CN109100111B - Device is put in test of freely flying of perpendicular wind tunnel model - Google Patents
Device is put in test of freely flying of perpendicular wind tunnel model Download PDFInfo
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- CN109100111B CN109100111B CN201810734111.3A CN201810734111A CN109100111B CN 109100111 B CN109100111 B CN 109100111B CN 201810734111 A CN201810734111 A CN 201810734111A CN 109100111 B CN109100111 B CN 109100111B
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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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- 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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Abstract
A vertical wind tunnel model free flight test releasing device is characterized in that the top of a rotary support main shaft which can be vertically folded upwards is arranged on a support frame at the upper part of a wind tunnel, the lower part of the rotary support main shaft penetrates through the middle part of a support consisting of a front support arm and a rear support arm, the rotary support main shaft is of a hollow structure, a pulley is arranged on the support frame above the rotary support main shaft, and a hanging rope which penetrates through the pulley penetrates through the rotary support main shaft and is connected with an upper hanger for hanging an airplane model; the rotary driving motor drives the main shaft of the rotary support to rotate, the front support arm is connected with the front support cylinder, the rear support arm is connected with the rear support cylinder, the front support cylinder is connected with the front extension shaft, the rear support cylinder is connected with the rear extension shaft, a front contact is arranged in the front extension shaft, a rear contact is arranged in the rear extension shaft, a connecting point which is used for being connected with the front contact and the rear contact is arranged on the airplane model, the airplane model is automatically put in by adopting magnetic control, the accuracy of the test is effectively improved, and meanwhile, the test accident caused by the fact that the putting time is immature is reduced.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests, in particular to a vertical wind tunnel model free flight test putting device.
Background
The tail rotor is also called as a helix, and refers to the phenomenon that an airplane rotates along a steep spiral flight path with a small radius and the height of the airplane drops sharply in a continuous stalling state, is one of the most complex and dangerous flight states of the airplane, and is directly related to the safety of the airplane and pilots. The test is one of the most important means for researching the tail spin characteristic of the airplane, and can be used for researching the tail spin characteristic of the airplane in detail so as to obtain a method for modifying the tail spin of the airplane.
When the vertical wind tunnel model free flight test is carried out, the throwing hand is put into a test section from the edge of the wind tunnel under the condition that the airplane model does not reach the airflow speed in the suspension state (when the airflow speed is less than the corresponding value of the suspension state of the airplane model, the aerodynamic force borne by the airplane model cannot balance the gravity of the airplane model, the upper hanger bears the action of partial airplane model gravity, the upper hanger bears the action of the airplane model gravity gradually reduced along with the continuous increase of the airflow speed, the throwing hand feels the action force of the upper hanger to determine the throwing time of the airplane model), the airplane model is put into a test section by hand, the initial rotation speed is exerted on the airplane model by hand, when the airflow speed is gradually increased until the aerodynamic force borne by the airplane, the lower hanger sags freely, the movement of the airplane model is not restrained any more, and the schematic diagram of the test process is shown in figure 1.
Due to the large variation in the tail spin characteristics of different types of aircraft: the average incidence angle of the tail rotation is about 30 degrees and 90 degrees at the minimum, the rotation speed is about 30 degrees/s at the minimum and about 200 degrees/s at the maximum, so that the throwing hand is required to strictly master the throwing posture of the airplane model and the initial rotation speed during the test, and particularly the latter has direct influence on the test result. In addition, the throwing hand also needs to master the opportunity of throwing in the airplane model, and throwing in when the air flow speed is too low or too high can all influence the success or failure of the test, even cause the test accident, like upper and lower cable winding airplane model and then lead to the airplane model impaired.
Disclosure of Invention
The invention aims to provide a vertical wind tunnel model free flight test putting device to solve the defects in the background technology.
