beam and a moving beam; the model connecting cone is provided with a central inner hole, and the movement of the pitching hinge is limited by the matching of the inner hole and the push rod; the connecting surface of the supporting rod is provided with a stepped inner hole, wherein the supporting device is connected with the connecting surface of the supporting rod through a large hole, and the small hole is used for supporting the push rod; the pair of beams and the pair of moving beams positioned between the model link cone and the connecting surface of the supporting rod are uniform in thickness and symmetrically distributed, the pair of moving beams are arranged between the beams, and the gap between the adjacent moving beams is not less than 0.5 mm; the model connecting cone can move relative to the connecting surface of the supporting rod through the moving beam.
Further, the vibration frequency of the short and blunt appearance test model is changed by adjusting the thickness of the cross beam.
Furthermore, the thickness range of the beam is 0.6mm-2.5 mm.
Furthermore, the moving beam comprises a front part, a middle part and a rear part, and the middle part is a straight beam with the thickness consistent with that of the cross beam; the included angles of the front part and the rear part are consistent with the included angles of the middle part, the front part and the rear part are connected with the connection surface of the model connecting cone and the supporting rod, and the straight beam is perpendicular to the cross beam.
Further, the included angle ranges from 30 degrees to 60 degrees.
Furthermore, the supporting device comprises a supporting rod, a fairing and a middle shaft;
the hollow strut adopts a conical surface matching mode, is arranged on a central shaft through a front end connecting wedge and a positioning key, and the central shaft is connected with a wind tunnel attack angle mechanism; the fairing is arranged at the front end of the middle shaft.
Compared with the prior art, the invention has the advantages that:
(1) compared with the conventional free vibration dynamic derivative test pitch hinge, the designed small-size pitch hinge has smaller axial size and can be better matched with a short and blunt profile aircraft model.
(2) The upper poking needle and the lower poking needle are connected in a fine thread mode, and initial angular displacement obtained by the model can be adjusted simply and quickly.
(3) The limiting block limits the push rod to move in the rolling direction, so that the effective implementation of each driving can be ensured.
(4) The different roof beam thickness of every single move hinge can satisfy the demand of the different free vibration frequency of experimental model.
Drawings
FIG. 1 is an assembly schematic according to an embodiment of the invention;
FIG. 2 is a schematic view of a pitch hinge according to an embodiment of the present invention;
FIG. 3 is a schematic view of a strut according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a stopper according to an embodiment of the present invention;
FIG. 5 is a schematic view of a high pressure cylinder according to an embodiment of the present invention;
FIG. 6 is a schematic illustration of a putter according to an embodiment of the present invention;
FIG. 7 is a schematic view of a lower dial needle according to an embodiment of the present invention;
FIG. 8 is a schematic view of an up-dial needle according to an embodiment of the present invention;
fig. 9 is a collected pitch displacement signal according to an embodiment of the present invention.
Detailed Description
Embodiments of the present invention are described in detail below with reference to the accompanying drawings.
As shown in fig. 1-8, the device for testing the free vibration dynamic derivative in the pitching direction of the short and blunt profile aircraft comprises a pitching hinge 5, a motion transmission device, a supporting device and a driving device; the following components are specifically included in this example: the device comprises a short blunt appearance model 1, a pitch hinge tensioning cushion block 2, a pitch hinge tensioning screw 3, a pitch hinge connecting taper sleeve 4, a pitch hinge 5, a push rod 6, a pitch hinge connecting taper pin 7, a pitch hinge connecting screw 8, an upper shifting needle 9, an upper shifting needle set screw 10, a lower shifting needle 11, a support rod 12, a limiting block 13, a limiting block set screw 14, an air cylinder 15, a high-pressure air cylinder set screw 16, a fairing 17, a connecting wedge 18, a positioning key 19 and a middle shaft 20;
as shown in FIG. 5, the cylinder 15 is a high pressure cylinder capable of withstanding a source pressure of not less than 5MPa, and is used as a driving device of the present invention and is disposed in the inner cavity of the supporting device. The thickness of the cylinder body of the cylinder is not less than 10mm, and the length of the sealing contact surface between the cylinder cover at the front end of the cylinder body and the cylinder body of the cylinder is not less than 40 mm; the screw thread matching length of the air inlet/outlet nozzle of the cylinder is not less than 20 mm. The materials of other parts of the cylinder except the sealing gasket are made of steel. The output speed of the driving device is not less than 2 m/s.
