CN213397576U - Water rescue amphibious aircraft critical ice-shaped wind tunnel research and development test steering device - Google Patents
Water rescue amphibious aircraft critical ice-shaped wind tunnel research and development test steering device Download PDFInfo
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- CN213397576U CN213397576U CN202022142473.9U CN202022142473U CN213397576U CN 213397576 U CN213397576 U CN 213397576U CN 202022142473 U CN202022142473 U CN 202022142473U CN 213397576 U CN213397576 U CN 213397576U
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- 238000012360 testing method Methods 0.000 title claims abstract description 14
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 9
- 238000012827 research and development Methods 0.000 title claims abstract description 7
- 230000007246 mechanism Effects 0.000 claims abstract description 21
- 230000008859 change Effects 0.000 claims abstract description 18
- 238000011981 development test Methods 0.000 claims 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000002474 experimental method Methods 0.000 description 5
- 230000008014 freezing Effects 0.000 description 4
- 238000007710 freezing Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
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Abstract
The utility model discloses a critical icy wind-tunnel research and development test of amphibious aircraft of rescue on water turns to device, including the wind channel, the inside in wind channel is provided with slewing mechanism, and slewing mechanism's inside is provided with steering mechanism, and slewing mechanism includes ring groove, and ring groove sets up on the inner wall in wind channel, and ring groove's inside joint has the swivel, the utility model discloses the beneficial effect who reaches is: the first motor through setting up drives first gear revolve, first gear drives annular rack and rotates, annular rack drives the change ring and rotates, drive the change ring when the change ring rotates and rotate, start the second motor and drive the second gear revolve, the second gear drives the arc rack and rotates around the change ring centre of a circle, it rotates around the change ring centre of a circle to encircle the actuating cylinder through turning to the zone, and then the aircraft model of two inside centre gripping of arc board that make takes place to rotate, and then the aircraft that makes can turn to inside the wind channel, and then the wind tunnel test that makes can draw the data of aircraft and different angle wind currents.
Description
Technical Field
The utility model relates to a critical icy wind-tunnel research and development test of amphibious aircraft of rescue on water turns to device belongs to wind-tunnel test technical field.
Background
The wind tunnel, i.e. wind tunnel laboratory, is a pipeline-shaped experimental facility which is used for generating and controlling airflow in an artificial mode, simulating the flowing condition of the air around an aircraft or an entity, measuring the action effect of the airflow on the entity and observing physical phenomena, is one of the most common and effective tools for aerodynamic experiments, and is a large-scale special wind tunnel with complex performance, which is a ground experimental facility for researching the icing forms, icing tolerances and anti-icing technology of different parts windward surfaces and an external sensing part of a detecting instrument when an airplane flies under icing meteorological conditions.
During the wind tunnel experiment, the airplane model is fixed in the icing wind tunnel, and the icing condition of the airplane model in the icing wind tunnel can be determined through the experiment of determining the icing form of each part of the airplane so as to determine the icing form, the icing area, the icing amount and the icing rate of the icing form, determine the icing tolerance and the surface which needs to be anti-iced, and provide a basis for safety design for the anti-icing of the airplane. However, when the existing icing wind tunnel is used for testing a fan, blown wind flow forward-direction airplanes can only obtain forward-direction anti-icing data of the airplanes, and cannot obtain data of wind flows facing other positions of a flyer.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to overcome prior art and when carrying out the wind tunnel experiment, fix the aircraft model inside freezing wind tunnel, through the aircraft model in the inside icing condition in freezing wind tunnel can be through confirming the experiment that each part of aircraft freezes the form to confirm the ice shape of freezing and icing district, icing volume and the speed of freezing, thereby confirm the surface of icing tolerance and must anti-icing, provide safety design's basis for the aircraft anti-icing. However, when the existing icing wind tunnel is used for testing a fan, the blown-up wind flow forward aircraft can only obtain forward anti-icing data of the aircraft, and cannot obtain data of other positions of the flying brother facing the wind flow.
