CN104512556A - Four-link opening mechanism of radar cover of airplane - Google Patents
Four-link opening mechanism of radar cover of airplane Download PDFInfo
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- CN104512556A CN104512556A CN201310460247.7A CN201310460247A CN104512556A CN 104512556 A CN104512556 A CN 104512556A CN 201310460247 A CN201310460247 A CN 201310460247A CN 104512556 A CN104512556 A CN 104512556A
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- bar shaped
- shaped
- radome
- hinged
- movable part
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Abstract
The invention belongs to the field of the design of a structure. The invention provides a four-link opening mechanism of a radar cover of an airplane. The mechanism comprises a strip-shaped fixed member, an n-shaped movable member, a strip-shaped direct connecting rod and a V-shaped bent connecting rod, wherein one end of the strip-shaped fixed member is fixed on the airplane body, and the other end of the strip-shaped fixed member is hinged to one end of the strip-shaped direct connecting rod; the other end of the strip-shaped direct connecting rod is hinged to one fork ear of the n-shaped movable member, the mounting surface of the n-shaped movable member is fixedly connected with the inner side of the radar cover, the other fork ear of the n-shaped movable member is hinged to one end of the V-shaped bent connecting rod, and the other end of the V-shaped bent connecting rod is hinged to a middle fork ear of the strip-shaped fixed member.
Description
Technical field
The invention belongs to field of structural design, relate to a kind of radome of fighter double leval jib opener.
Background technology
For keeping aerodynamic configuration, present generation aircraft boat radome opener is arranged in radome inside usually, and current main opener has chute type and Fixed hinge formula.It is good that track is opened by chute type mechanism, without interfering, and when radome is closed and fuselage fit closely, good airproof performance.But weight is large, large on airframe structure impact, and fixing poor to cover body under radome open mode.Fixed hinge formula mechanism light and stationarity is better, but because radar cover body can only rotate around fixed rotating shaft, path of motion is not good, the interference of radome and airframe structure when needing to change to eliminate unlatching to airframe structure, cannot fit tightly between radome and fuselage simultaneously, cause leak tightness to be deteriorated.
Summary of the invention
Object of the present invention: propose a kind of radome of fighter double leval jib opener, under the prerequisite of not changing airframe structure, carry out Trajectory Design by double leval jib principle, enables radome realize the breakdown action required, meets and open and close requirement.
Technical scheme of the present invention: a kind of radome of fighter double leval jib opener, comprising:
The connecting element of bar shaped, the movable part of Π shape, the straight connection rod of bar shaped, the curved rod of V-arrangement;
Connecting element one end of described bar shaped is fixed on fuselage, and straight connection rod one end of the described bar shaped connecting element other end and bar shaped is hinged; It is hinged that the straight connection rod other end of bar shaped and the movable part of Π shape one pitches ear, the attachment face of the movable part of Π shape is fixedly connected with inside radome, one end of another fork ear of the movable part of Π shape and the curved rod of V-arrangement is hinged, and the other end of the curved rod of V-arrangement is hinged on the middle part fork ear of the connecting element of bar shaped.
Advantage of the present invention: the present invention, without the need to arranging slide rail, need not change fuselage shape, can keep the integraty of airframe structure; Can not interfere collision with fuselage, track is reasonable; And volume is little, lightweight.
Accompanying drawing illustrates:
Fig. 1 is schematic diagram of the present invention.
Fig. 2 is leverage schematic diagram of the present invention.
Fig. 3 a is the motion schematic diagram one of radome of fighter double leval jib opener of the present invention.
Fig. 3 b is the motion schematic diagram two of radome of fighter double leval jib opener of the present invention.
Fig. 3 c is the motion schematic diagram three of radome of fighter double leval jib opener of the present invention.
Fig. 3 d is the motion schematic diagram four of radome of fighter double leval jib opener of the present invention.
Fig. 3 e is the motion schematic diagram five of radome of fighter double leval jib opener of the present invention.
Fig. 3 f is the motion schematic diagram six of radome of fighter double leval jib opener of the present invention.
Fig. 3 g is the motion schematic diagram seven of radome of fighter double leval jib opener of the present invention.
Fig. 4 is the overall schematic of radome of fighter double leval jib opener of the present invention.
Fig. 5 is right side mechanism connecting bridge partial enlarged drawing in Fig. 4.
