CN104743131A - Airborne meter-wave radar transmitting antenna midair folding and unfolding mechanism - Google Patents
Airborne meter-wave radar transmitting antenna midair folding and unfolding mechanism Download PDFInfo
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- CN104743131A CN104743131A CN201510173598.9A CN201510173598A CN104743131A CN 104743131 A CN104743131 A CN 104743131A CN 201510173598 A CN201510173598 A CN 201510173598A CN 104743131 A CN104743131 A CN 104743131A
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Abstract
The invention relates to the technical field of radar installation, in particular to an airborne meter-wave radar transmitting antenna midair folding and unfolding mechanism which can fold and unfold a meter-wave radar transmitting antenna in the flying process of an aircraft. The folding and unfolding mechanism is mounted on an aircraft wing, a triangular support is hinged onto the wing through a first vertex, a first actuating cylinder and the support are positioned in the same plane, one end of the first actuating cylinder is hinged to the wing, the other end of the first actuating cylinder is hinged to a third vertex of the support, a connecting rod and the support are positioned in the same plane, one end of the connecting rod is hinged to a second vertex of the support, the other end of the connecting rod is fixedly connected with the transmitting antenna, a second actuating cylinder and the support are positioned in the same plane, one end of the second actuating cylinder is hinged onto a beam between the first vertex and the second vertex, and the other end of the second actuating cylinder is hinged to the connecting rod. The airborne meter-wave radar transmitting antenna midair folding and unfolding mechanism can drive the support and the transmitting antenna to rotate through the first actuating cylinder, so that the meter-wave radar transmitting antenna in the flying process of the aircraft is folded and unfolded.
Description
Technical field
The present invention relates to radar field engineering field, relate to the aerial jack of a kind of airborne meter wave radar emitting antenna.
Background technology
At present, a lot of aircraft is provided with airborne meter wave radar, and airborne meter wave radar emitting antenna is arranged on central wing outer rim usually, be located substantially on bottom wing, and require that emitting antenna will possess draw-in and draw-off function, to open when needs, all the other time pack up, reduce on flight impact.And emitting antenna has usually, and diameter is large, quality feature heavily, and need to bear huge air resistance aloft; For diameter be 4.8 meters, weight 80 emitting antenna that is kilogram, when it puts down in the air, maximum air resistance reaches 400 kilograms.Therefore, needing to design a kind of emitting antenna jack is arranged on wing by emitting antenna, to realize the draw-in and draw-off function of emitting antenna in aircraft flight.
Summary of the invention
The object of the present invention is to provide the aerial jack of a kind of airborne meter wave radar emitting antenna, the folding and unfolding of meter wave radar emitting antenna can be realized in aircraft flight.
The aerial jack of one provided by the invention airborne meter wave radar emitting antenna, is arranged on aircraft wing, comprises:
Leg-of-mutton support, described support is hinged on described wing by the first summit;
First pressurized strut, is positioned at same plane with described support, and one end of described first pressurized strut is with to state wing hinged, and the 3rd summit of the other end and described support is hinged;
Pipe link, is positioned at same plane with described support, one end of described pipe link and the second summit of described support hinged, the other end is fixedly connected with described emitting antenna;
Second pressurized strut, is positioned at same plane with described support, and one end of described second pressurized strut is hinged on the crossbeam between the first summit of described support and the second summit, the other end and described pipe link hinged.
Alternatively, described aerial jack also comprises:
First sleeve, is fixedly installed on the first summit place of described support, and the axes normal of described first sleeve is in described support place plane;
Rotating shaft, two ends and described wing are fixed, and described first sleeve rotates and is arranged in described rotating shaft.
Alternatively, described aerial jack also comprises:
Second sleeve, is fixedly installed on described support, and the axes normal of described second sleeve is in described support place plane;
3rd sleeve, identical with described second sleeve-shaped, be fixedly installed on described support, the axes normal of described 3rd sleeve is in described support place plane, wherein, described first sleeve, the second sleeve and the distribution triangular in shape of the 3rd sleeve, and described second sleeve axis equals the distance of described 3rd sleeve axis to described first sleeve axis to the distance of described first sleeve axis;
Lock pin, external diameter is not more than the internal diameter of described second sleeve, described lock pin is positioned at described side face, and axes normal is in described support place plane, and described lock pin axis equals the distance of described second sleeve axis to described first sleeve axis to the distance of described first sleeve axis;
Locking pressurized strut, one end is fixed on described wing, and the other end is connected with described lock pin, stretches for driving described lock pin.
Alternatively, described lock pin comprises the first lock pin and the second lock pin, is symmetricly set on described support both sides;
Described locking pressurized strut comprises the first locking pressurized strut and the second locking pressurized strut, is symmetricly set on described support both sides, and described first locking pressurized strut is connected with described first lock pin, and described second locking pressurized strut is connected with described second lock pin.