In order to solve the technical problem, the utility model provides a following technical scheme:
the utility model discloses a critical ice-shaped wind tunnel research and development test steering device of an amphibious aircraft for rescue on water, which comprises a wind channel, wherein a rotating mechanism is arranged inside the wind channel, and a steering mechanism is arranged inside the rotating mechanism;
slewing mechanism includes ring groove, ring groove sets up on the inner wall in wind channel, ring groove's inside joint has the change, the ring channel has been seted up on the outer wall of change, the inside of ring channel is provided with annular rack, annular rack meshes with first gear mutually, first gear joint is in the joint inslot portion, the joint groove is set up on the outer wall in wind channel, the first drive shaft of the central fixedly connected with of department of first gear, the output fixed connection of first drive shaft and first motor, first motor fixed connection is on the outer wall in wind channel.
As a preferred technical scheme of the utility model, steering mechanism includes the pivot, two fixed connection is on the both ends inner wall of change ring respectively in the pivot, two the other end of pivot passes through the bearing and rotates the connection on the both ends outer wall of change ring, equal fixedly connected with cylinder on the upper and lower both ends inner wall of change ring, the output fixedly connected with arc board of cylinder, fixedly connected with arc rack on the lateral wall of one side of change ring, arc rack meshes with the second gear mutually, the second gear is fixed cup joints on the second drive shaft on the surface, the second drive shaft rotates to be connected on the inner wall in wind channel, the one end of second drive shaft and the output fixed connection of second motor, second motor fixed connection is on the outer wall in wind channel.
As an optimal technical scheme of the utility model, ring groove and swivel phase-match.
As an optimized technical scheme of the utility model, the arc rack sets up around the centre of a circle of steering ring.
As an optimal technical solution of the present invention, the circle center of the steering ring coincides with the circle center of the swivel.
The utility model discloses the beneficial effect who reaches is: the first motor through setting up drives first gear revolve, first gear drives annular rack and rotates, annular rack drives the change ring and rotates, drive the change ring when the change ring rotates and rotate, start the second motor and drive the second gear revolve, the second gear drives the arc rack and rotates around the change ring centre of a circle, it rotates around the change ring centre of a circle to encircle the actuating cylinder through turning to the zone, and then the aircraft model of two inside centre gripping of arc board that make takes place to rotate, and then the aircraft that makes can turn to inside the wind channel, and then the wind tunnel test that makes can draw the data of aircraft and different angle wind currents.
Drawings
The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural diagram of the present invention;
fig. 2 is a schematic top view of the present invention;
fig. 3 is a sectional view taken along the direction a-a of the present invention;
in the figure: 1. an air duct; 2. a rotating mechanism; 21. an annular neck; 22. rotating the ring; 23. an annular groove; 24. An annular rack; 25. a first gear; 26. a clamping groove; 27. a first drive shaft; 28. a first motor; 3. A steering mechanism; 31. a rotating shaft; 32. a bearing; 33. a steering ring; 34. a cylinder; 35. an arc plate; 36. an arc-shaped rack; 37. a second gear; 38. a second drive shaft; 39. a second motor.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are presented herein only to illustrate and explain the present invention, and not to limit the present invention.
Example 1
As shown in fig. 1-3, the utility model provides a critical ice-shaped wind tunnel research and development test steering device for an amphibious aircraft for rescue on water, which comprises a wind channel 1, a rotating mechanism 2 arranged in the wind channel 1, and a steering mechanism 3 arranged in the rotating mechanism 2;
the rotating mechanism 2 comprises an annular clamping groove 21, the annular clamping groove 21 is formed in the inner wall of the air duct 1, a rotating ring 22 is clamped in the annular clamping groove 21, an annular groove 23 is formed in the outer wall of the rotating ring 22, an annular rack 24 is arranged in the annular groove 23, the annular rack 24 is meshed with a first gear 25, the first gear 25 is clamped in a clamping groove 26, the clamping groove 26 is formed in the outer wall of the air duct 1, a first driving shaft 27 is fixedly connected to the center of the first gear 25, the first driving shaft 27 is fixedly connected with the output end of a first motor 28, the first motor 28 is fixedly connected to the outer wall of the air duct 1, the first motor 28 is started to drive the first gear 25 to rotate, the first gear 25 drives the annular rack 24 to rotate, the annular rack 24 drives the rotating ring 22 to rotate, and when the rotating ring 22 rotates, the steering ring 33 is driven to rotate, and the airplane model is driven to.
