CN210513615U - Rudder deflection angle changing device for wind tunnel test model - Google Patents
Rudder deflection angle changing device for wind tunnel test model Download PDFInfo
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- CN210513615U CN210513615U CN201921225722.1U CN201921225722U CN210513615U CN 210513615 U CN210513615 U CN 210513615U CN 201921225722 U CN201921225722 U CN 201921225722U CN 210513615 U CN210513615 U CN 210513615U
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Abstract
A wind tunnel test model rudder deflection angle changing device relates to the field of wind tunnel test model design; a rudder, an angle pin, a jackscrew and a model; wherein, the model is axially and horizontally placed; the rudder is vertically and fixedly arranged at the top end of the model, and vertically and downwards extends into the model; the angle pin is horizontally arranged in the model and fixedly connected with the rudder, so that the rudder is clamped; the jackscrew is arranged inside the model; the jackscrew is fixedly arranged at the axial outer end of the angle pin; the limiting of the angle pin is realized; the rudder comprises a control surface and a control shaft; wherein the control surface is arranged at the top end of the model; the control shaft is axially and vertically fixedly arranged at the bottom of the control surface; the rudder shaft vertically extends downwards into a rudder shaft hole of the model; the utility model discloses both guaranteed that the rudder declination is accurate, realized easy operation convenience again. Practice proves that the device has good effect.
Description
Technical Field
The utility model relates to a wind tunnel test model design field, especially a wind tunnel test model helm deflection angle changing device.
Background
The aircraft control surface is used for generating an aircraft balance force and a control force by deflection in the airflow to operate the aerodynamic surface of the aircraft, so that the control of the deflection angle of the control surface is critical. The traditional wind tunnel test model rudder deflection angle changing device has various forms such as a common angle pin, a rotating shaft and a positioning pin, an angle block and the like. Common angle pin: the effective contact length between the model and the angle pin is required to be more than 20mm, and the model needs to be disassembled and assembled sometimes, so that the limitation is certain; the rotating shaft is provided with a positioning pin: the structural design is limited by the model space; an angle block: this form needs a set of rudder face of every angle processing, and is in large quantity, and the handling capacity is big, and the cost is higher, and it takes time to change the rudder state of inclining.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome the above-mentioned not enough of prior art, provide a wind-tunnel test model becomes rudder declination device, both guaranteed that the rudder declination is accurate, realize easy operation convenience again. Practice proves that the device has good effect.
The above object of the present invention is achieved by the following technical solutions:
a wind tunnel test model rudder deflection angle changing device comprises a rudder, an angle pin, a jackscrew and a model; wherein, the model is axially and horizontally placed; the rudder is vertically and fixedly arranged at the top end of the model, and vertically and downwards extends into the model; the angle pin is horizontally arranged in the model and fixedly connected with the rudder, so that the rudder is clamped; the jackscrew is arranged inside the model; the jackscrew is fixedly arranged at the axial outer end of the angle pin; the limiting of the angle pin is realized.
In the wind tunnel test model rudder deflection angle varying device, the side wall of the top end of the model is provided with a rudder shaft hole and an angle pin groove; the rudder shaft hole is axially arranged along the vertical direction; the angle pin groove is axially arranged along the horizontal direction; and the rudder shaft hole is communicated with the angle pin slot.
In the above device for changing the rudder deflection angle of the wind tunnel test model, the rudder comprises a control surface and a control shaft; wherein the control surface is arranged at the top end of the model; the control shaft is axially and vertically fixedly arranged at the bottom of the control surface; and the rudder shaft vertically extends downwards into a rudder shaft hole of the model.
In the above wind tunnel test model rudder deflection angle varying device, the rudder shaft and the rudder shaft hole are in clearance fit; the distance between the outer wall of the rudder shaft and the inner wall of the rudder shaft hole is 0.01-0.03 mm.
In the above wind tunnel test model rudder deflection angle varying device, the angle pin includes 2 straight pin columns and 1 oblique pin column; the 2 straight pins are symmetrically arranged in the angle pin grooves in parallel, and the axial directions of the straight pins are parallel to the axial direction of the angle pin grooves; 1 inclined pin column is fixedly arranged among 2 straight pin columns; 2 straight pins and 1 oblique pin constitute H-shaped structure.
In the above wind tunnel test model rudder deflection angle varying device, the inclination angle δ of the oblique pin column is 0-50 °.
In the wind tunnel test model rudder deflection angle varying device, the outer side wall of the straight pin column is in clearance fit with the inner wall of the angle pin groove; the distance between the outer side wall of the straight pin column and the inner wall of the angle pin groove is 0.01-0.03 mm.
In the above wind tunnel test model rudder deflection angle varying device, the jackscrew is embedded in a rear groove surrounded by the straight edge of the oblique pin column and the 2 straight pin columns; the jackscrew is in threaded connection with the angle pin.
In the wind tunnel test model rudder deflection angle varying device, an inclined groove is formed in the position, corresponding to the angle pin groove, of the axial side wall of the rudder shaft; the inclination angle of the inclined groove is delta; the bevel edge of the angle pin is correspondingly arranged with the inclined groove.