Fig. 6 is left side mechanism connecting bridge partial enlarged drawing in Fig. 4.
Detailed description of the invention:
Below in conjunction with accompanying drawing, the present invention is described in further detail.
A kind of radome of fighter double leval jib opener provided by the invention, as shown in Figure 5, comprising:
The connecting element 52 of bar shaped, the movable part 54 of Π shape, the straight connection rod 53 of bar shaped, the curved rod 55 of V-arrangement;
Connecting element 52 one end fastener 56 of described bar shaped is fixed on fuselage 51, and straight connection rod 53 one end of described bar shaped connecting element 52 other end and bar shaped is hinged; It is hinged that straight connection rod 53 other end of bar shaped and the movable part 54 of Π shape one pitches ear, the attachment face (upper surface) of the movable part 54 of Π shape is fixedly connected with inside radome, one end of another fork ear of the movable part 54 of Π shape and the curved rod 55 of V-arrangement is hinged, and the other end of the curved rod 55 of V-arrangement is hinged on the middle part fork ear of the connecting element 52 of bar shaped.
Principle of work of the present invention as shown in Figure 1, 2.In FIG, 11 represent 1# leverage, and 12 represent 2# leverage, and 13 represent 3# leverage, and 14 represent 4# leverage, 1#, 2#, 3# and 4# leverage composition four-bar linkage.F represents direction and the point of action of applying power.During motion, apply power F to 2# leverage, so four-bar linkage can move according to projected path, the final condition of final arrival shown in dotted line.
In fig. 2,21 represent connecting element, and 22 deputy activity parts, 23 represent curved rod, and 24 represent straight connection rod.Wherein, 21(connecting element) 1# leverage in pie graph 1,22(movable part) 2# leverage in pie graph in 1,23(curved rod) 3# leverage in pie graph 1,24(straight connection rod) 4# leverage in pie graph 1.Linkage parameter arranges as follows:
21(1# leverage) the long 80.9mm of equivalent bar, with horizon angle 8.5 °;
22(2# leverage) the long 50.1mm of equivalent bar;
23(3# leverage) the long 70.8mm of equivalent bar, motion initial attitude and horizon angle 69 °;
24(4# leverage) the long 84mm of equivalent bar;
As shown in Fig. 3 a, Fig. 3 b, Fig. 3 c, Fig. 3 d, Fig. 3 e, Fig. 3 f, Fig. 3 g, when giving movable part 22(2# leverage) propelling thrust time, movable part can according to double leval jib principle, according to the theory locus motion designed, namely dig on the certain distance that first travels forward is backward, avoid the On/Off action realizing radome with the interference of airframe structure.
As shown in Figure 4, in order to improve kinematic accuracy and stability, the straight connection rod of the connecting element of bar shaped, the movable part of Π shape, bar shaped, the curved rod of V-arrangement are respectively two groups, and fuselage is symmetrical arranged.
In Figure 5,51 represent airframe structure, and 52 represent right connecting element, and 53 represent right straight connection rod, and 54 represent right movable part, and 55 represent right curved rod, and 56 represent fastener.
In figure 6,61 represent airframe structure, and 62 represent left connecting element, and 63 represent left straight connection rod, and 64 represent left movable part, and 65 represent left curved rod, and 66 represent fastener.
The present invention realizes the connection of radome and airframe structure by left and right Liang Zu mechanism, and the length parameters of Liang Zu mechanism, athletic posture and rotating shaft position are all completely the same, and Mei Zu mechanism all can realize separately the path of motion designed.The two parallel four-bar linkage of Liang Zu mechanism composition, can balance the load that opener is subject to, improve kinematic accuracy and stability, and fixing to cover body under improving radome opening.
The shape of the length parameters of four-bar linkage, initial motion attitude and part can be changed according to the applicable cases of different radome.
After using the present invention to be connected with airframe structure by radome, radome just according to double leval jib principle, according to the theory locus of design, can realize predetermined On/Off action.
