CN109060291B - Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft - Google Patents
Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft Download PDFInfo
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- CN109060291B CN109060291B CN201810932958.2A CN201810932958A CN109060291B CN 109060291 B CN109060291 B CN 109060291B CN 201810932958 A CN201810932958 A CN 201810932958A CN 109060291 B CN109060291 B CN 109060291B
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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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
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Abstract
A device for measuring and testing the angle of a low-frequency vibration dynamic derivative test in the pitching direction of a short and blunt profile aircraft comprises a model connecting cone (51), a bearing shaft (52), a bearing shaft pin (53), a strain beam (54), a strut connecting shaft (56), a bearing end cover (57), a bearing nut (58) and a bearing (510); the front end conical surface of the model connecting cone (51) is connected with a short and blunt appearance test model; the rear end of the model connecting cone (51) is supported on the bearing shaft (52) through a bearing shaft pin (53); two ends of the strain beam (54) are respectively arranged on the model connecting cone (51) and the support rod connecting shaft (56); the inner ring of the bearing (510) is arranged on the bearing shaft (52) and is fixed in the axial direction by a bearing nut (58); the outer ring of the bearing (510) is arranged on the support rod connecting shaft (56), and the axial direction of the bearing is fixed by a bearing end cover (57); the strain beam (54) is adhered with a strain sheet, and when the model connecting cone (51) moves relative to the support rod connecting shaft (56), the angle time history is measured through the strain beam (54).
Description
Technical Field
The invention relates to a test device for acquiring a dynamic derivative of an aircraft in a low-frequency state by a free vibration dynamic derivative test method aiming at a short and blunt profile aircraft, wherein the low-frequency vibration frequency is 1Hz-3 Hz.
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. A certain similarity criterion is required to be met during a dynamic derivative wind tunnel test, wherein one main similarity parameter is reduction frequency, namely the motion frequency of a test model after scaling is simulated through the wind tunnel test according to the motion frequency of an actual aircraft. Because the factors such as supporting rigidity, strength and the like are considered at the same time, the simulation of the low-frequency vibration of the wind tunnel test of the dynamic derivative of the short and blunt profile aircraft is always a technical difficulty.
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. The forced vibration test method can realize the dynamic derivative test of lower frequency by adjusting the frequency of the driving source, but the forced vibration test method needs to simultaneously measure the aerodynamic force and the angular displacement of the model, needs the internal space of the model in the front and back directions to be larger, and is difficult to realize by adopting the forced vibration test method aiming at the aircraft with the shape of the blunt body. 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 low-frequency free vibration dynamic derivative test of the aircraft needs to be further researched. Therefore, in order to obtain the low-frequency state dynamic derivative of the short and blunt profile aircraft, a set of low-frequency free vibration dynamic derivative test device is designed for researching the dynamic stability characteristics 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 measuring and testing the angle of the low-frequency vibration dynamic derivative in the pitching direction of the short and blunt profile aircraft.
The technical solution of the invention is as follows: a test angle measuring device for a pitch direction low-frequency vibration dynamic derivative of a short blunt profile aircraft comprises: the model connecting cone, the bearing shaft pin, the strain beam, the support rod connecting shaft, the bearing end cover, the bearing nut and the bearing;
the front end conical surface of the model connecting cone is connected with a short and blunt appearance test model; the rear end of the model connecting cone is supported on the bearing shaft through a bearing shaft pin; two ends of the strain beam are respectively arranged on the model connecting cone and the strut connecting shaft; the bearing inner ring is arranged on the bearing shaft and is fixed in the axial direction by a bearing nut; the bearing outer ring is arranged on the support rod connecting shaft, and the axial direction of the bearing outer ring is fixed by the bearing end cover; and the strain beam is adhered with a strain sheet, and when the model connecting cone moves relative to the support rod connecting shaft, the angle time history is measured through the strain beam.
Furthermore, two strain beams are adopted and are symmetrically distributed relative to the central axis of the test device.
Furthermore, the strain beam 4 is a V-shaped beam, and the included angle of the V-shaped beam is 90 +/-8 degrees.
Furthermore, the thickness of the edge beam is 0.1mm-0.25 mm.