In the above wind tunnel test model rudder deflection angle varying device, the oblique side of the angle pin passes through the axis of the rudder shaft.
Compared with the prior art, the utility model have following advantage:
(1) the tail end face of the model is directly operated, the model does not need to be disassembled or assembled, the test cost is reduced, and the test efficiency is improved;
(2) the utility model has simple and convenient processing and high angle positioning precision;
(3) the utility model discloses extensively be applicable to various wind-tunnel test models, be particularly useful for the model that rudder axle and model tail end face distance are shorter.
Drawings
Fig. 1 is a side sectional view of the rudder deflection angle varying device of the present invention;
fig. 2 is a top cross-sectional view of the angle pin of the present invention.
Detailed Description
The invention will be described in further detail with reference to the following figures and specific embodiments:
the utility model provides a wind tunnel test model rudder deflection angle changing device, which adopts clearance fit and thread fit to ensure accurate and firm positioning of the deflection angle of a control surface, is simple and convenient to operate and greatly improves the test efficiency; meanwhile, the device is widely applicable to various test models, in particular to models with short distance between a rudder shaft and the tail face of the model.
As shown in fig. 1, which is a side cross-sectional view of a rudder deflection angle varying device, it can be known from the figure that a wind tunnel test model rudder deflection angle varying device comprises a rudder 1, an angle pin 2, a jackscrew 3 and a model 4; wherein, the model 4 is axially and horizontally placed; the rudder 1 is vertically and fixedly arranged at the top end of the model 4, and the rudder 1 vertically extends downwards into the model 4; the angle pin 2 is horizontally arranged in the model 4, and the angle pin 2 is fixedly connected with the rudder 1, so that the rudder 1 is clamped; the jackscrew 3 is arranged inside the model 4; and the jackscrew 3 is fixedly arranged at the axial outer end of the angle pin 2; the limiting of the angle pin 2 is realized.
Wherein, the side wall of the top end of the model 4 is provided with a rudder shaft hole 41 and an angle pin slot 42; the rudder shaft hole 41 is axially arranged along the vertical direction; the angle pin groove 42 is axially arranged along the horizontal direction; and the rudder shaft hole 41 communicates with the angle pin groove 42. The rudder 1 comprises a control surface 11 and a control shaft 12; wherein the control surface 11 is arranged at the top end of the model 4; the control shaft 12 is axially and vertically fixedly arranged at the bottom of the control surface 11; and the rudder shaft 12 extends vertically downward into the rudder shaft hole 41 of the model 4.
The rudder shaft 12 is in clearance fit with the rudder shaft hole 41; the distance between the outer wall of the rudder shaft 12 and the inner wall of the rudder shaft hole 41 is 0.01-0.03 mm.
As shown in fig. 2, which is a top cross-sectional view of the angle pin, it can be seen that the angle pin 2 includes 2 straight pins 21 and 1 oblique pin 22; the 2 straight pins 21 are symmetrically arranged in the angle pin slot 42 in parallel, and the axial direction of the straight pins 21 is parallel to the axial direction of the angle pin slot 42; 1 inclined pin 22 is fixedly arranged between 2 straight pins 21; 2 straight pins 21 and 1 oblique pin 22 form an H-shaped structure. The angle delta of the angle pin 22 is 0-50 deg..
The outer side wall of the straight pin column 21 is in clearance fit with the inner wall of the angle pin groove 42; the distance between the outer side wall of the straight pin 21 and the inner wall of the angle pin groove 42 is 0.01-0.03 mm.
The jackscrew 3 is embedded in a rear groove formed by the straight edges of the inclined pins 22 and the 2 straight pins 21; the jackscrew 3 is in threaded connection with the angle pin 2. The diameter of the jackscrew 3 is smaller than the diameter of the opening of the rear groove, the front end face of the jackscrew 3 props against the groove face of the rear end of the angle pin and is fixedly connected with the model through threaded fit, and the accuracy of the rudder deflection angle delta is guaranteed.
An inclined groove 13 is formed in the axial side wall of the rudder shaft 12 corresponding to the angle pin groove 42; the inclination angle of the inclined groove 13 is delta; the inclined edge of the angle pin 2 is installed corresponding to the inclined groove 13. And the hypotenuse of the angle pin 2 passes through the axis of the rudder shaft 12.
The assembling process of the rudder deflection angle changing device comprises the following steps:
firstly, inserting the rudder shaft 12 into the model rudder shaft hole 41 for clearance fit; then inserting the angle pin 2 into the model angle pin slot 42, wherein the upper surface, the lower surface, the left surface and the right surface are in clearance fit with the model angle pin slot 42, the groove surface at the front end of the angle pin 2 passes through the axis of the rudder shaft 12, and the upper surface and the lower surface are in clearance fit with the rudder shaft angle pin slot 42; finally, the jackscrew 3 is screwed into the threaded hole of the model, and the front end face of the jackscrew 3 props against the groove face at the rear end of the angle pin, so that the accuracy of the rudder deflection angle delta is guaranteed.
