CN112623185A - Radome bracket with control surface - Google Patents
Radome bracket with control surface Download PDFInfo
- Publication number
- CN112623185A CN112623185A CN202011599228.9A CN202011599228A CN112623185A CN 112623185 A CN112623185 A CN 112623185A CN 202011599228 A CN202011599228 A CN 202011599228A CN 112623185 A CN112623185 A CN 112623185A
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- CN
- China
- Prior art keywords
- bracket
- control surface
- radome
- support
- rear edge
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000005406 washing Methods 0.000 claims abstract description 7
- 230000000903 blocking effect Effects 0.000 abstract description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
The invention belongs to the technical field of radars for airplanes, and discloses a radome bracket with a control surface, which is arranged on the back of a machine body and used for supporting a radome on an airplane, wherein the radome bracket with the control surface at least comprises a landing leg, and the landing leg comprises: a fixed bracket 1; a bracket trailing edge control surface 2; the trailing edge control surface of the bracket is arranged at the trailing edge of the fixed bracket. The side washing and blocking of the radar support of the early warning machine to the vertical fin can be effectively reduced, the course stability of the airplane is improved, meanwhile, the flight resistance of the airplane under the sideslip condition can be reduced, and the performance of the airplane is improved.
Description
Technical Field
The invention belongs to the technical field of radars for airplanes, and particularly relates to a radome bracket with a control surface.
Background
In the existing early warning machine, a fixed bracket is usually adopted to support the radome. Although the appearance and the installation position of the bracket are both optimally designed, in the actual flight of the airplane, the side washing and blocking effects of the radome body bracket on the vertical fin reduce the vertical fin efficiency and obviously reduce the course stability of the airplane.
The existing solutions of the early warning machine include the following: the aircraft flight control system is improved, but the improvement degree is limited, and the aircraft flight control system is generally used under the condition of early warning of high course stability of an airborne aircraft body; pneumatic measures such as adding small vertical tails on ventral fins, a horizontal tail end plate and a horizontal tail are added, the weight and the pneumatic resistance of the airplane are increased, and the performance of the airplane is reduced.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a radome bracket with a control surface, which can effectively reduce side wash and drag of the radome bracket of the early warning machine on a vertical fin, improve course stability of an aircraft, and simultaneously reduce flight resistance of the aircraft under a sideslip condition, and improve performance of the aircraft.
In order to achieve the purpose, the invention is realized by adopting the following technical scheme.
A radome support with a control surface for supporting a radome on an aircraft, the radome support with a control surface comprising at least one leg, the leg comprising: a fixed bracket 1; a bracket trailing edge control surface 2;
the trailing edge control surface of the bracket is arranged at the trailing edge of the fixed bracket.
The technical scheme of the invention has the characteristics and further improvements that:
(1) the radome bracket with the control surface further comprises:
the front edge control surface of the bracket is arranged on the front edge of the fixed bracket, the front edge control surface of the bracket is connected with the rear edge control surface of the bracket in a follow-up manner and swings along with the rear edge control surface of the bracket, and the follow-up mechanism is a link mechanism or a worm and gear mechanism.
(2) When the radome bracket with the control surface comprises two support legs, the two support legs are arranged at a preset angle.
(3) The radome bracket with the control surface further comprises: a controller for controlling the operation of the electronic device,
when the radome bracket with the control surface only comprises: when the trailing edge of the bracket is in the rudder surface, the controller is used for controlling the deflection of the trailing edge rudder surface of the bracket;
when the radome bracket with the control surface comprises: when the support front edge control surface and the support rear edge control surface are arranged, the controller is used for respectively controlling the deflection of the support front edge control surface and the support rear edge control surface;
when the radome bracket with the control surface comprises: and when the support front edge control surface and the support rear edge control surface are connected through the follow-up mechanism, the controller is used for controlling the deflection of the support rear edge control surface, and the support front edge control surface swings along with the support rear edge control surface.
(4) And certain gaps are reserved at the upper end and the lower end of the fixed support 1 respectively, so that the deflection of the front edge control surface and the rear edge control surface of the support does not interfere with other components.
(5) The control surface of the rear edge of the bracket is arranged on the rear edge of the fixed bracket through a link mechanism or a worm gear;
the control surface of the front edge of the bracket is arranged on the front edge of the fixed bracket through a link mechanism or a worm gear.
(6) When an included angle exists between the incoming flow and the aircraft course, the trailing edge control surface of the support deflects under the action of aerodynamic force, and the tail of the trailing edge control surface of the support generates a deflection trend which points to the direction parallel to the incoming flow. Therefore, the side washing of the vertical fin by the support is reduced, and the course stability of the airplane is improved.