Furthermore, the main body of the supporting connecting shaft is a cylinder, a moving groove is formed in the front end of the cylinder, the rear end of the model connecting cone moves in the moving groove, and cylindrical holes are formed in two end faces of the moving groove and used for mounting a bearing; the rear end of the cylinder is provided with a stepped hole.
Furthermore, the clearance between the two sides of the rear end of the model connecting cone and the motion groove is larger than 1 mm.
A low-frequency vibration dynamic derivative test device for a pitching direction of a short and blunt profile aircraft comprises the angle measuring device, a motion transmission device, a supporting device and a driving device;
the driving device is arranged in the inner cavity of the supporting device, and the output end of the driving device is connected with the motion transmission device to drive the motion transmission device to move back and forth; one end of the strut connecting shaft is fixedly connected with the supporting device; the movement of the angle measuring device is limited by the movement transmission device before and after the test; in the test process, the short and blunt appearance model is driven to do low-frequency motion around the rotation center of the angle measuring device through the back-and-forth motion of the motion transmission device.
Furthermore, the motion transmission device comprises a push rod, an upper shifting needle, a lower shifting needle and a limiting block;
the push rod is arranged in the inner cavity of the supporting device and is connected with the output end of the driving device, and 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; before and after the test, the push rod penetrates through a stepped small hole of the connecting shaft of the support rod to be matched with a hole arranged at the rear end of the connecting cone of the model, so that the movement of the angle measuring device is limited; 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 low-frequency movement around the center of the bearing shaft.
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.
Further, the output speed of the driving device is not less than 2 m/s.
Furthermore, the driving device adopts an air cylinder capable of bearing air source pressure not lower than 5Mpa, the thickness of the cylinder body of the air 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 air 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 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 existing pitching hinge front cone for free vibration dynamic derivative test, the designed small-size model connecting cone has smaller axial size and can be better matched with a short and blunt profile aircraft model.
(2) The low-frequency vibration of the testing device can be realized by installing the two thin moment beams in the vertical symmetry mode, and meanwhile, the measurement error can be reduced by collecting signals of the two moment beams, so that the measurement precision is improved.
(3) The model connecting cone is installed on the supporting rod connecting shaft through the pair of bearings 619/8, can bear large axial load during testing, and has small pitching direction rigidity and good aerodynamic performance matched with the short and blunt profile aircraft.
Drawings
FIG. 1 is an assembly schematic according to an embodiment of the invention;
FIG. 2 is a schematic view of a mold connecting cone according to an embodiment of the present invention;
FIG. 3 is a schematic view of a bearing shaft according to an embodiment of the present invention;
FIG. 4 is a schematic view of a strain beam according to an embodiment of the present invention;
FIG. 5 is a schematic view of a bearing end cap according to an embodiment of the invention;
FIG. 6 is a schematic view of a strut connecting shaft according to an embodiment of the present invention;
FIG. 7 is a general assembly view of an embodiment according to the present invention;
FIG. 8 is a schematic view of a strut according to an embodiment of the present invention;
FIG. 9 is a schematic view of a stopper according to an embodiment of the present invention;
FIG. 10 is a schematic view of a high pressure cylinder according to an embodiment of the present invention;
FIG. 11 is a schematic illustration of a putter according to an embodiment of the present invention;
FIG. 12 is a schematic view of a lower dial needle according to an embodiment of the present invention;
FIG. 13 is a schematic view of an up-dial needle according to an embodiment of the present invention;
fig. 14 is a diagram of a low frequency pitch angular displacement signal collected in accordance with 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. 1-6, the device for testing the low-frequency vibration dynamic derivative in the pitching direction of the short blunt profile aircraft comprises: the device comprises a model connecting cone 51, a bearing shaft 52, a bearing shaft pin 53, a strain beam 54, a strain beam screw 55, a support rod connecting shaft 56, a bearing end cover 57, a bearing nut 58, a bearing end cover screw 59 and a bearing 619/8510;
the front end conical surface of the model connecting cone 51 is connected with a short and blunt appearance test model; the rear end of the model connecting cone 51 is supported on the bearing shaft 52 through a bearing shaft pin 53; the front section of the strain beam 54 is arranged on the model connecting cone 51 through a strain beam screw 55, and the rear end is arranged on the support rod connecting shaft 56 through the strain beam screw 55; the bearing nut 58 is arranged on the support rod connecting shaft 56 through a bearing end cover screw 59 and is used for fixing the outer ring of the bearing 619/8510; the middle part of the bearing shaft 52 is matched with the model connecting cone 51, and the inner ring of the bearing 619/8510 and the bearing nut 58 are arranged on two sides. The bearing 510 outer ring is arranged on the support rod connecting shaft 56, and the axial direction of the bearing is fixed by the bearing end cover 57; the rear end of the support rod connecting shaft 56 is arranged on the support rod in a taper pin and screw mode, the inner hole at the front end supports and is provided with the outer ring of the bearing 619/8510, and the model connecting cone 51 can freely rotate relative to the support rod connecting shaft 56; the strain beam 54 is attached with a strain gauge, and when the model connecting cone 51 moves relative to the strut connecting shaft 56, the angular time history is measured through the strain beam 54. When the model connecting cone moves relative to the supporting rod connecting shaft, the time history of relative movement angular displacement can be measured through the strain gauge adhered to the strain beam, the voltage signal value of an angular displacement signal is acquired through the data acquisition system, and then corresponding data processing is carried out, so that a corresponding low-frequency pitching stable derivative can be obtained.