The details of the present invention not described in detail in the specification are well known to those skilled in the art.
Claims (10)
1. The utility model provides a wind tunnel test model helm-changing declination device which characterized in that: the rudder comprises a rudder (1), an angle pin (2), a jackscrew (3) and a model (4); wherein the model (4) is axially and horizontally placed; the rudder (1) is vertically and fixedly installed at the top end of the model (4), and the rudder (1) vertically extends downwards into the model (4); the angle pin (2) is horizontally arranged inside the model (4), and the angle pin (2) is fixedly connected with the rudder (1) to clamp the rudder (1); the jackscrew (3) is arranged inside the model (4); the jackscrew (3) is fixedly arranged at the axial outer end of the angle pin (2); the limiting of the angle pin (2) is realized.
2. The wind tunnel test model rudder deflection angle device according to claim 1, characterized in that: a rudder shaft hole (41) and an angle pin groove (42) are formed in the side wall of the top end of the model (4); the rudder shaft hole (41) is axially arranged along the vertical direction; the angle pin slot (42) is axially arranged along the horizontal direction; and the rudder shaft hole (41) is communicated with the angle pin groove (42).
3. The wind tunnel test model rudder deflection angle device according to claim 2, characterized in that: the rudder (1) comprises a control surface (11) and a control shaft (12); wherein the control surface (11) is arranged at the top end of the model (4); the rudder shaft (12) is axially and vertically fixedly arranged at the bottom of the rudder surface (11); and the rudder shaft (12) vertically extends downwards into a rudder shaft hole (41) of the model (4).
4. The wind tunnel test model rudder deflection angle device according to claim 3, characterized in that: the rudder shaft (12) is in clearance fit with the rudder shaft hole (41); the distance between the outer wall of the rudder shaft (12) and the inner wall of the rudder shaft hole (41) is 0.01-0.03 mm.
5. The wind tunnel test model rudder deflection angle device according to claim 4, characterized in that: the angle pin (2) comprises 2 straight pins (21) and 1 inclined pin (22); the 2 straight pins (21) are symmetrically arranged in the angle pin groove (42) in parallel, and the axial direction of the straight pins (21) is parallel to the axial direction of the angle pin groove (42); 1 inclined pin column (22) is fixedly arranged among 2 straight pin columns (21); 2 straight pins (21) and 1 inclined pin (22) form an H-shaped structure.
6. The wind tunnel test model rudder deflection angle device according to claim 5, characterized in that: the inclination angle delta of the inclined pin column (22) is 0-50 degrees.
7. The wind tunnel test model rudder deflection angle device according to claim 6, characterized in that: the outer side wall of the straight pin column (21) is in clearance fit with the inner wall of the angle pin groove (42); the distance between the outer side wall of the straight pin column (21) and the inner wall of the angle pin groove (42) is 0.01-0.03 mm.
8. The wind tunnel test model rudder deflection angle device according to claim 7, characterized in that: the jackscrew (3) is embedded in a rear groove formed by the straight edges of the inclined pins (22) and the 2 straight pins (21); the jackscrew (3) is in threaded connection with the angle pin (2).
9. The wind tunnel test model rudder deflection angle device according to claim 8, characterized in that: an inclined groove (13) is formed in the position, corresponding to the angle pin groove (42), of the axial side wall of the rudder shaft (12); the inclination angle of the inclined groove (13) is delta; the bevel edge of the angle pin (2) is correspondingly arranged with the inclined groove (13).
10. The wind tunnel test model rudder deflection angle device according to claim 9, characterized in that: the bevel edge of the angle pin (2) passes through the axis of the rudder shaft (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921225722.1U CN210513615U (en) | 2019-07-31 | 2019-07-31 | Rudder deflection angle changing device for wind tunnel test model |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921225722.1U CN210513615U (en) | 2019-07-31 | 2019-07-31 | Rudder deflection angle changing device for wind tunnel test model |
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| CN210513615U true CN210513615U (en) | 2020-05-12 |
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| CN201921225722.1U Active CN210513615U (en) | 2019-07-31 | 2019-07-31 | Rudder deflection angle changing device for wind tunnel test model |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111504593A (en) * | 2020-05-26 | 2020-08-07 | 上海机电工程研究所 | Fixed frock suitable for air vane jet wind tunnel test |
| CN114001917A (en) * | 2021-11-02 | 2022-02-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for assembling and disassembling control surface angle sheet |
-
2019
- 2019-07-31 CN CN201921225722.1U patent/CN210513615U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111504593A (en) * | 2020-05-26 | 2020-08-07 | 上海机电工程研究所 | Fixed frock suitable for air vane jet wind tunnel test |
| CN114001917A (en) * | 2021-11-02 | 2022-02-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for assembling and disassembling control surface angle sheet |
| CN114001917B (en) * | 2021-11-02 | 2023-05-05 | 中国空气动力研究与发展中心超高速空气动力研究所 | Control surface angle piece assembling and disassembling method |
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