The technical problem solved by the invention is realized by adopting the following technical scheme:
a vertical wind tunnel model free flight test releasing device comprises a pulley, a rotary support main shaft, a rotary driving gear, a horizontal motion platform, a base, a support, a rear extension shaft, a front extension shaft and an airplane model for free flight test; the top of a rotary support main shaft which can be vertically folded upwards is arranged on a support frame at the upper part of the wind tunnel, the lower part of the rotary support main shaft penetrates through the middle part of a support frame consisting of a front support arm and a rear support arm, the rotary support main shaft is of a hollow structure, a pulley is arranged on the support frame above the rotary support main shaft, one end of a hanging rope which penetrates through the pulley is pulled by an operator, and the other end of the hanging rope penetrates through the rotary support main shaft and is connected with an upper hanger for hanging an airplane model; the base is arranged on the periphery of the upper part of the main shaft of the rotating bracket, the horizontal motion platform is arranged on the base, the rotating drive motor for rotationally driving the main shaft of the rotating bracket is arranged on the horizontal motion platform at one side of the main shaft of the rotating bracket, and the rotating drive gear is sleeved on the main shaft of the rotating bracket and is connected with the rotating drive motor; the front support arm is connected with the front support cylinder, the rear support arm is connected with the rear support cylinder, the front support cylinder is connected with the front extension shaft, the rear support cylinder is connected with the rear extension shaft, a front contact is arranged in the front extension shaft, a rear contact is arranged in the rear extension shaft, cable passages for electrifying the front contact and the rear contact are respectively arranged in the front support arm, the rear support arm, the front support cylinder and the rear support cylinder are used for adjusting and connecting the positions of the front contact and the rear contact of an airplane model, and the front extension shaft and the rear extension shaft are used for adjusting the posture of the airplane model; the front extension shaft and the rear extension shaft have the same structure, the front contact and the rear contact have the same structure, the front contact comprises a control circuit board, a force sensor, an electromagnet and a contact cover, the rear extension shaft has a hollow structure, the cable for electrifying passes through the cable passage to be connected with the electromagnet arranged in the contact cover, the contact cover is connected with the rear extension shaft, the force sensor is arranged at one side of the electromagnet, the control circuit board is respectively connected with the force sensor and the electromagnet, the airplane model is provided with a connecting point for connecting with the front contact and the rear contact, the magnetic force generated by the electromagnet is used for suspending the airplane model in the center of the vertical wind tunnel, the force sensor is used for collecting the gravity of the airplane model born by the contact, when the pulling force is smaller than a certain threshold value, the electromagnet is disconnected, the automatic throwing of the airplane model is achieved, the magnetic force of the electromagnet is controlled through the control circuit board and the force sensor, and the airplane model is grabbed and thrown.
In the invention, the bottom of the main shaft of the rotary bracket is provided with a cable access opening, an upper hanger for hanging the airplane model passes through the cable access opening, and the free swing of the upper hanger cannot be influenced when the bracket is folded.
In the invention, the lower part of the airplane model is provided with a pipe for installing a balance weight.
In the invention, a film camera for recording the release of the airplane model free flight test is arranged on one side of the wind tunnel.
In the invention, a vertical driving motor for vertically driving the main shaft of the rotating bracket to retract upwards is arranged on the horizontal moving platform at the other side of the main shaft of the rotating bracket, the main shaft of the rotating bracket is provided with teeth for being meshed with a vertical moving gear, and the vertical moving gear is connected with the vertical driving motor.
In the invention, the front supporting arm is connected with the front supporting cylinder through a horizontal contraction or extension adjusting mechanism, and the rear supporting arm is connected with the rear supporting cylinder through a horizontal contraction or extension adjusting mechanism.
In the invention, the front supporting cylinder is connected with the front extension shaft through a vertical contraction or extension adjusting mechanism, and the rear supporting cylinder is connected with the rear extension shaft through a vertical contraction or extension adjusting mechanism.