Alternatively, described aerial jack also comprises:
Strut bar, is arranged on described side face, and one end and the described wing of described strut bar are hinged, and the other end is hinged on the crossbeam between the first summit of described support and the second summit.
Alternatively, described strut bar comprises two, is symmetricly set on described support both sides, and described two strut bars are identical with the position of articulating point of described crossbeam.
Beneficial effect of the present invention:
In the aerial jack of airborne meter wave radar emitting antenna provided by the invention, first summit of triangular supports is hinged on wing, second summit place connects emitting antenna by pipe link, while making holder pivots, drive emitting antenna to rotate, simultaneously, also be hinged with the first pressurized strut at the 3rd summit place of support, power can be provided for the rotation of support, thus realize the folding and unfolding of meter wave radar emitting antenna in aircraft flight.
Accompanying drawing explanation
Fig. 1 is the structural representation of the aerial jack of the present invention's airborne meter wave radar emitting antenna;
Fig. 2 is the structural representation in the aerial jack of the present invention's airborne meter wave radar emitting antenna with locking pressurized strut;
Fig. 3 is the structural representation in the aerial jack of the present invention's airborne meter wave radar emitting antenna with strut bar.
Detailed description of the invention
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.
As shown in Figure 1 to Figure 3, the aerial jack of airborne meter wave radar emitting antenna of the present invention, is arranged on aircraft wing, comprises the parts such as support 1, first pressurized strut 2.
Particularly, support 1 is triangular in shape, has the first summit, the second summit and the 3rd summit; And support 1 is hinged on wing (central wing outer rim place) by the first summit 11.Wherein, the first summit 11 of support 1 can adopt multiple applicable mode hinged, the such as mode such as bearing, bearing pin.In the present embodiment, fix first sleeve 14 at the first summit 11 place, the axes normal of the first sleeve 14 is in support 1 place plane, comprise a rotating shaft 15 again, the two ends of rotating shaft 15 are fixed on corresponding position on wing, above-mentioned first sleeve 14 rotates and is arranged in rotating shaft 15, thus makes support 1 can follow 15 rotations around the shaft of the first sleeve 14.
First pressurized strut 2 is hydraulic actuator, and one end is fixed end, and the other end is drive end.First pressurized strut 2 and support 1 are positioned at same plane (i.e. support 1 three summits determine plane), wherein, one end (fixed end or drive end) of first pressurized strut 2 is hinged with wing, 3rd summit 13 of the other end and support 1 is hinged, makes to drive support 1 15 to rotate around the shaft in the first pressurized strut 2 telescopic process.Also it should be noted that, the first pressurized strut 2 can be controlled by multiple applicable hydraulic efficiency pressure system, repeats no more herein.
Pipe link 3 and support 1 are positioned at same plane, wherein, one end of pipe link 3 and the second summit 12 of support 1 hinged, the other end is fixedly connected with emitting antenna 4, makes emitting antenna 4 can follow pipe link 3 and rotates around the second summit 12.
Second pressurized strut 5 is hydraulic actuator, and one end is fixed end, and the other end is drive end.Second pressurized strut 5 and support 1 are positioned at same plane, and wherein, one end of the second pressurized strut 5 is hinged on the crossbeam between the first summit 11 of support 1 and the second summit 12, the other end and pipe link 3 hinged.In addition, on above-mentioned crossbeam, corresponding position can arrange base, hinged to facilitate with the second pressurized strut 5.
In the aerial jack of airborne meter wave radar emitting antenna provided by the invention, first summit 11 of triangular supports 1 is hinged on wing, second summit 12 place connects emitting antenna 4 by pipe link 3, pipe link 3 is driven to rotate together with emitting antenna 4 while rotating to make support 1, simultaneously, also be hinged with the first pressurized strut 2 at the 3rd summit 12 place of support 1, power can be provided for the rotation of support 1, thus realize the rotation folding and unfolding of meter wave radar emitting antenna in aircraft flight.
Support 1 lockout mechanism can also be comprised in the aerial jack of airborne meter wave radar emitting antenna of the present invention, can lock when emitting antenna 4 folding and unfolding completes.Particularly, lockout mechanism comprises the second sleeve 6, the 3rd sleeve 7, lock pin and locking pressurized strut etc.
Second sleeve 6 is fixedly installed on support 1, and the axes normal of the second sleeve 6 is in support 1 place plane.3rd sleeve 7 is identical with the second sleeve 6 shape, is fixedly installed on support 1, and the axes normal of the 3rd sleeve 7 is in support 1 place plane.Further, especially as shown in Figure 2, the first sleeve 14, second sleeve 6 and the distribution triangular in shape of the 3rd sleeve 7, and the second sleeve 6 axis equals the distance of the 3rd sleeve 7 axis to the first sleeve 14 axis to the distance of the first sleeve 14 axis.It should be noted that, above-mentioned concrete structure can carry out the selection be applicable to as required, repeats no more.
