CN206450396U - A kind of aircraft haulage gear for wind tunnel test - Google Patents
A kind of aircraft haulage gear for wind tunnel test Download PDFInfo
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- CN206450396U CN206450396U CN201720108799.5U CN201720108799U CN206450396U CN 206450396 U CN206450396 U CN 206450396U CN 201720108799 U CN201720108799 U CN 201720108799U CN 206450396 U CN206450396 U CN 206450396U
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- bearing
- support arm
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- spool
- groove
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Abstract
The utility model discloses a kind of aircraft haulage gear for wind tunnel test, including：First bearing, the second bearing, spool, motor, support arm and pull rope；First bearing and the second bearing are fixed in the outer hole wall of wind-tunnel；Spool is installed by the first bearing and the second bearing and fixed；Motor is fixed on the second bearing, and the output shaft of motor is connected with spool by key；Support arm is fixed on the interior hole wall of wind-tunnel；Wherein, support arm is internally provided with groove, the center of the entrance of groove just to spool；The one ends wound of pull rope is on spool, and the other end is sequentially passed through after the hole wall of wind-tunnel, the entrance of groove, is passed, is connected with aircraft from the outlet of groove.The utility model solves traction problems of the bug in wind tunnel test, and simulation bug is towed the process of flight.
Description
Technical field
The utility model belongs to vehicle technology field, more particularly to a kind of aircraft hauling machine for wind tunnel test
Structure.
Background technology
With the development of science and technology, modern weapons intercepting system is increasingly advanced, to avoid aircraft from being locked, flight
Device is synchronously flown in flight course, it is necessary to draw some small aircraft, so as to disturb enemy radar, reduction aircraft is hit
In probability.Bug does not have power set, the completely traction by main aircraft, and the flight of bug can not disturb master
The flight of aircraft is wanted, and can not be influenced each other each other.Thus it is guaranteed that the flight attitude of bug is most important.
Wind tunnel test is to examine the vital means of bug flight attitude, the utility model precisely in order to solving small
Traction problems of the aircraft in wind tunnel test and design, simulation bug is towed the process of flight.
Utility model content
Technology of the present utility model solves problem：Overcoming the deficiencies in the prior art, there is provided a kind of flying for wind tunnel test
Row device haulage gear, it is intended to solve traction problems of the bug in wind tunnel test, simulation bug is towed flight
Process.
In order to solve the above-mentioned technical problem, the utility model discloses a kind of aircraft hauling machine for wind tunnel test
Structure, including：First bearing (1), the second bearing (2), spool (3), motor (4), support arm (5) and pull rope (6)；
First bearing (1) and the second bearing (2) are fixed in the outer hole wall of wind-tunnel；
The spool (3) is installed by first bearing (1) and the second bearing (2) and fixed；
The motor (4) is fixed on second bearing (2), and output shaft and the spool (3) of the motor (4) lead to
Cross key connection；
The support arm (5) is fixed on the interior hole wall of wind-tunnel；Wherein, the support arm (5) is internally provided with groove (7),
Center of the entrance of the groove (7) just to the spool (3)；
The one ends wound of the pull rope (6) is on the spool (3), and the other end sequentially passes through the hole wall, described of wind-tunnel
After the entrance of groove (7), pass, be connected with aircraft from the outlet of the groove (7).
In the above-mentioned aircraft haulage gear for wind tunnel test, the support arm (5) includes：The first support arm of level
(501), and, with the first support arm (501) be in set angle second support arm (502), and, be arranged on described first
The pulley (503) of the corner of arm (501) and second support arm (502) connection；
Wherein, the pulley (503) is arranged on the first support arm (501) and second support arm by clutch shaft bearing (801)
(502) corner of connection；
The other end of the pull rope (6), which is passed through, to be arranged on after the internal first paragraph groove of first support arm (501), is passed through
Pulley (503) deflecting, is passed from the internal second segment groove of second support arm (502) is arranged on.
In the above-mentioned aircraft haulage gear for wind tunnel test, the value of the set angle is：30 °~60 °；
The first support arm (501) is located on the axis of the wind-tunnel.
In the above-mentioned aircraft haulage gear for wind tunnel test, the pull rope (6) meets setting length, so as to fly
Range of movement satisfaction≤600mm of row device.
In the above-mentioned aircraft haulage gear for wind tunnel test, first bearing (1) and the second bearing (2) and volume
Connected between axle (3) by second bearing (802)；Wherein, first bearing (1) and the second bearing (2) and second axle
The outer ring for holding (802) coordinates, and the spool (3) and the inner ring of the second bearing (802) coordinate.
In the above-mentioned aircraft haulage gear for wind tunnel test, the entrance and exit of the groove (7) is oval
Fillet.
The utility model has advantages below：
(1) the aircraft haulage gear described in the utility model for wind tunnel test, solves bug in wind-tunnel
Traction problems during experiment, can simulate the process that bug is towed flight, the flight attitude of bug is examined
Test, it is ensured that flight of the bug without interference with main aircraft, it is to avoid influence of the bug to main aircraft.