The supporting device mainly comprises a supporting rod 12, a fairing 17 and a middle shaft 20; the hollow strut 12 is installed on a middle shaft 20 through a front end connecting wedge 18 and a positioning key 19 in a conical surface matching mode, and the middle shaft 20 is connected with a wind tunnel attack angle mechanism; the fairing 17 is mounted at the forward end of the central shaft 20 by means of a screw thread.
As shown in fig. 2, the pitch hinge 5 is an integrated structure, and includes a model link cone 51, a strut connecting surface 52, a cross beam 53, and a moving beam 54; the model connecting cone 51 is provided with a central inner hole, and the movement of the pitching hinge is limited by the matching of the inner hole and the push rod 6; the connecting surface 52 of the supporting rod is provided with a stepped inner hole, wherein the supporting device is connected with the connecting surface of the supporting rod through a big hole, and a small hole is used for supporting the push rod; a pair of beams 53 and a pair of moving beams 54 which are positioned between the model link cone 51 and the strut connecting surface 52 are consistent in thickness and are symmetrically distributed, the pair of moving beams are arranged between the beams, and the gap between the adjacent moving beams is not less than 0.5 mm; the model link cones 51 are movable relative to the strut connecting faces 52 by means of movement beams 54. The vibration frequency of the short and blunt appearance test model is changed by adjusting the thickness of the cross beam. The thickness of the beam ranges from 0.6mm to 2.5 mm.
The moving beam 54 includes three portions, front, middle and rear, the middle portion being a straight beam having a thickness corresponding to the thickness of the cross beam; the included angles between the front part and the rear part and the middle part are consistent, the front part and the rear part are connected with a model connecting cone 51 and a support rod connecting surface 52, and the straight beam is perpendicular to the cross beam. The included angle is in the range of 30-60 degrees.
The motion transmission device comprises a push rod 6, an upper poking needle 9, a lower poking needle 11 and a limiting block 13; the cylinder 15 is arranged in the inner cavity of the rear end of the supporting rod 12 through two high-pressure cylinder fixing screws 16, the output end of the cylinder is connected with one end of a push rod 6 arranged in the inner cavity of the supporting rod 12, and the push rod 6 is driven to move back and forth in the inner cavity of the supporting rod 12; the pitching hinge 5 is arranged at the front end of the supporting rod 12 in a 90-degree included angle mode through two pitching hinge connecting taper pins 7 and two pitching hinge connecting screws 8, the short and blunt appearance model 1 is arranged at the front end of the pitching hinge 5 through a pitching hinge connecting taper sleeve 4 in a conical surface matching mode, and the short and blunt appearance model 1 and the pitching hinge 5 are axially and tightly connected through the pitching hinge tensioning cushion block 2 and the four pitching hinge tensioning screws 3; the limiting block 13 is arranged on the support rod 12 through a limiting block fixing screw 14 and limits the push rod 6 to move back and forth; the lower shifting needle 11 is arranged at the front end of the push rod 6, the push rod 6 drives the lower shifting needle 11 to move back and forth, the upper shifting needle 9 is arranged at the rear end of the inner cavity of the short and blunt appearance model 1, and the upper shifting needle 9 is tightly fixed by an upper shifting needle set screw 10; the movement of the pitching hinge is limited by the push rod 6 before and after the test; in the test process, the lower poking needle 11 drives the upper poking needle 9 to move upwards through the back-and-forth movement of the push rod, so that the upper poking needle 9 and the short and blunt appearance model 1 obtain initial angular displacement, and the short and blunt appearance model 1 does free vibration movement around the center of the pitching hinge 5. The amplitude of the short and blunt shape test model is controlled by adjusting the distance difference between the vertexes of the upper dial needle 9 and the lower dial needle 11.