Lock pin external diameter is not more than the internal diameter of the second sleeve 6, and lock pin is positioned at support 1 side, and axes normal is in support 1 place plane, and lock pin axis equals the distance of the second sleeve 6 axis to the first sleeve 14 axis to the distance of the first sleeve 14 axis.Locking pressurized strut one end is fixed on wing, and the other end is connected with lock pin, stretches for driving lock pin.
In embodiments of the present invention, when the second sleeve 6 or the 3rd sleeve 7 follow turn to support 1 turn to a certain applicable position time, can lock pressurized strut can make lock pin extend, and extend in the second sleeve 6 or the 3rd sleeve 7, thus support 1 is fixed.Particularly, design time, when lock pin can stretch into the second sleeve 6 lock time, represent support 1 drive emitting antenna 4 to be in full open position.Relatively, when lock pin can stretch into the 3rd sleeve 7 lock time, represent support 1 drive emitting antenna 4 to be in complete collapsed state.
Further, lock pin can comprise the first lock pin 81 and the second lock pin 82, is symmetricly set on support 1 both sides.Locking pressurized strut comprises the first locking pressurized strut 91 and the second locking pressurized strut 92, and be symmetricly set on support 1 both sides, the first locking pressurized strut 91 is connected with the first lock pin 81, and the second locking pressurized strut 92 is connected with the second lock pin 82.Stretch into two sleeves 6 or the 3rd sleeve 7 realizes the fixing of support 1 by the first lock pin 81 of symmetry and the second lock pin 82 simultaneously, emitting antenna 4 can either be achieved on receiving and the locking of down state, meanwhile, compare single lock pin, such Stability Analysis of Structures is stronger.
It should be noted that, the angle that support 1 rotates can carry out according to the size of the emitting antenna 4 of reality and wing shapes the selection that is applicable to, is all select rotation 90 ° usually.For the diagram direction shown in Fig. 1, when jack will put down emitting antenna 4, be that the first pressurized strut 2 is extended, whole system is rotated around rotating shaft 15, the second pressurized strut 5 simultaneously is also extended, pipe link 3 is rotated around the second summit 12, ensure that emitting antenna 4 remains level putting down in process, until mechanism always motion pipe link 3 vertically time stop, putting down process complete, coordinated with the second sleeve 6 by the first lock pin 81 and the second lock pin 82 again, thus whole support 1 is locked.Process of packing up is contrary, is finally coordinated with the 3rd sleeve 7 by the first lock pin 81 and the second lock pin 82, realizes lock function, repeat no more herein.
In addition, the present invention is at the aerial jack of airborne meter wave radar emitting antenna, and emitting antenna 4 is less than 5 degree with fuselage plane included angle in folding and unfolding process.Further, can the part that the first pressurized strut 2 and rotating shaft 15 on jack are connected with wing be set to detachable, and can Non-follow control, be equivalent to possess jury launch function, by its jettisoning, aircraft safety can be ensured when jack fault.
Aircraft wing is elastic body, and has certain vibration during Aircraft Air flight, therefore, also wants control antenna to be out of shape and keep tracking accuracy while needing to avoid being coupled with above-mentioned motion frequency.In design process of the present invention, being the vibration frequency adjusting whole mechanism by adjusting each pipe beam internal-and external diameter, avoiding airplane motion frequency and wing flutter frequency.
The present invention can also comprise strut bar 9.Strut bar 9 is arranged on support 1 side, and one end and the wing of strut bar 9 are hinged, and the other end is hinged on the crossbeam between the first summit 11 of support 1 and the second summit 12, can provide the bearing force of side direction, lateral force resisting for support 1.The angle that the length of strut bar 9 and installation site can be rotated according to support 1 and size are determined, repeat no more.Further, strut bar also comprises two, is symmetricly set on support both sides, and two strut bars are identical with the position of articulating point of crossbeam, support, improve stability further from both sides to support 1.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (5)
1. the aerial jack of airborne meter wave radar emitting antenna, is arranged on aircraft wing, it is characterized in that, comprising:
Leg-of-mutton support (1), described support (1) is hinged on described wing by the first summit (11);
First pressurized strut (2), same plane is positioned at described support (1), one end of described first pressurized strut (2) is with to state wing hinged, and the 3rd summit (13) of the other end and described support (1) is hinged;
Pipe link (3), same plane is positioned at described support (1), one end of described pipe link (3) and second summit (12) of described support (1) hinged, the other end is fixedly connected with described emitting antenna (4);
Second pressurized strut (5), same plane is positioned at described support (1), one end of described second pressurized strut (5) is hinged on the crossbeam between first summit (11) of described support (1) and the second summit (12), the other end and described pipe link (3) hinged.
