CN105000193A - Follow-up radome bracket and follow-up radar with same as well as aircraft - Google Patents
Follow-up radome bracket and follow-up radar with same as well as aircraft Download PDFInfo
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- CN105000193A CN105000193A CN201510349329.3A CN201510349329A CN105000193A CN 105000193 A CN105000193 A CN 105000193A CN 201510349329 A CN201510349329 A CN 201510349329A CN 105000193 A CN105000193 A CN 105000193A
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- radome
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- 238000000034 method Methods 0.000 abstract description 8
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- 238000009434 installation Methods 0.000 description 1
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- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The invention discloses a follow-up radome bracket and a follow-up radar with the same as well as an aircraft. The follow-up radome bracket comprises a fixed shaft and a fairing, wherein the fixed shaft is fixedly arranged on a body of the aircraft; the fairing is arranged on the aircraft and sleeves the fixed shaft; and the fairing can rotate around the fixed shaft, wherein in the flight process of the aircraft, the fairing is impacted by an air stream moving relative to the aircraft so that the fairing rotates with the direction of the air stream. The follow-up radome bracket disclosed by the invention is advantaged in that the fairing is impacted by the air stream moving relative to the aircraft in the flight process of the aircraft so that the fairing rotates with the direction of the air stream; therefore, the contacting area between the fairing and the air stream is always minimum. The interference of the follow-up radome bracket to the aircraft in the flight process of the aircraft is reduced so that the direction stability of the aircraft is improved and the resistance of the follow-up radome bracket to the aircraft in the flight process of the aircraft is reduced.
Description
Technical Field
The invention relates to the technical field of radars for airplanes, in particular to a follow-up radar cover bracket for supporting a radar cover on an airplane, a follow-up radar with the same and an airplane.
Background
In existing aircraft, a fixed support is typically used to support the radome. Although the appearance and the installation position of the support are optimally designed, in the actual flight of the airplane, due to the turbulent flow relationship in the air, the support has larger influence on the empennage of the airplane when receiving the air turbulent flow, and the course stability of the airplane is obviously reduced.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a compliant radome mount which overcomes or at least mitigates at least one of the above-mentioned disadvantages of the prior art.
To achieve the above object, the present invention provides a servo radome bracket for supporting a radome on an aircraft. The servo radome bracket includes: a stationary shaft for fixed disposition to a fuselage of the aircraft; the fairing is arranged on the airplane and sleeved on the fixed shaft, and can relatively rotate around the fixed shaft; wherein, during flight of the aircraft, an airflow moving relative to the aircraft impacts the fairing, causing the fairing to rotate with the airflow direction.
Preferably, one end of the fixed shaft is fixedly connected with the airplane, and the other end of the fixed shaft is fixedly connected with a radome of the airplane and used for supporting the radome.
Preferably, the stationary shaft is hollow and the connection lines for connecting the aircraft to the radome pass through the stationary shaft to be connected to each other.
Preferably, the fairing comprises two interconnected faces, the fixed axis being arranged at the maximum distance between the two faces of the fairing.
Preferably, the fairing is shaped to minimise the force-bearing area of the fairing when an airflow moving relative to the aircraft impacts the sideslip angle envelope of the fairing.
Preferably, the fairing includes a fixed portion fixedly connected to the fuselage of the aircraft and a rotating portion relatively rotatable about the rotation axis.
Preferably, the dimension of the fixed portion in the axial direction of the fixed shaft is such as to prevent the rotating portion and the aircraft from interfering with each other when the rotating portion rotates relative to the fixed shaft.
The invention also provides a follow-up radar which comprises a follow-up radome and is characterized in that the follow-up radar further comprises the follow-up radome bracket.
Preferably, the servo radar comprises two servo radome brackets, and the two servo radome brackets are arranged oppositely and support the servo radome together.
The invention also provides an aircraft comprising a follow-up radar as described above.
According to the servo radome bracket, the cowling can relatively rotate around the rotating shaft; during flight of the aircraft, the air flow moving relative to the aircraft impacts the fairing, causing the fairing to rotate with the direction of said air flow, thereby causing the contact area of the fairing with the direction of the air flow to be always minimal. The interference of the follow-up radome bracket to the airplane in the airplane flying process is reduced, the course stability of the airplane is improved, and the resistance of the follow-up radome bracket to the airplane in the airplane flying process is reduced.
Drawings
Fig. 1 is a schematic structural view of a servo radome bracket according to an embodiment of the invention, which is mounted on an airplane.
Fig. 2 is another schematic view of the structure of the servo radome of fig. 1.
Reference numerals:
| 1 | fairing | 12 | Rotating part |
| 2 | Fixed shaft | 4 | Radar cover |
| 3 | Aircraft with a flight control device | ||
| 11 | Fixing part |
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
The invention discloses a follow-up radome bracket, which is used for supporting a radome on an airplane and comprises a fixed shaft and a fairing, wherein the fixed shaft is fixedly arranged on a fuselage of the airplane; the fairing is arranged on the airplane and sleeved on the rotating shaft, and can rotate around the rotating shaft relatively. Wherein, during flight of the aircraft, an airflow moving relative to the aircraft impacts the fairing, causing the fairing to rotate with said airflow direction, thereby aligning the leading edge of the fairing with the airflow direction, even if the force-bearing area of the fairing is minimal.