(2) the aircraft haulage gear described in the utility model for wind tunnel test, simple in construction, installing/dismounting side
Just.
(3) the aircraft haulage gear described in the utility model for wind tunnel test, pull rope on support arm by setting
Groove realization and the connection of aircraft are put, and the turning of groove is provided with pulley, pull rope is reduced in motion process
Frictional resistance, it is to avoid pull rope it is stuck.
(4) the aircraft haulage gear described in the utility model for wind tunnel test, designs oval at the two ends of groove
Shape fillet, reduce the abrasion of pull rope, it is to avoid the fracture of pull rope, extends the service life of pull rope.
Brief description of the drawings
Fig. 1 is a kind of structural representation of aircraft haulage gear for wind tunnel test in the utility model；
Fig. 2 is a kind of scheme of installation of pulley in the utility model embodiment.
Embodiment
It is new to this practicality below in conjunction with accompanying drawing to make the purpose of this utility model, technical scheme and advantage clearer
The public embodiment of type is described in further detail.
Reference picture 1, shows a kind of structural representation of aircraft haulage gear for wind tunnel test in the utility model
Figure.In the present embodiment, the aircraft haulage gear for wind tunnel test, including：First bearing 1, the second bearing 2, volume
Axle 3, motor 4, support arm 5 and pull rope 6.
As shown in figure 1, the bearing 2 of the first bearing 1 and second is fixed in the outer hole wall of wind-tunnel 9.The spool 3 passes through
The bearing 2 of first bearing 1 and second, which is installed, to be fixed.The motor 4 is fixed on second bearing 2, the motor 4 it is defeated
Shaft is connected with the spool 3 by key.The support arm 5 is fixed on the interior hole wall of wind-tunnel；Wherein, the inside of the support arm 5
It is provided with groove 7, the center of the entrance of the groove 7 just to the spool 3.The one ends wound of the pull rope 6 is in the volume
On axle 3, the other end is sequentially passed through after the hole wall of wind-tunnel, the entrance of the groove 7, is passed from the outlet of the groove 7, with flying
Row device 10 is connected.
It is preferred that, the support arm 5 includes：The first support arm 501 of level, and, it is in set angle with the first support arm 501
The second support arm 502 of degree, and, it is arranged on the pulley 503 for the corner that the first support arm 501 and second support arm 502 are connected.
In the present embodiment, reference picture 2, show a kind of scheme of installation of pulley in the utility model embodiment.Institute
State corner's (turning of connecting of first support arm 501 and second support arm 502 that pulley 503 is arranged on support arm 5 by clutch shaft bearing 801
At angle).Specifically, such as Fig. 2, one end and the support arm 5 of clutch shaft bearing 801 coordinate, and the other end coordinates with end cap 11, and end cap 11 is fixed
On support arm 5, pulley 503 is freely rotatable.
Wherein, the other end of the pull rope 6 is passed through through being arranged on after the first paragraph groove inside first support arm 501
The deflecting of pulley 503 is crossed, is passed from the second segment groove being arranged on inside second support arm 502.
It should be noted that the support arm 5 can be an overall structure, first support arm 501 and second are classified as
Arm 502 is only to facilitate description, should not be used as to limitation of the present utility model.
It is preferred that, the value of the set angle is：30 °~60 ° (including 30 ° and 60 °).The first support arm 501
In on the axis of the wind-tunnel.For example, the horizontal range of interior hole wall of the first support arm 501 away from wind-tunnel 9 can be
600mm。
It is preferred that, the pull rope 6 meets setting length, so that range of movement satisfaction≤600mm of aircraft 10.Change and
Yan Zhi, can control the length of pull rope 6, and then allow aircraft 10 in the range of 600mm by the motion of spool 3
Motion.
It is preferred that, connected between the bearing 2 of the first bearing 1 and second and spool 3 by second bearing 802；Wherein, institute
State the first bearing 1 and the second bearing 2 and the outer ring of the second bearing 802 coordinates, the spool 3 and the second bearing 802
Inner ring coordinate.
It is preferred that, the oval fillet of entrance and exit of the groove 7.
In the present embodiment, the operation principle of the aircraft haulage gear for wind tunnel test is as follows：
A kind of operation principle of aircraft hitch structure for wind tunnel test is that the driving spool 3 of motor 4 is rotated, and is passed through
Pull rope 6 drives aircraft 10 to move.In wind tunnel test, pull rope 6 is discharged, when pull rope 6 is discharged into certain length, is stopped
Only discharge, observe the flight attitude of now aircraft 10；Stop before experiment, then pull rope 6 is recovered to initial position.
In summary, the aircraft haulage gear described in the utility model for wind tunnel test, solves bug
Traction problems in wind tunnel test, can simulate the process that bug is towed flight, to the flight attitude of bug
Test, it is ensured that flight of the bug without interference with main aircraft, it is to avoid influence of the bug to main aircraft.