(7) When an included angle exists between an incoming flow and the aircraft course, the control surface at the rear edge of the support deflects under the action of aerodynamic force, the tail part of the control surface at the rear edge of the support generates a deflection trend pointing to the direction opposite to the incoming flow, and the head part of the control surface at the front edge of the support generates a deflection trend pointing to the direction parallel to the incoming flow along with the control surface at the rear edge of the support through a follower mechanism.
The invention can effectively reduce the side washing and the blocking of the radar bracket of the early warning machine to the vertical fin, improve the course stability of the airplane, and simultaneously can reduce the flight resistance of the airplane under the sideslip condition and improve the performance of the airplane. The electric and hydraulic pipelines leading from the airplane body to the radar cover body can pass through the wing box part of the fixed support, and the space of the part is equivalent to that of a conventional support, so the engineering realizability of the invention is higher.
Drawings
Fig. 1 is a schematic structural diagram of a radome with a control surface according to an embodiment of the present invention;
wherein, 1-fixing the bracket; 2-a bracket trailing edge control surface; 3-trailing edge control surface separation surface; 4-a fixed support wing box portion; 5-leading edge separation plane; 6-support front edge control surface; 7-aircraft nose; 8-aircraft wings; 9-rear fuselage of the aircraft.
Detailed Description
The embodiment of the invention provides a radome bracket with a control surface, which is arranged on the back of a fuselage and used for supporting a radome on an airplane, as shown in fig. 1, the radome bracket with the control surface at least comprises a supporting leg, and the supporting leg comprises: a fixed bracket 1; a bracket trailing edge control surface 2;
the trailing edge control surface of the bracket is arranged at the trailing edge of the fixed bracket.
Further:
(1) the radome bracket with the control surface further comprises:
the front edge control surface of the bracket is arranged on the front edge of the fixed bracket, the front edge control surface of the bracket is connected with the rear edge control surface of the bracket in a follow-up manner and swings along with the rear edge control surface of the bracket, and the follow-up mechanism is a link mechanism or a worm and gear mechanism.
(2) When the radome bracket with the control surface comprises two support legs, the two support legs are arranged at a preset angle.
(3) The radome bracket with the control surface further comprises: a controller for controlling the operation of the electronic device,
when the radome bracket with the control surface only comprises: when the trailing edge of the bracket is in the rudder surface, the controller is used for controlling the deflection of the trailing edge rudder surface of the bracket;
when the radome bracket with the control surface comprises: when the support front edge control surface and the support rear edge control surface are arranged, the controller is used for respectively controlling the deflection of the support front edge control surface and the support rear edge control surface;
when the radome bracket with the control surface comprises: and when the support front edge control surface and the support rear edge control surface are connected through the follow-up mechanism, the controller is used for controlling the deflection of the support rear edge control surface, and the support front edge control surface swings along with the support rear edge control surface.
(4) And certain gaps are reserved at the upper end and the lower end of the fixed support 1 respectively, so that the deflection of the front edge control surface and the rear edge control surface of the support does not interfere with other components.
(5) The control surface of the rear edge of the bracket is arranged on the rear edge of the fixed bracket through a link mechanism or a worm gear;
the control surface of the front edge of the bracket is arranged on the front edge of the fixed bracket through a link mechanism or a worm gear.
(6) When an included angle exists between the incoming flow and the aircraft course, the trailing edge control surface of the support deflects under the action of aerodynamic force, and the tail of the trailing edge control surface of the support generates a deflection trend which points to the direction parallel to the incoming flow. Therefore, the side washing of the vertical fin by the support is reduced, and the course stability of the airplane is improved.
(7) When an included angle exists between an incoming flow and the aircraft course, the control surface at the rear edge of the support deflects under the action of aerodynamic force, the tail part of the control surface at the rear edge of the support generates a deflection trend pointing to the direction opposite to the incoming flow, and the head part of the control surface at the front edge of the support generates a deflection trend pointing to the direction parallel to the incoming flow along with the control surface at the rear edge of the support through a follower mechanism.
The invention can effectively reduce the side washing and the blocking of the radar bracket of the early warning machine to the vertical fin, improve the course stability of the airplane, and simultaneously can reduce the flight resistance of the airplane under the sideslip condition and improve the performance of the airplane. The electric and hydraulic pipelines leading from the airplane body to the radar cover body can pass through the wing box part of the fixed support, and the space of the part is equivalent to that of a conventional support, so the engineering realizability of the invention is higher.
Claims (8)
1. A radome bracket with a control surface, which is installed on the back of a fuselage and is used for supporting a radome on an airplane, characterized in that the radome bracket with the control surface at least comprises a landing leg, and the landing leg comprises: a fixed bracket (1); a bracket trailing edge control surface (2);
the trailing edge control surface of the bracket is arranged at the trailing edge of the fixed bracket.