As shown in fig. 7-13, a device for testing the low-frequency vibration dynamic derivative in the pitching direction of a short and blunt profile aircraft comprises the angle measuring device 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 and blunt appearance model 1, a tensioning cushion block 2, a tensioning screw 3, a connecting taper sleeve 4, an angle measuring device 5, a push rod 6, a connecting taper pin 7, a 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, a cylinder 15, a high-pressure cylinder set screw 16, a fairing 17, a connecting wedge 18, a positioning key 19 and a middle shaft 20;
the cylinder 15 adopts a high-pressure cylinder capable of bearing the air source pressure of not less than 5Mpa, is used as a driving device of the device and is placed 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 driving device is arranged in the inner cavity of the supporting device, and the output end of the driving device is connected with the motion transmission device to drive the motion transmission device to move back and forth; one end of the strut connecting shaft 56 is fixedly connected with the supporting device; the movement of the angle measuring device is limited by the movement transmission device before and after the test; in the test process, the short and blunt appearance model 1 is driven to do low-frequency motion around the rotation center of the angle measuring device by the back-and-forth motion of the motion transmission device.
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.
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 angle measuring device is arranged at the front end of the supporting rod 12, the short and blunt appearance model 1 is arranged at the front end of the angle measuring device 5 through the connecting taper sleeve 4, the contact mode is conical surface fit, and the short and blunt appearance model 1 and the angle measuring device 5 are axially and tightly connected through the tensioning cushion block 2 and the four 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; before and after the test, the push rod 6 penetrates through a stepped small hole of the support rod connecting shaft 56 to be matched with a hole arranged at the rear end of the model connecting cone 51, so that the movement of the angle measuring device is limited; in the test process, the lower shifting needle 11 drives the upper shifting 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 low-frequency movement around the center of the bearing shaft 52. 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.
Examples
When the device for testing the low-frequency vibration dynamic derivative in the pitching direction of the short and blunt profile aircraft is used for testing, the rear-end strut connecting shaft 56 of the device is installed on the strut, the front-end model connecting cone 51 is connected with a test model, the model connecting cone 51 is connected with the strut connecting shaft 56 through the strain beam 54, the model connecting cone 51 can freely vibrate relative to the strut connecting shaft 56 under the rigid support of the strain beam 54, the pair of bearings 619/8510 can bear the axial load borne by the model, the model can drive the model connecting cone 51 to freely attenuate around the strut connecting shaft 56 by applying an initial angular displacement to the model, the time history of the angular displacement can be measured through the strain gauge adhered to the strain beam 54, and the low-frequency pitching stable derivative can be obtained through corresponding data processing.