According to the servo radome bracket, the cowling can relatively rotate around the rotating shaft; during flight of the aircraft, the air flow moving relative to the aircraft impacts the fairing, causing the fairing to rotate with the direction of said air flow, thereby causing the contact area of the fairing with the direction of the air flow to be always minimal. The interference of the follow-up radome bracket to the airplane in the airplane flying process is reduced, the course stability of the airplane is improved, and the resistance of the follow-up radome bracket to the airplane in the airplane flying process is reduced.
Fig. 1 is a schematic structural view of a servo radome bracket according to an embodiment of the invention, which is mounted on an airplane. Fig. 2 is another schematic view of the structure of the servo radome of fig. 1.
Usually, the radar on the airplane is arranged on the tail wing part of the airplane, and the radar comprises a radar cover and a radar component inside the radar cover.
The follow-up radome bracket shown in fig. 1 comprises a fixed shaft 2 and a radome 1.
Referring to fig. 1 and 2, the stationary shaft 2 is for being fixedly disposed to a fuselage of an aircraft 3. Specifically, one end of the fixed shaft 2 is fixedly arranged on the airplane 3, and the other end is used for being connected with the radome 4 and supporting the radome 4.
In the present embodiment, the stationary shaft 2 is hollow in the middle, and the connection lines for connecting the aircraft 3 to the radome 4 are connected to each other after passing through the hollow interior of the stationary shaft 2.
It will be appreciated that the stationary shaft 2 is intended to support the radome 4 and therefore should be of a strength to at least carry the load of the radome 4.
It will be appreciated that in an alternative embodiment, the stationary shaft is a solid shaft to increase the strength of the stationary shaft. The connection of the radome 4 to the aircraft 3 is routed externally.
Referring to fig. 1 and fig. 2, in the present embodiment, the fairing 1 is disposed on the aircraft 3 and sleeved on the fixed shaft 2, and the fairing 1 can relatively rotate around the fixed shaft 2. Specifically, in the present embodiment, the cowling 1 has inside it a housing portion housing the fixed shaft 2, the fixed shaft 2 being mounted inside the housing portion inside the cowling 1. During flight of the aircraft, the air flow moving relative to the aircraft impacts the fairing 1, causing the fairing 1 to rotate with the direction of the air flow.
Referring to fig. 2, in the present embodiment, the fairing 1 includes a fixed portion 11 and a rotating portion 12, the fixed portion 11 is fixedly connected to the fuselage of the aircraft 4, and the rotating portion 12 is relatively rotatable about the rotating shaft 2. And the dimension of the fixed part 11 in the axial direction of the fixed shaft 2 is such as to prevent the rotating part 12 from interfering with the aircraft when the rotating part 12 rotates relative to the fixed shaft 2.
With this configuration, the portion of the cowl 1 that contacts the aircraft 3 can be set so as to be fixed to the aircraft 3 without rotating relative to the aircraft 3, and interference between the cowl 1 and the aircraft 3 when the cowl 1 rotates relative to the rotary shaft 2 is prevented.
Referring to fig. 2, the fairing 1 comprises two interconnected faces, and the stationary shaft 2 is arranged at the maximum distance between the two faces of the fairing 1, with the center of compression of the fairing 1 behind the stationary shaft 2 (in the figure in a direction into the plane of the paper). Specifically, the accommodating portion of the cowl 1 described above is provided at a position where the thickness of the cowl 1 is the largest in the nose-to-tail direction of the aircraft of the entire cowl 1, and the position is located at the middle of the cowl 1 in the direction. Thus, when the fairing 1 rotates, the portions on either side of this central portion are substantially equal in volume and symmetrical to each other.
Referring to fig. 2, in the present embodiment, the shape of the fairing 1 is such that the force-bearing area of the fairing 1 is minimised when an airflow moving relative to the aircraft impacts the sideslip angle wrap of the fairing 1. Specifically, the fairing 1 itself has a streamline shape, and when the incoming flow has a sideslip angle β with the body axis of the aircraft, the fairing 1 is behind the fixed shaft 2 due to the pressure center, and the head of the fairing 1 is deviated to the incoming flow direction.
The invention also provides a follow-up radar which comprises a follow-up radome and further comprises the follow-up radome bracket. It will be appreciated that the size of the compliant radar cover will depend on the aircraft design requirements. One or more compliant radome mounts may be provided. Referring to fig. 2, in this embodiment, the following radar includes two following radome brackets, and the two following radome brackets are disposed opposite to each other, and support the following radome together.
The invention also provides an aircraft comprising a follow-up radar as described above.