Before a test is started, firstly, determining the extension lengths of a front supporting cylinder and a rear supporting cylinder according to the size of an airplane model and the position of a connecting point on the airplane model, then determining the initial attack angle of the thrown airplane model according to a theoretical calculation value of the tail spin characteristic of the airplane, controlling the initial attack angle of the thrown airplane model by adjusting the extension lengths of a front extension shaft and a rear extension shaft, and suspending the airplane model in the center of a vertical wind tunnel through the attraction force generated by an electromagnet; when a test is started, after a wind tunnel is driven, a rotary driving motor is started to drive a main shaft of a rotary support to rotate, so that an airplane model is driven to rotate at a fixed initial rotation speed, the rotation speed range is 0-20 revolutions per second, the vertical upward air flow speed generated by a vertical wind tunnel is gradually increased from small to small, the aerodynamic force borne by the airplane model is gradually increased, the tensile force borne by a front contact and a rear contact is gradually reduced, and when the tensile force is smaller than a certain threshold value, an electromagnet is switched off, so that the airplane model is automatically put in; the aircraft model sinks under the action of gravity, and in order to avoid collision between the aircraft model and a vertical wind tunnel model free flight test putting device in the rotating process, a vertical driving motor is started to drive a vertical motion gear, a driving rotating support main shaft is driven to vertically and quickly fold upwards so as to be separated from a test section, and the test interference is avoided.
Has the advantages that: according to the invention, the magnetic force is adopted to control the airplane model to be automatically thrown in, and meanwhile, by controlling the throwing posture, the initial rotation rate and the like of the airplane model, the artificial error caused by the free flight test of the vertical wind tunnel model due to insufficient experience or accidental factors of a throwing hand is avoided, the test accuracy is effectively improved, and meanwhile, the test accident caused by the fact that the throwing hand cannot master the throwing time of the airplane model is reduced; in addition, the vertical driving motor drives the driving rotating support main shaft to be vertically and quickly folded upwards, so that the collision between the throwing device and the airplane model is avoided, and the throwing device is positioned above the airplane model and cannot interfere with the air flow blown from the lower part of the airplane model.
Drawings
Fig. 1 is a schematic diagram of a conventional vertical wind tunnel model free flight test.
FIG. 2 is a schematic structural diagram of a preferred embodiment of the present invention.
Fig. 3 is a schematic diagram of a front contact structure in a preferred embodiment of the invention.
FIG. 4 is a schematic view of the rear support canister installation in the preferred embodiment of the invention.
Fig. 5 is a sectional view taken along line a-a in fig. 4.
FIG. 6 is a schematic view of an airplane model suspended from the center of a vertical wind tunnel in accordance with a preferred embodiment of the present invention.
Fig. 7 is a schematic diagram of a free flight test state according to a preferred embodiment of the present invention.
In FIG. 1, the following are labeled: pulley 1, upper hanger 2, ring 3, elastic thread insert 4, lower deflector rod 5, lower hanger 6, tension wire 7, pipe 8, counterweight 9, movie camera 10.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.
Referring to fig. 2 to 7, the vertical wind tunnel model free flight test launching device includes a pulley 1, a pipe 8, a counterweight 9, a film camera 10, a rotary support main shaft 11, a rotary drive gear 12, a vertical motion gear 13, a vertical drive motor 14, a horizontal motion platform 15, a base 16, a rear arm 17, a horizontal contraction or extension adjusting mechanism 18, a rear support cylinder 19, a vertical contraction or extension adjusting mechanism 20, a rear extension shaft 21, a rear contact 22, a cable access 23, a front contact 24, a front extension shaft 25, a front support cylinder 26, a cable passage 27, a front arm 28, a rotary drive motor 29, a vertical wind tunnel model free flight test launching device 30, an airplane model 31, a hanging rope 32, an operator 33, a cable a, a cable passage B, a control circuit board and force sensor C, an