Secondly, the aircraft haulage gear described in the utility model for wind tunnel test, simple in construction, installing/dismounting side
Just.
In addition, the aircraft haulage gear described in the utility model for wind tunnel test, pull rope passes through on support arm
Set groove to realize the connection with aircraft, and the turning of groove is provided with pulley, reduce pull rope in motion process
In frictional resistance, it is to avoid pull rope it is stuck.Further, the oval fillet of two ends design of groove, reduces traction
The abrasion of rope, it is to avoid the fracture of pull rope, extends the service life of pull rope.
It is described above, the only optimal embodiment of the utility model, but protection domain of the present utility model is not
This is confined to, any one skilled in the art can readily occur in the technical scope that the utility model is disclosed
Change or replacement, should all cover within protection domain of the present utility model.
The content not being described in detail in the utility model specification belongs to the known technology of professional and technical personnel in the field.
Claims (6)
1. a kind of aircraft haulage gear for wind tunnel test, it is characterised in that including：First bearing (1), the second bearing
(2), spool (3), motor (4), support arm (5) and pull rope (6)；
First bearing (1) and the second bearing (2) are fixed in the outer hole wall of wind-tunnel；
The spool (3) is installed by first bearing (1) and the second bearing (2) and fixed；
The motor (4) is fixed on second bearing (2), and output shaft and the spool (3) of the motor (4) pass through key
Connection；
The support arm (5) is fixed on the interior hole wall of wind-tunnel；Wherein, the support arm (5) is internally provided with groove (7), described
Center of the entrance of groove (7) just to the spool (3)；
The one ends wound of the pull rope (6) is on the spool (3), and the other end sequentially passes through the hole wall of wind-tunnel, the groove
(7) after entrance, pass, be connected with aircraft from the outlet of the groove (7).
2. aircraft haulage gear according to claim 1, it is characterised in that the support arm (5) includes：The first of level
Support arm (501), and, it is in the second support arm (502) of set angle with the first support arm (501), and, it is arranged on described the
The pulley (503) of the corner of one support arm (501) and second support arm (502) connection；
Wherein, the pulley (503) is arranged on the first support arm (501) and second support arm (502) by clutch shaft bearing (801)
The corner of connection；
The other end of the pull rope (6), which is passed through, to be arranged on after the internal first paragraph groove of first support arm (501), by described
Pulley (503) deflecting, is passed from the internal second segment groove of second support arm (502) is arranged on.
3. aircraft haulage gear according to claim 2, it is characterised in that
The value of the set angle is：30 °~60 °；
The first support arm (501) is located on the axis of the wind-tunnel.
4. aircraft haulage gear according to claim 1, it is characterised in that the pull rope (6) meets setting length,
So that range of movement satisfaction≤600mm of aircraft.
5. aircraft haulage gear according to claim 1, it is characterised in that first bearing (1) and the second bearing
(2) it is connected between spool (3) by second bearing (802)；Wherein, first bearing (1) and the second bearing (2) with it is described
The outer ring of second bearing (802) coordinates, and the spool (3) and the inner ring of the second bearing (802) coordinate.
6. aircraft haulage gear according to claim 1, it is characterised in that the entrance and exit of the groove (7) is in
Oval fillet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720108799.5U CN206450396U (en) | 2017-02-06 | 2017-02-06 | A kind of aircraft haulage gear for wind tunnel test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720108799.5U CN206450396U (en) | 2017-02-06 | 2017-02-06 | A kind of aircraft haulage gear for wind tunnel test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206450396U true CN206450396U (en) | 2017-08-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720108799.5U Active CN206450396U (en) | 2017-02-06 | 2017-02-06 | A kind of aircraft haulage gear for wind tunnel test |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109100110A (en) * | 2018-08-10 | 2018-12-28 | 中国航天空气动力技术研究院 | One kind being applied to double venturi Thrust-vectoring Nozzles ventilation supporting arm devices |
| CN114923656A (en) * | 2022-07-20 | 2022-08-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Rope supporting system for full-aircraft flutter wind tunnel test |
-
2017
- 2017-02-06 CN CN201720108799.5U patent/CN206450396U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109100110A (en) * | 2018-08-10 | 2018-12-28 | 中国航天空气动力技术研究院 | One kind being applied to double venturi Thrust-vectoring Nozzles ventilation supporting arm devices |
| CN109100110B (en) * | 2018-08-10 | 2020-05-12 | 中国航天空气动力技术研究院 | Be applied to two throat thrust vectoring nozzle support arm device of ventilating |
| CN114923656A (en) * | 2022-07-20 | 2022-08-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Rope supporting system for full-aircraft flutter wind tunnel test |
| CN114923656B (en) * | 2022-07-20 | 2023-05-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Rope supporting system for full-machine flutter wind tunnel test |
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