2. A control surface radome bracket of claim 1 further comprising:
the support front edge control surface (6) is arranged on the front edge of the fixed support and is in follow-up connection with the support rear edge control surface and swings along with the support rear edge control surface, and the follow-up mechanism is a link mechanism or a worm and gear mechanism.
3. A rudder surface radome bracket according to claim 1 wherein when the rudder surface radome bracket includes two legs, the two legs are arranged at a predetermined angle.
4. A control surface radome bracket of claim 1 further comprising: a controller for controlling the operation of the electronic device,
when the radome bracket with the control surface only comprises: when the trailing edge of the bracket is in the rudder surface, the controller is used for controlling the deflection of the trailing edge rudder surface of the bracket;
when the radome bracket with the control surface comprises: when the support front edge control surface and the support rear edge control surface are arranged, the controller is used for respectively controlling the deflection of the support front edge control surface and the support rear edge control surface;
when the radome bracket with the control surface comprises: and when the support front edge control surface and the support rear edge control surface are connected through the follow-up mechanism, the controller is used for controlling the deflection of the support rear edge control surface, and the support front edge control surface swings along with the support rear edge control surface.
5. Radome bracket with control surfaces according to claim 2, wherein gaps are reserved at the upper end and the lower end of the fixing bracket (1) respectively, so that the deflection of the control surfaces of the front edge and the rear edge of the bracket does not interfere with other components.
6. A radome bracket with a control surface according to claim 2 wherein the radome bracket is a radome body,
the control surface of the rear edge of the bracket is arranged on the rear edge of the fixed bracket through a link mechanism or a worm gear;
the control surface of the front edge of the bracket is arranged on the front edge of the fixed bracket through a link mechanism or a worm gear.
7. The radome bracket of claim 1 wherein the trailing edge control surface of the bracket is deflected pneumatically when the incoming flow forms an angle with the aircraft heading, and the tail of the trailing edge control surface of the bracket is deflected in a direction parallel to the incoming flow. Therefore, the side washing of the vertical fin by the support is reduced, and the course stability of the airplane is improved.
8. The radome bracket with the control surfaces as claimed in claim 2, wherein when the incoming flow forms an angle with the aircraft heading, the control surfaces on the rear edge of the bracket deflect under the action of aerodynamic force, the tail part of the control surfaces on the rear edge of the bracket generates a deflection trend pointing to the opposite direction of the incoming flow, and the head part of the control surfaces on the front edge of the bracket follows the control surfaces on the rear edge of the bracket through a follower mechanism to generate a deflection trend pointing to the direction parallel to the incoming flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011599228.9A CN112623185A (en) | 2020-12-29 | 2020-12-29 | Radome bracket with control surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011599228.9A CN112623185A (en) | 2020-12-29 | 2020-12-29 | Radome bracket with control surface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112623185A true CN112623185A (en) | 2021-04-09 |
Family
ID=75287612
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011599228.9A Pending CN112623185A (en) | 2020-12-29 | 2020-12-29 | Radome bracket with control surface |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112623185A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU781981B1 (en) * | 2000-11-20 | 2005-06-23 | Bae Systems Plc | Aircraft sensor window |
| CN103466074A (en) * | 2013-09-24 | 2013-12-25 | 中国航天空气动力技术研究院 | Ship-based net collision recovery unmanned aerial vehicle |
| CN105000193A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Follow-up radome bracket and follow-up radar with same as well as aircraft |
| CN106904273A (en) * | 2017-01-26 | 2017-06-30 | 龙川 | Sailing boat seaplane |
| CN107109947A (en) * | 2014-10-10 | 2017-08-29 | 赛峰飞机发动机公司 | The stator of aircraft turbine engine |
-
2020
- 2020-12-29 CN CN202011599228.9A patent/CN112623185A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU781981B1 (en) * | 2000-11-20 | 2005-06-23 | Bae Systems Plc | Aircraft sensor window |
| CN103466074A (en) * | 2013-09-24 | 2013-12-25 | 中国航天空气动力技术研究院 | Ship-based net collision recovery unmanned aerial vehicle |
| CN107109947A (en) * | 2014-10-10 | 2017-08-29 | 赛峰飞机发动机公司 | The stator of aircraft turbine engine |
| CN105000193A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Follow-up radome bracket and follow-up radar with same as well as aircraft |
| CN106904273A (en) * | 2017-01-26 | 2017-06-30 | 龙川 | Sailing boat seaplane |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210409 |
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| RJ01 | Rejection of invention patent application after publication |