electromagnet D, a contact cover E, a support surface F, a support arm tangent plane G, A supporting cylinder section H, a cable passage section I and an adjusting and fastening knob J; the top of a rotary support main shaft 11 which can be vertically folded upwards is arranged on a support frame at the upper part of a wind tunnel, the lower part of the rotary support main shaft 11 penetrates through the middle part of the support frame consisting of a front support arm 28 and a rear support arm 17, the rotary support main shaft 11 is of a hollow structure, a cable access opening 23 is arranged at the bottom of the rotary support main shaft 11, a pulley 1 is arranged on the support frame above the rotary support main shaft 11, one end of a hanging rope 32 which penetrates through the pulley 1 is pulled by an operator 33, the other end of the hanging rope 32 penetrates through the rotary support main shaft 11 and is connected with an upper hanger for hanging an airplane model 31, a pipe 8 for installing a counterweight 9 is arranged at the lower part of the airplane model 31, and a film camera 10 for recording free flight; the base 16 is arranged on the periphery of the upper part of the rotating bracket main shaft 11, the horizontal motion platform 15 is arranged on the base 16, the vertical driving motor 14 for vertically driving the rotating bracket main shaft 11 is arranged on the horizontal motion platform 15 at one side of the rotating bracket main shaft 11, the rotating driving motor 29 for rotationally driving the rotating bracket main shaft 11 is arranged on the horizontal motion platform 15 at the other side of the rotating bracket main shaft 11, the rotating driving gear 12 is sleeved on the rotating bracket main shaft 11 and is connected with the rotating driving motor 29, one end of the vertical motion gear 13 is connected with the vertical driving motor 14, and the other end of the vertical motion gear 13 is meshed with teeth arranged on the rotating bracket main shaft 11; the front support arm 28 is connected with a front support cylinder 26 through a horizontal contraction or extension adjusting mechanism 18, the rear support arm 17 is connected with a rear support cylinder 19 through a horizontal contraction or extension adjusting mechanism 18, the front support cylinder 26 is connected with a front extension shaft 25 through a vertical contraction or extension adjusting mechanism 20, the rear support cylinder 19 is connected with a rear extension shaft 21 through a vertical contraction or extension adjusting mechanism 20, a front contact 24 is arranged in the front extension shaft 25, a rear contact 22 is arranged in the rear extension shaft 21, cable passages 27 for electrifying are respectively arranged in the front support arm 28, the rear support arm 17, the front support cylinder 26 and the rear support cylinder 19 can contract or extend along the horizontal direction, the positions of the front contact 24 and the rear contact 22 which are connected with the airplane model 31 are adjusted, and the front support cylinder can contract or extend along the vertical direction for adjusting the model posture; the structure of the front extension shaft 25 is the same as that of the rear extension shaft 21, the structure of the front contact 24 is the same as that of the rear contact 22, the front contact 24 comprises a control circuit board, a force sensor C, an electromagnet D and a contact cover E, the rear extension shaft 21 is of a hollow structure, a cable A used for electrifying passes through a cable passage B to be connected with the electromagnet D arranged in the contact cover E, the contact cover E is connected with the rear extension shaft 21, the force sensor C is arranged on one side of the electromagnet D, the control circuit board is respectively connected with the force sensor C and the electromagnet D, a connecting point used for being connected with the front contact 24 and the rear contact 22 is arranged on the airplane model 31, the magnetic force generated by the electromagnet D is used for suspending the airplane model 31 in the center of a vertical wind tunnel, the force sensor C is used for acquiring the gravity of the airplane model 31 born by the contact, when the pulling force is smaller than a certain threshold value (5-, the magnetic force of the electromagnet D is controlled through the control circuit board and the force sensor C, so that the airplane model 31 can be grabbed and thrown.
In this embodiment, the upper hanger of the suspended airplane model 31 passes through the cable passage opening 23, and free swing of the upper hanger is not affected when the bracket is retracted.