The test model is arranged on the supporting rod through the pitching hinge, the push rod is driven by the high-pressure cylinder to move back and forth, the upper poking needle on the test model can be given an initial force by the rapid back and forth movement of the lower poking needle on the push rod, so that the test model obtains an initial angular displacement, the test model can do free damping movement under the action of the pitching hinge, the angular displacement time history of the free damping movement of the model can be measured through the strain gauge attached to the pitching hinge, the voltage signal value of an angular displacement signal of the pitching hinge is acquired through the data acquisition system, and then corresponding pitching stable derivative can be obtained through corresponding data processing.
Examples
When the device for testing the free vibration dynamic derivative in the pitching direction of the short and blunt profile aircraft is used for testing, a central shaft 20 of the device is arranged on a wind tunnel bent knife, a high-pressure cylinder 15 is arranged in an inner cavity of a supporting rod 12, a push rod 6 is driven to move forwards and backwards quickly through the high-pressure cylinder 15, a lower poking needle 11 on the push rod 6 drives a lower poking needle 9 quickly to perform initial angular displacement on the lower poking needle 9 and the short and blunt profile model 1, the short and blunt profile model 1 performs free vibration motion around the center of a pitching hinge 5 under the elastic support of the pitching hinge 5, the time history of the angular displacement can be measured through a strain gauge attached to the pitching hinge 5, and the pitching stable derivative can be obtained through corresponding data processing.
The overall size of the whole set of test mechanism is about 1000mm, the diameter of the front end of the supporting rod 12 is 22mm, the diameter of the pitching hinge 5 is 32mm, the pitching vibration angle can be +/-5 degrees by the whole set of test mechanism, and the vibration frequency can be 8 Hz-20 Hz by changing the beam thickness of the pitching hinge 5. As shown in fig. 9, the initial angular displacement is 2.8 ° and the vibration frequency is 15Hz, which is the time history of the pitch angle collected during the test.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (7)
1. A device for testing the free vibration dynamic derivative of a short and blunt profile aircraft in the pitching direction is characterized by comprising: a pitching hinge (5), a motion transmission device, a supporting device and a driving device; the motion transmission device comprises a push rod (6), an upper poking needle (9), a lower poking needle (11) and a limiting block (13);
the driving device is placed in the inner cavity of the supporting device, and the output end of the driving device is connected with one end of a push rod (6) placed in the inner cavity of the supporting device to drive the push rod (6) to move back and forth; one end of the pitching hinge (5) is fixedly connected with the supporting device, and the other end of the pitching hinge is connected with the short and blunt appearance test model; the limiting block (13) is arranged on the supporting device and limits the push rod (6) to only move back and forth; the lower shifting needle (11) is arranged on the push rod (6), and the upper shifting needle (9) is arranged on the short and blunt appearance test model; the movement of the pitching hinge is limited by the push rod (6) before and after the test; in the test process, the lower poking needle (11) drives the upper poking needle (9) to move upwards through the back-and-forth movement of the push rod, so that the short and blunt appearance model (1) is driven to do free vibration movement around the rotation center of the pitching hinge (5);
the driving device adopts an air cylinder capable of bearing air source pressure not lower than 5 Mpa; the thickness of the cylinder body of the cylinder is not less than 10mm, and the length of the sealing contact surface between the cylinder cover at the front end of the cylinder body and the cylinder body of the cylinder is not less than 40 mm; the thread matching length of the air inlet/outlet nozzle of the cylinder is not less than 20 mm; the output speed of the driving device is not less than 2 m/s;
the pitching hinge (5) is of an integrated structure and comprises a model link cone (51), a support rod connecting surface (52), a cross beam (53) and a moving beam (54); the model connecting cone (51) is provided with a central inner hole, and the movement of the pitching hinge is limited by the matching of the inner hole and the push rod (6); a step inner hole is formed in the support rod connecting surface (52), wherein the supporting device is connected with the support rod connecting surface through a large hole, and the small hole is used for supporting the push rod; a pair of beams (53) and a pair of moving beams (54) which are positioned between the model linking cone (51) and the support rod connecting surface (52) are uniform in thickness and symmetrically distributed, the pair of moving beams are arranged between the beams, and the gap between the adjacent moving beams is not less than 0.5 mm; enabling the model connecting cone (51) to move relative to the strut connecting surface (52) through the moving beam (54); the thickness of the beam ranges from 0.6mm to 2.5 mm.