Claims (2)
1. a radome of fighter double leval jib opener, is characterized in that, comprising:
The connecting element of bar shaped, the movable part of Π shape, the straight connection rod of bar shaped, the curved rod of V-arrangement;
Connecting element one end of described bar shaped is fixed on fuselage, and straight connection rod one end of the described bar shaped connecting element other end and bar shaped is hinged; It is hinged that the straight connection rod other end of bar shaped and the movable part of Π shape one pitches ear, the attachment face of the movable part of Π shape is fixedly connected with inside radome, one end of another fork ear of the movable part of Π shape and the curved rod of V-arrangement is hinged, and the other end of the curved rod of V-arrangement is hinged on the middle part fork ear of the connecting element of bar shaped.
2. a kind of radome of fighter double leval jib opener as claimed in claim 1, is characterized in that, the straight connection rod of the connecting element of bar shaped, the movable part of Π shape, bar shaped, the curved rod of V-arrangement are respectively two groups, are symmetrical arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460247.7A CN104512556A (en) | 2013-09-30 | 2013-09-30 | Four-link opening mechanism of radar cover of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460247.7A CN104512556A (en) | 2013-09-30 | 2013-09-30 | Four-link opening mechanism of radar cover of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104512556A true CN104512556A (en) | 2015-04-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310460247.7A Pending CN104512556A (en) | 2013-09-30 | 2013-09-30 | Four-link opening mechanism of radar cover of airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN104512556A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143871A (en) * | 2016-07-09 | 2016-11-23 | 精功（绍兴）复合材料有限公司 | A kind of radome of fighter double leval jib opener |
| CN109131916A (en) * | 2018-09-13 | 2019-01-04 | 吉林省翼启飞科技有限公司 | A kind of unmanned plane fast insert-pull carry platform |
| CN111645872A (en) * | 2020-05-11 | 2020-09-11 | 四川沃洛佳科技有限公司 | Fixing device for airborne radar of unmanned aerial vehicle and using method |
| RU215413U1 (en) * | 2022-09-26 | 2022-12-12 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | AIRCRAFT NOSE FAIRING |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2943756A (en) * | 1956-05-24 | 1960-07-05 | Gen Dynamics Corp | Hinge structure |
| DE1481684A1 (en) * | 1966-05-13 | 1969-03-20 | Ver Flugtechnische Werke | Device for folding down a protective covering for an aircraft device |
| US6796529B1 (en) * | 2003-07-08 | 2004-09-28 | Avibank.Mfg., Inc. | Aircraft strut |
| US20070045467A1 (en) * | 2004-06-29 | 2007-03-01 | Airbus France | Device and method for fastening an aircraft radome |
| WO2013001224A1 (en) * | 2011-06-27 | 2013-01-03 | Airbus Operations Sas | Method of opening a protective dome, in particular a radome, and radome equipped with a pantograph for implementation thereof |
-
2013
- 2013-09-30 CN CN201310460247.7A patent/CN104512556A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2943756A (en) * | 1956-05-24 | 1960-07-05 | Gen Dynamics Corp | Hinge structure |
| DE1481684A1 (en) * | 1966-05-13 | 1969-03-20 | Ver Flugtechnische Werke | Device for folding down a protective covering for an aircraft device |
| US6796529B1 (en) * | 2003-07-08 | 2004-09-28 | Avibank.Mfg., Inc. | Aircraft strut |
| US20070045467A1 (en) * | 2004-06-29 | 2007-03-01 | Airbus France | Device and method for fastening an aircraft radome |
| WO2013001224A1 (en) * | 2011-06-27 | 2013-01-03 | Airbus Operations Sas | Method of opening a protective dome, in particular a radome, and radome equipped with a pantograph for implementation thereof |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143871A (en) * | 2016-07-09 | 2016-11-23 | 精功（绍兴）复合材料有限公司 | A kind of radome of fighter double leval jib opener |
| CN109131916A (en) * | 2018-09-13 | 2019-01-04 | 吉林省翼启飞科技有限公司 | A kind of unmanned plane fast insert-pull carry platform |
| CN109131916B (en) * | 2018-09-13 | 2024-05-10 | 吉林省翼启飞科技有限公司 | Quick plug mounting platform of unmanned aerial vehicle |
| CN111645872A (en) * | 2020-05-11 | 2020-09-11 | 四川沃洛佳科技有限公司 | Fixing device for airborne radar of unmanned aerial vehicle and using method |
| RU215413U1 (en) * | 2022-09-26 | 2022-12-12 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | AIRCRAFT NOSE FAIRING |
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Application publication date: 20150415 |