In the embodiment, before the test starts, firstly, the extension lengths of the front support cylinder 26 and the rear support cylinder 19 are determined according to the size of the airplane model 31 and the position of a connection point on the airplane model 31, after the front support cylinder 26 and the rear support cylinder 19 are adjusted to the predetermined positions, the front support cylinder 26 and the rear support cylinder 19 are screwed and fixed through adjusting the fastening knob J, then, according to a theoretical calculation value of airplane tail spin characteristics, the initial attack angle of the airplane model 31 is determined, the initial attack angle of the airplane model 31 is controlled through adjusting the extension lengths of the front extension shaft 25 and the rear extension shaft 21, the airplane model 31 is connected with the front contact 24 and the rear contact 22 through a connection point on the airplane body, and the attraction force generated by the electromagnet D is suspended in the center of; when a test is started, after a wind tunnel is driven, the rotary driving motor 29 is started to drive the main shaft 11 of the rotary support to rotate, so that the airplane model 31 is driven to rotate at a fixed initial rotation speed, the rotation speed range is 0-20 revolutions per second, the vertical upward air flow speed generated by the vertical wind tunnel is gradually increased from small to small, the aerodynamic force borne by the airplane model 31 is gradually increased, the tensile force borne by the front contact 24 and the rear contact 22 is gradually reduced, and when the tensile force is smaller than a certain threshold value (5-10N), the electromagnet D is switched off, so that the airplane model 31 is automatically put in; the airplane model 31 sinks under the action of gravity (the upper hanger of the airplane model 31 is pulled by an operator 33 to control the sinking distance), and in order to avoid collision between the airplane model 31 and the vertical wind tunnel model free flight test releasing device 30 in the rotating process, the vertical driving motor 14 is started, the rotating support main shaft 11 is driven by the driving vertical motion gear 13 to vertically and quickly retract upwards so as to be separated from a test section, and the test interference is avoided.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. A vertical wind tunnel model free flight test releasing device comprises a pulley, a rotary support main shaft, a rotary driving gear, a horizontal motion platform, a base, a support, a rear extension shaft, a front extension shaft and an airplane model for free flight test; the device is characterized in that the top of a rotary support main shaft which can be vertically folded upwards is arranged on a support frame at the upper part of a wind tunnel, the lower part of the rotary support main shaft penetrates through the middle part of a support frame consisting of a front support arm and a rear support arm, the rotary support main shaft is of a hollow structure, a pulley is arranged on the support frame above the rotary support main shaft, one end of a hanging rope which penetrates through the pulley is pulled by an operator, and the other end of the hanging rope penetrates through the rotary support main shaft and is connected with an upper hanger for hanging an; the base is arranged on the periphery of the upper part of the main shaft of the rotating bracket, the horizontal motion platform is arranged on the base, the rotating drive motor for rotationally driving the main shaft of the rotating bracket is arranged on the horizontal motion platform at one side of the main shaft of the rotating bracket, and the rotating drive gear is sleeved on the main shaft of the rotating bracket and is connected with the rotating drive motor; the front support arm is connected with the front support cylinder, the rear support arm is connected with the rear support cylinder, the front support cylinder is connected with the front extension shaft, the rear support cylinder is connected with the rear extension shaft, a front contact is arranged in the front extension shaft, a rear contact is arranged in the rear extension shaft, and cable passages for electrifying the front contact and the rear contact are respectively arranged in the front support arm, the rear support arm, the front support cylinder and the rear support cylinder; the front extension shaft and the rear extension shaft are identical in structure, the front contact and the rear contact are identical in structure, the front contact comprises a control circuit board, a force sensor, an electromagnet and a contact cover, the rear extension shaft is of a hollow structure, a cable for electrifying penetrates through a cable passage to be connected with the electromagnet installed in the contact cover, the contact cover is connected with the rear extension shaft, the force sensor is arranged on one side of the electromagnet, the control circuit board is respectively connected with the force sensor and the electromagnet, and a connecting point for connecting the front contact and the rear contact is arranged on the airplane model.
2. The vertical wind tunnel model free flight test releasing device according to claim 1, wherein a cable access port is arranged at the bottom of the main shaft of the rotating bracket.
3. The vertical wind tunnel model free flight test launching device according to claim 1, characterized in that a pipe for mounting a counterweight is arranged at the lower part of the aircraft model.
4. The vertical wind tunnel model free flight test release device according to claim 1, characterized in that a movie camera for recording the release of the airplane model free flight test is arranged at one side of the wind tunnel.
5. The vertical wind tunnel model free flight test throwing device according to claim 1, wherein a vertical driving motor for vertically driving the rotating support main shaft to retract upwards is arranged on a horizontal moving platform on the other side of the rotating support main shaft, teeth for meshing with a vertical moving gear are arranged on the rotating support main shaft, and the vertical moving gear is connected with the vertical driving motor.