The steering mechanism 3 comprises a rotating shaft 31, the two rotating shafts 31 are respectively fixedly connected to the inner walls of the two ends of the rotating ring 22, the other ends of the two rotating shafts 31 are rotatably connected to the outer walls of the two ends of the steering ring 33 through bearings 32, air cylinders 34 are fixedly connected to the inner walls of the upper and lower ends of the steering ring 33, an arc plate 35 is fixedly connected to the output end of the air cylinder 34, an arc rack 36 is fixedly connected to the side wall of one side of the steering ring 33, the arc rack 36 is meshed with a second gear 37, the second gear 37 is fixedly sleeved on the surface of a second driving shaft 38, the second driving shaft 38 is rotatably connected to the inner wall of the air duct 1, one end of the second driving shaft 38 is fixedly connected to the output end of a second motor 39, the second motor 39 is fixedly connected to the outer wall of the air duct 1, the second motor 39 is started to drive the second gear 37 to rotate, drive cylinder 34 through steering ring 33 and rotate around the steering ring 33 centre of a circle, and then the aircraft model of the inside centre gripping of two arc boards 35 that make takes place to turn to down, and then the aircraft model that makes can turn to inside the wind channel, makes aircraft model and wind channel interior wind current multi-angle contact, and then the wind tunnel test that makes can obtain the data of aircraft and different angle wind currents.
The annular slot 21 is matched with the rotary ring 22 to prevent the rotary ring 22 from shaking in the annular slot 21.
The arc-shaped rack 36 is arranged around the center of the steering ring 33, so that the arc-shaped rack 36 drives the steering ring 33 to rotate synchronously when rotating.
The circle center of the steering ring 33 coincides with the circle center of the swivel 22, so that the swivel 22 rotates to drive the airplane model inside the steering ring 33 to rotate around the same circle point.
Specifically, when the utility model is used, firstly, the airplane model is placed between the two arc plates 35, then the air cylinder 34 is started, the two arc plates 35 are pushed to approach each other through the air cylinder 34, and then the two arc plates 35 clamp and fix the airplane model, when the multi-angle data of the airplane facing to the wind flow needs to be known, the first motor 28 is started to drive the first gear 25 to rotate, the first gear 25 drives the annular rack 24 to rotate, the annular rack 24 drives the swivel 22 to rotate, the swivel 22 drives the swivel 33 to rotate when rotating, the second motor 39 is started to drive the second gear 37 to rotate, the second gear 37 drives the arc rack 36 to rotate around the circle center of the swivel 33, the air cylinder 34 is driven to rotate around the circle center of the swivel 33 through the swivel 33, and then the airplane model clamped inside the two arc plates 35 rotates, and then the airplane model can be steered inside the wind channel, the airplane model is in multi-angle contact with the wind flow in the air channel, and then the wind tunnel test can obtain the data of the airplane and the wind flow at different angles.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The steering device for the critical ice-shaped wind tunnel research and development test of the amphibious aircraft for rescue on water is characterized by comprising an air duct (1), wherein a rotating mechanism (2) is arranged in the air duct (1), and a steering mechanism (3) is arranged in the rotating mechanism (2);
slewing mechanism (2) include ring slot (21), ring slot (21) are seted up on the inner wall in wind channel (1), the inside joint of ring slot (21) has change (22), ring channel (23) have been seted up on the outer wall of change (22), the inside of ring channel (23) is provided with annular rack (24), annular rack (24) mesh with first gear (25), first gear (25) joint is inside joint groove (26), joint groove (26) are seted up on the outer wall in wind channel (1), the first drive shaft (27) of fixedly connected with is located at the center of first gear (25), the output fixed connection of first drive shaft (27) and first motor (28), first wind channel motor (28) fixed connection is on the outer wall in wind channel (1).