2. aerial jack according to claim 1, is characterized in that, also comprise:
First sleeve (14), is fixedly installed on the first summit (11) place of described support (1), and the axes normal of described first sleeve (14) is in described support (1) place plane;
Rotating shaft (15), two ends and described wing are fixed, and the rotation of described first sleeve (14) is arranged in described rotating shaft (15).
3. aerial jack according to claim 1, is characterized in that, also comprise:
Second sleeve (6), is fixedly installed on described support (1), and the axes normal of described second sleeve (6) is in described support (1) place plane;
3rd sleeve (7), identical with described second sleeve (6) shape, be fixedly installed on described support (1), the axes normal of described 3rd sleeve (7) is in described support (1) place plane, wherein, described first sleeve (14), the second sleeve (6) and the 3rd sleeve (7) distribution triangular in shape, and described second sleeve (6) axis equals the distance of described 3rd sleeve (7) axis to described first sleeve (14) axis to the distance of described first sleeve (14) axis;
Lock pin, external diameter is not more than the internal diameter of described second sleeve (6), described lock pin is positioned at described support (1) side, axes normal is in described support (1) place plane, and described lock pin axis equals the distance of described second sleeve (6) axis to described first sleeve (14) axis to the distance of described first sleeve (14) axis;
Locking pressurized strut, one end is fixed on described wing, and the other end is connected with described lock pin, stretches for driving described lock pin.
4. aerial jack according to claim 3, is characterized in that, described lock pin comprises the first lock pin (81) and the second lock pin (82), is symmetricly set on described support (1) both sides;
Described locking pressurized strut comprises the first locking pressurized strut (91) and the second locking pressurized strut (92), be symmetricly set on described support (1) both sides, described first locking pressurized strut (91) is connected with described first lock pin (81), and described second locking pressurized strut (92) is connected with described second lock pin (82).
5. aerial jack according to claim 1, is characterized in that, also comprise:
Strut bar (9), be arranged on described support (1) side, one end and the described wing of described strut bar (9) are hinged, and the other end is hinged on the crossbeam between first summit (11) of described support (1) and the second summit (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510173598.9A CN104743131B (en) | 2015-04-13 | 2015-04-13 | A kind of aerial jack of airborne metre wave radar transmitting antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510173598.9A CN104743131B (en) | 2015-04-13 | 2015-04-13 | A kind of aerial jack of airborne metre wave radar transmitting antenna |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104743131A true CN104743131A (en) | 2015-07-01 |
| CN104743131B CN104743131B (en) | 2017-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510173598.9A Active CN104743131B (en) | 2015-04-13 | 2015-04-13 | A kind of aerial jack of airborne metre wave radar transmitting antenna |
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| Country | Link |
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| CN (1) | CN104743131B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109524758A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of Multi-Function Antenna mounting platform |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0336745A2 (en) * | 1988-04-08 | 1989-10-11 | Kabushiki Kaisha Toshiba | Portable antenna apparatus |
| EP1189301A2 (en) * | 2000-09-15 | 2002-03-20 | Space Systems / Loral, Inc. | Main reflector and subreflector deployment and storage systems |
| CN200947462Y (en) * | 2006-09-14 | 2007-09-12 | 中国兵器工业第二○六研究所 | Folding radar antenna lifting gearing |
| WO2008128077A1 (en) * | 2007-04-13 | 2008-10-23 | Winegard Company | High wind elevation mechanism for a satellite antenna system |
| CN202423532U (en) * | 2011-12-12 | 2012-09-05 | 南京恩瑞特实业有限公司 | Hydraulic-drive collapsible radar antenna elevating mechanism |
-
2015
- 2015-04-13 CN CN201510173598.9A patent/CN104743131B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0336745A2 (en) * | 1988-04-08 | 1989-10-11 | Kabushiki Kaisha Toshiba | Portable antenna apparatus |
| EP1189301A2 (en) * | 2000-09-15 | 2002-03-20 | Space Systems / Loral, Inc. | Main reflector and subreflector deployment and storage systems |
| CN200947462Y (en) * | 2006-09-14 | 2007-09-12 | 中国兵器工业第二○六研究所 | Folding radar antenna lifting gearing |
| WO2008128077A1 (en) * | 2007-04-13 | 2008-10-23 | Winegard Company | High wind elevation mechanism for a satellite antenna system |
| CN202423532U (en) * | 2011-12-12 | 2012-09-05 | 南京恩瑞特实业有限公司 | Hydraulic-drive collapsible radar antenna elevating mechanism |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109524758A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of Multi-Function Antenna mounting platform |
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| Publication number | Publication date |
|---|---|
| CN104743131B (en) | 2017-03-01 |
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