6. The vertical wind tunnel model free flight test launching device according to claim 1, characterized in that the front support arm is connected with the front support cylinder through a horizontal contraction or extension adjusting mechanism, and the rear support arm is connected with the rear support cylinder through a horizontal contraction or extension adjusting mechanism.
7. The vertical wind tunnel model free flight test launching device according to claim 1, characterized in that the front support cylinder is connected with the front extension shaft through a vertical contraction or extension adjusting mechanism, and the rear support cylinder is connected with the rear extension shaft through a vertical contraction or extension adjusting mechanism.
8. The vertical wind tunnel model free flight test releasing device according to any one of claims 1 to 7, characterized in that before a test starts, firstly, the extension lengths of a front supporting cylinder and a rear supporting cylinder are determined, then, according to a theoretical calculation value of aircraft tail rotation characteristics, the initial attack angle of releasing the aircraft model is determined, the extension lengths of a front extension shaft and a rear extension shaft are adjusted to control the initial attack angle of releasing the aircraft model, and the aircraft model is suspended in the center of a vertical wind tunnel through the attraction force generated by an electromagnet; when a test is started, after a wind tunnel is driven, a rotary driving motor is started to drive a main shaft of a rotary support to rotate, so that an airplane model is driven to rotate at a fixed initial rotation speed, the rotation speed range is 0-20 revolutions per second, the vertical upward air flow speed generated by a vertical wind tunnel is gradually increased from small to small, the aerodynamic force borne by the airplane model is gradually increased, the pulling forces borne by a front contact and a rear contact are gradually reduced, and when the pulling force is smaller than a certain threshold value, an electromagnet is switched off, and the airplane model is automatically put in.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810734111.3A CN109100111B (en) | 2018-07-06 | 2018-07-06 | Device is put in test of freely flying of perpendicular wind tunnel model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810734111.3A CN109100111B (en) | 2018-07-06 | 2018-07-06 | Device is put in test of freely flying of perpendicular wind tunnel model |
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| CN109100111A CN109100111A (en) | 2018-12-28 |
| CN109100111B true CN109100111B (en) | 2020-05-12 |
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| CN201810734111.3A Active CN109100111B (en) | 2018-07-06 | 2018-07-06 | Device is put in test of freely flying of perpendicular wind tunnel model |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109916589B (en) * | 2019-03-27 | 2020-04-14 | 西北工业大学 | Method for testing pressure change characteristics in airdrop cabin of large-size object of transport airplane |
| CN110793744B (en) * | 2019-12-02 | 2021-04-13 | 中国空气动力研究与发展中心 | Wind tunnel test model suspension joint |
| CN110793718B (en) * | 2019-12-03 | 2021-01-26 | 中国空气动力研究与发展中心 | Vertical wind tunnel tail spin test model rotational inertia measurement torsion pendulum table |
| CN111504592B (en) * | 2020-05-06 | 2021-09-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Initial motion state presetting method for high-speed wind tunnel release model test |
| CN112284674B (en) * | 2020-10-21 | 2021-09-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Electromagnet hanging and throwing device for hypersonic wind tunnel model free flight test |
| CN112577707A (en) * | 2020-12-29 | 2021-03-30 | 中国航天空气动力技术研究院 | Impulse wind tunnel air-breathing type engine push resistance measurement test system |
| CN113252285B (en) * | 2021-07-15 | 2021-10-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Vertical wind tunnel model pitching-rolling test device and use method |
| CN115655635B (en) * | 2022-12-14 | 2023-03-07 | 中国空气动力研究与发展中心高速空气动力研究所 | Two-freedom-degree supporting system for full-body freedom-degree flutter or gust test |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3865472B2 (en) * | 1997-07-24 | 2007-01-10 | 石川島播磨重工業株式会社 | Vertical wind tunnel for free descent training |
| CN100343884C (en) * | 2005-04-28 | 2007-10-17 | 西北工业大学 | Plane fleight principle comprehensive demonstration instrument |
| RU2410659C2 (en) * | 2009-04-27 | 2011-01-27 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Method to detect characteristics of aircraft model spin and device for its realisation |
| CN204788880U (en) * | 2015-07-17 | 2015-11-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device is put in fast to wind -tunnel mini mod |
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