Advantageously, the aircraft is a pre-warning aircraft.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A follow-up radome mount for supporting a radome on an aircraft, the follow-up radome mount comprising:
a fixed shaft (2) for fixed arrangement to a fuselage of the aircraft (3);
the fairing (1) is arranged on the airplane and sleeved on the fixed shaft (2), and the fairing (1) can rotate around the fixed shaft (2) relatively; wherein,
during the flight of the aircraft, the air flow moving relative to the aircraft impacts the fairing (1), causing the fairing (1) to rotate with the direction of the air flow.
2. A servo radome bracket according to claim 1, wherein one end of the stationary shaft (2) is fixedly connected to the aircraft (3) and the other end of the stationary shaft (2) is fixedly connected to the radome (4) of the aircraft for supporting the radome (4).
3. A servo radome holder according to claim 2, wherein the stationary shaft (2) is hollow, and connecting lines for connecting the aircraft to the radome pass through the stationary shaft (2) for mutual connection.
4. The servo radome bracket of claim 3 wherein the radome (1) comprises two faces connected to each other, the stationary shaft (2) being arranged at the maximum distance between the two faces of the radome (1).
5. The compliant radome bracket of claim 4 wherein the shape of the fairing (1) is such that the force-bearing area of the fairing (1) is minimised when an airflow moving relative to the aircraft impacts the sideslip angle envelope of the fairing (1).
6. The servo radome bracket of claim 1 wherein the fairing (1) comprises a stationary part (11) and a rotating part (12), the stationary part (11) being fixedly connected to the fuselage of the aircraft (4), the rotating part (12) being relatively rotatable about the axis of rotation (2).
7. The servo radar cover holder according to claim 6, wherein the stationary part (11) has a dimension in the axial direction of the stationary shaft (2) such that the rotating part (12) is prevented from interfering with the aircraft when the rotating part (12) is rotated relative to the stationary shaft (2).
8. A follow-up radar comprising a follow-up radome, characterized in that the follow-up radar further comprises a follow-up radome bracket according to any one of claims 1 to 7.
9. The follow-up radar according to claim 8, wherein the follow-up radar comprises two follow-up radome brackets, and the two follow-up radome brackets are oppositely arranged and jointly support the follow-up radome.
10. An aircraft, characterized in that it comprises a radar according to any one of claims 8 or 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510349329.3A CN105000193B (en) | 2015-06-23 | 2015-06-23 | A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510349329.3A CN105000193B (en) | 2015-06-23 | 2015-06-23 | A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105000193A true CN105000193A (en) | 2015-10-28 |
| CN105000193B CN105000193B (en) | 2017-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510349329.3A Active CN105000193B (en) | 2015-06-23 | 2015-06-23 | A kind of servo-actuated radar cover stent and the servo-actuated radar with which and aircraft |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379510A (en) * | 2016-09-29 | 2017-02-08 | 华东电子工程研究所（中国电子科技集团公司第三十八研究所） | Load structure integrated sensor flight vehicle |
| CN106628109A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Rotating and connecting structure of aircraft radome |
| CN107477096A (en) * | 2017-09-30 | 2017-12-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of large-scale rotary body and the attachment structure of rotating shaft |
| CN108045554A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of turbofan twin vertical fin early warning plane |
| CN109558691A (en) * | 2018-12-14 | 2019-04-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of shock resistance design method of airborne equipment bracket |
| CN109665112A (en) * | 2019-01-31 | 2019-04-23 | 江苏恒铭达航空设备有限公司 | Helicopter electronic self-defence component mounting bracket and helicopter |
| CN112623185A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Radome bracket with control surface |
| CN112896544A (en) * | 2021-02-04 | 2021-06-04 | 浙江大学 | A placer outside frame for aircraft cover support soon |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106379510A (en) * | 2016-09-29 | 2017-02-08 | 华东电子工程研究所（中国电子科技集团公司第三十八研究所） | Load structure integrated sensor flight vehicle |
| CN106628109A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Rotating and connecting structure of aircraft radome |
| CN107477096A (en) * | 2017-09-30 | 2017-12-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of large-scale rotary body and the attachment structure of rotating shaft |
| CN108045554A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of turbofan twin vertical fin early warning plane |
| CN109558691A (en) * | 2018-12-14 | 2019-04-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of shock resistance design method of airborne equipment bracket |
| CN109665112A (en) * | 2019-01-31 | 2019-04-23 | 江苏恒铭达航空设备有限公司 | Helicopter electronic self-defence component mounting bracket and helicopter |
| CN112623185A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Radome bracket with control surface |
| CN112896544A (en) * | 2021-02-04 | 2021-06-04 | 浙江大学 | A placer outside frame for aircraft cover support soon |
| CN112896544B (en) * | 2021-02-04 | 2022-11-15 | 浙江大学 | A placer outside frame for aircraft cover support soon |
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| Publication number | Publication date |
|---|---|
| CN105000193B (en) | 2017-03-08 |
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