2. The test device of claim 1, wherein: the cylinder except the sealing gasket is made of steel.
3. The test device of claim 1, wherein: the amplitude of the short and blunt shape test model is controlled by adjusting the distance difference between the vertexes of the upper dial needle (9) and the lower dial needle (11).
4. The test device of claim 1, wherein: the vibration frequency of the short and blunt appearance test model is changed by adjusting the thickness of the cross beam.
5. The test device of claim 1, wherein: the moving beam (54) comprises a front part, a middle part and a rear part, and the middle part is a straight beam with the thickness consistent with that of the cross beam; the included angles of the front part and the rear part are consistent with the included angles of the middle part, the front part and the rear part are connected with a model connecting cone (51) and a support rod connecting surface (52), and the straight beam is perpendicular to the cross beam.
6. The test device of claim 5, wherein: the included angle ranges from 30 degrees to 60 degrees.
7. The test device of claim 1, wherein: the supporting device comprises a supporting rod (12), a fairing (17) and a middle shaft (20);
the hollow supporting rod (12) is installed on a middle shaft (20) through a front end connecting wedge (18) and a positioning key (19) in a conical surface matching mode, and the middle shaft (20) is connected with a wind tunnel attack angle mechanism; the fairing (17) is arranged at the front end of the middle shaft (20).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810932942.1A CN109238622B (en) | 2018-08-16 | 2018-08-16 | Device for testing free vibration dynamic derivative of short and blunt profile aircraft in pitching direction |
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| CN201810932942.1A CN109238622B (en) | 2018-08-16 | 2018-08-16 | Device for testing free vibration dynamic derivative of short and blunt profile aircraft in pitching direction |
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| CN109238622A CN109238622A (en) | 2019-01-18 |
| CN109238622B true CN109238622B (en) | 2020-07-14 |
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| CN110940484B (en) * | 2019-11-13 | 2021-11-16 | 中国航天空气动力技术研究院 | Rolling forced vibration dynamic derivative test device for high-speed flying wing model under large attack angle |
| CN110940483B (en) * | 2019-11-13 | 2021-12-07 | 中国航天空气动力技术研究院 | Pitching yawing free vibration dynamic derivative test device for large slenderness ratio aircraft |
| CN116818259B (en) * | 2023-08-23 | 2023-10-27 | 中国航空工业集团公司沈阳空气动力研究所 | Vibration damping device and method for dynamic derivative test mechanism |
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| US6721682B1 (en) * | 2002-01-07 | 2004-04-13 | The United States Of America As Represented By The Secretary Of The Navy | Aerodynamic prediction using semiempirical prediction techniques and methods therefor |
| JP4015004B2 (en) * | 2002-11-01 | 2007-11-28 | 川崎重工業株式会社 | Helicopter airfoil simulation method |
| CN101726401B (en) * | 2009-12-09 | 2011-10-26 | 中国航空工业第一集团公司沈阳空气动力研究所 | Scale measuring device for pitching dynamic derivative experiment |
| CN102818692B (en) * | 2012-08-17 | 2015-04-22 | 中国航天空气动力技术研究院 | Yaw-angle free vibration test device with short and blunt appearance like spacecraft |
| CN107966264B (en) * | 2017-11-09 | 2019-09-06 | 中国航天空气动力技术研究院 | One kind being used for hypersonic wind tunnel rolling forced vibration dynamic derivative experimental rig |
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