Whole testing arrangement length is 85mm, and the diameter is 40mm, and during the experiment, whole testing arrangement is placed at the experimental model inner chamber of short blunt appearance aircraft. The test device can realize the pitching vibration angle of +/-10 degrees to the maximum extent, and can realize the vibration frequency of 1 Hz-8 Hz by changing the beam thickness of the strain beam. As shown in fig. 14, the initial angular displacement is 3.8 ° and the vibration frequency is 1.8Hz, which are the time histories 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 (9)
1. The utility model provides a be used for experimental angle measuring device of short blunt appearance aircraft pitch direction low frequency vibration dynamic derivative which characterized in that includes: the device comprises a model connecting cone (51), a bearing shaft (52), a bearing shaft pin (53), a strain beam (54), a support rod connecting shaft (56), a bearing end cover (57), a bearing nut (58) and a bearing (510);
the front end conical surface of the model connecting cone (51) is connected with a short and blunt appearance test model; the rear end of the model connecting cone (51) is supported on the bearing shaft (52) through a bearing shaft pin (53); two ends of the strain beam (54) are respectively arranged on the model connecting cone (51) and the support rod connecting shaft (56); the inner ring of the bearing (510) is arranged on the bearing shaft (52) and is fixed in the axial direction by a bearing nut (58); the outer ring of the bearing (510) is arranged on the support rod connecting shaft (56), and the axial direction of the bearing is fixed by a bearing end cover (57); the strain beam (54) is adhered with a strain gauge, and when the model connecting cone (51) moves relative to the support rod connecting shaft (56), the strain beam (54) is used for measuring the angle time history; two strain beams are adopted and are symmetrically distributed relative to the central axis of the angle measuring device; the strain beam (54) is a V-shaped beam, and the included angle of the V shape is 90 +/-8 degrees; the thickness of the strain beam is 0.1mm-0.25 mm.
2. The angle measuring apparatus according to claim 1, wherein: the main body of the connecting shaft of the support rod is a cylinder, the front end of the cylinder is provided with a moving groove, the rear end of the model connecting cone (51) moves in the moving groove, and two end faces of the moving groove are provided with cylindrical holes for mounting a bearing; the rear end of the cylinder is provided with a stepped hole.
3. The angle measuring apparatus according to claim 1, wherein: the clearance between the two sides of the rear end of the model connecting cone (51) and the moving groove is more than 1 mm.
4. The utility model provides a be used for short blunt appearance aircraft pitch direction low frequency vibration dynamic derivative test device which characterized in that: comprising the angle measuring device, the motion transmission device, the support device, the drive device of claim 1;
the driving device is arranged in the inner cavity of the supporting device, and the output end of the driving device is connected with the motion transmission device to drive the motion transmission device to move back and forth; one end of the strut connecting shaft (56) is fixedly connected with the supporting device; the movement of the angle measuring device is limited by the movement transmission device before and after the test; in the test process, the short and blunt appearance test model is driven to do low-frequency motion around the rotation center of the angle measuring device through the back-and-forth motion of the motion transmission device.
5. The testing device of claim 4, wherein: 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 push rod (6) is arranged in the inner cavity of the supporting device and is connected with the output end of the driving device, and 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; before and after the test, the push rod (6) penetrates through a stepped small hole of the support rod connecting shaft (56) to be matched with a hole arranged at the rear end of the model connecting cone (51) so as to limit the movement of the angle measuring device; 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 test model is driven to do low-frequency movement around the center of the bearing shaft (52).
6. The test device of claim 5, 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).
7. The testing device of claim 4, wherein: the output speed of the driving device is not less than 2 m/s.
8. The testing device of claim 7, wherein: the driving device adopts a cylinder capable of bearing air source pressure not lower than 5Mpa, the thickness of a cylinder body of the cylinder is not less than 10mm, and the length of a sealing contact surface between a 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.
9. The testing device of claim 4, 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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| CN201810932958.2A CN109060291B (en) | 2018-08-16 | 2018-08-16 | Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft |
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| CN201810932958.2A CN109060291B (en) | 2018-08-16 | 2018-08-16 | Device for measuring and testing angle of low-frequency vibration dynamic derivative in pitching direction of short and blunt profile aircraft |
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| CN109060291A CN109060291A (en) | 2018-12-21 |
| CN109060291B true CN109060291B (en) | 2021-02-09 |
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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 |
| CN111289208B (en) * | 2020-03-06 | 2021-01-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Model tail boom device suitable for fighter plane wind tunnel test |
| CN116046330B (en) * | 2023-03-30 | 2023-06-16 | 中国航空工业集团公司哈尔滨空气动力研究所 | Three-degree-of-freedom virtual flight test device capable of ventilating |
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| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 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 |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 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 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 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 |
| CN102818692A (en) * | 2012-08-17 | 2012-12-12 | 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 |
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