2. The critical ice-shaped wind tunnel development test steering device for the amphibious aircraft for rescue on water according to claim 1, wherein the steering mechanism (3) comprises two rotating shafts (31), the two rotating shafts (31) are respectively and fixedly connected to inner walls of two ends of a rotating ring (22), the other ends of the two rotating shafts (31) are rotatably connected to outer walls of two ends of a steering ring (33) through bearings (32), inner walls of the upper end and the lower end of the steering ring (33) are respectively and fixedly connected with air cylinders (34), an output end of each air cylinder (34) is fixedly connected with an arc plate (35), an arc rack (36) is fixedly connected to a side wall of one side of the steering ring (33), the arc rack (36) is meshed with a second gear (37), the second gear (37) is fixedly sleeved on the surface of a second driving shaft (38), and the second driving shaft (38) is rotatably connected to an inner wall of the air duct (1), one end of the second driving shaft (38) is fixedly connected with the output end of a second motor (39), and the second motor (39) is fixedly connected to the outer wall of the air duct (1).
3. The critical ice-shaped wind tunnel development test steering device of the amphibious rescue aircraft according to claim 1, wherein the ring-shaped clamping groove (21) is matched with the rotating ring (22).
4. The critical ice-shaped wind tunnel development test steering device of the amphibious rescue aircraft according to claim 2, wherein the arc-shaped rack (36) is arranged around the center of the steering ring (33).
5. The critical ice-shaped wind tunnel development test steering device of the amphibious water rescue aircraft according to claim 2, wherein the circle center of the steering ring (33) coincides with the circle center of the rotating ring (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022142473.9U CN213397576U (en) | 2020-09-25 | 2020-09-25 | Water rescue amphibious aircraft critical ice-shaped wind tunnel research and development test steering device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022142473.9U CN213397576U (en) | 2020-09-25 | 2020-09-25 | Water rescue amphibious aircraft critical ice-shaped wind tunnel research and development test steering device |
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| Publication Number | Publication Date |
|---|---|
| CN213397576U true CN213397576U (en) | 2021-06-08 |
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| CN202022142473.9U Active CN213397576U (en) | 2020-09-25 | 2020-09-25 | Water rescue amphibious aircraft critical ice-shaped wind tunnel research and development test steering device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114061887A (en) * | 2021-12-01 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Amphibious aircraft power lift-increasing full-mode wind tunnel test device |
-
2020
- 2020-09-25 CN CN202022142473.9U patent/CN213397576U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114061887A (en) * | 2021-12-01 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Amphibious aircraft power lift-increasing full-mode wind tunnel test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Research and development of critical ice wind tunnel test steering device for water rescue amphibious aircraft Effective date of registration: 20220304 Granted publication date: 20210608 Pledgee: Shaanxi SME financing Company limited by guarantee Pledgor: XI'AN YALONG AVIATION ELECTROMECHANICAL CO.,LTD. Registration number: Y2022980002171 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20230816 Granted publication date: 20210608 Pledgee: Shaanxi SME financing Company limited by guarantee Pledgor: XI'AN YALONG AVIATION ELECTROMECHANICAL CO.,LTD. Registration number: Y2022980002171 |
|
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 710089 No. 38, Hangkong 1st Road, National Aviation high tech industry base, Xi'an, Shaanxi Province Patentee after: Xi'an Yalong Aviation Electromechanical Co.,Ltd. Country or region after: China Address before: No.38, Hangkong 1st Road, Xi'an Aviation base, Shaanxi 710000 Patentee before: XI'AN YALONG AVIATION ELECTROMECHANICAL CO.,LTD. Country or region before: China |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Research and development of a critical ice shaped wind tunnel for amphibious aircraft in water rescue, testing and turning device Granted publication date: 20210608 Pledgee: Xi'an Caijin Financing Guarantee Co.,Ltd. Pledgor: Xi'an Yalong Aviation Electromechanical Co.,Ltd. Registration number: Y2024980005601 |