CN106628109A - Rotating and connecting structure of aircraft radome - Google Patents
Rotating and connecting structure of aircraft radome Download PDFInfo
- Publication number
- CN106628109A CN106628109A CN201611217520.3A CN201611217520A CN106628109A CN 106628109 A CN106628109 A CN 106628109A CN 201611217520 A CN201611217520 A CN 201611217520A CN 106628109 A CN106628109 A CN 106628109A
- Authority
- CN
- China
- Prior art keywords
- radome
- rotating
- bearing
- hydraulic motor
- topples
- Prior art date
- 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
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
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
- H01Q1/428—Collapsible radomes; rotatable, tiltable radomes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gears, Cams (AREA)
Abstract
The invention belongs to the technical field of aviation and relates to a rotating and connecting structure of an aircraft radome. The rotating and connecting structure mainly comprises a radome (1), a rack wheel (2), a pinion (3), a speed reducer (4), a hydraulic motor (5), a support seat (6), an overturning bearing (7), a transition part (8), a bolt (9), a bolt (10), a bracket (11) and a reinforcer (12). The overturning bearing of an inner gear is arranged in the radome, and a load of the radome is transferred to a bearing inner ring and then transferred to the bracket by virtue of drive of the hydraulic motor, so that a large-size and large-inertia radome rotating function and load transferring are achieved. The rotating and connecting structure is simple, good in force transmission characteristic and light in weight, adopts rotating driving, and adopts a rotating driving, connection and installation method of the aircraft radome. Rotating of the radome can be achieved, the load of the rotating radome is transferred to the bracket, and the problems of large-inertia rotating and load transferring are solved.
Description
Technical field
The invention belongs to technical field of aerospace, is related to radome of fighter rotation and attachment structure.
Background technology
Radome is the significant feature of early warning plane, is also the difficult point developed.The radar of traditional early warning plane is in collar plate shape thunder
Up in cover antenna transmitting fan-shaped beam, and rotated using mechanical type rotating pedestal so that radar beam can scan cover it is certain
Spatial domain, referred to as mechanical scanning；This mode must treat radar antenna rotate a circle or complete the single pass cycle, capture again
After target, lasting tracking could be implemented to same target, general AEW surveillance radar rotating speed is about 5～6 times per minute,
It is exactly 30 ° per second～36 °.Antenna house is designed to an entirety with antenna, and during antenna scanning, antenna and antenna house rotate together
(rotation cover).Rotation cover is installed on the top of aircraft, drives rotation cover to carry out circular scanning by gearing.How effectively will be used to greatly
The radome of amount rotates, and can bear various load, and rotation and support connection are technical bottlenecks.
E-3A disk diameter 9.14m, thick 1.83m, azimuth is then mechanical scan, in the task of execution, disc day
Irdome can be with 6 turns per minute of speed rate rotation, the orientation for enabling radar beam to cover 360 °, if radar is not required to work in flight
When, it is to maintain spring bearing lubrication, radar antenna still can be so that per 4 minutes 1 turn of speed rate rotations, the present invention be before effect is reached
Put, there is provided another rotation mode.
The content of the invention
The purpose of the present invention is：There is provided a kind of on the premise of structural strength is met, simple structure, rotation driving, power transmission
Characteristic is good, and a kind of lightweight aircraft rotation and support connect.
The technical scheme is that：A kind of airplane radome rotation and attachment structure, it is characterised in that including thunder
Up to cover (1), gear wheel (2), little gear (3), reductor (4), hydraulic motor (5), bearing (6), the bearing that topples (7), transition piece
(8), bolt (9), bolt (10), support (11), reinforcement (12), wherein, support (11) is designed for double airfoil type, by one
The transition piece (8) that integrated machine adds is coupled together, and forms bearing structure, selects a bearing that topples (7), the bearing that topples (7) outer ring
Connection radome (1), inner ring connection transition piece (8), gear wheel (2) size is mutually coordinated with the bearing that topples (7) outer ring, hydraulic motor
(5) it is power source, connection little gear (3), little gear (3) engages with gear wheel (2), reductor (4) and hydraulic motor (5) and little
Gear (3) is connected, and starts hydraulic motor (5), drives reductor (4), gear wheel-train, drive gear wheel (2) transmission, radome
(1) and then rotate.
The invention has the beneficial effects as follows：One kind is provided on the premise of structural strength rigidity is met, simple structure, power transmission is special
Property good, rotation driving, a kind of lightweight radome of fighter rotation driving and connection mounting means.Can realize that radome revolves
The radome load transmission for turn, rotating solves large inertia rotation and a posting difficult problem on support.
Description of the drawings
Fig. 1 is a kind of radome of fighter rotation of the invention and connection diagram；
Wherein, radome (1), gear wheel (2), little gear (3), reductor (4), hydraulic motor (5), bearing (6), topple
Bearing (7), transition piece (8), bolt (9), bolt (10), support (11), reinforcement (12).
Specific embodiment
The present invention and embodiment are elaborated below in conjunction with the accompanying drawings.
Referring to Fig. 1, a kind of airplane radome of the invention rotates and attachment structure, it is characterised in that including radome
(1), gear wheel (2), little gear (3), reductor (4), hydraulic motor (5), bearing (6), the bearing that topples (7), transition piece (8),
Bolt (9), bolt (10), support (11), reinforcement (12), wherein, support (11) is designed for double airfoil type, by an entirety
The transition piece (8) that machine adds is coupled together, and forms bearing structure, selects a bearing that topples (7), the connection of the bearing that topples (7) outer ring
Radome (1), inner ring connection transition piece (8), gear wheel (2) size is mutually coordinated with the bearing that topples (7) outer ring, hydraulic motor (5)
It is power source, connection little gear (3), little gear (3) engages with gear wheel (2), reductor (4) and hydraulic motor (5) and little tooth
Wheel (3) is connected, and starts hydraulic motor (5), drives reductor (4), gear wheel-train, drive gear wheel (2) transmission, radome (1)
And then rotate.
Concrete assembling of the invention and work follow these steps to carry out：
Transition piece is added to be connected as a single entity double airfoil type support integrated machine first, it is ensured that the bearing inner race that topples can be with support transition
Part connects, and becomes standing part.
The bearing outer ring that topples is connected with radome by a circle bolt, and toppling, bearing top connects a big disk gear.
Hydraulic motor, reductor, little gear are fixed on integrated machine plus transition piece, and little gear is engaged with gear wheel.
Transition piece standing part ensures 10mm with radome rotating part border uniform gap.Periodically apply profit to the bearing that topples
Consistent lubricant.
Start hydraulic motor, the rotating speed needed to radome through reductor primary speed-down, gear engagement double reduction.
The load that radome comes, passes to the bearing outer ring that topples, in the ball by scribbling lubricating grease by radome skeleton
Inner ring is passed to, the bearing inner race that topples is passed to again on transition piece, and transition piece is passed on support skeleton, passing to fuselage frame, Liang Shangping
Weighing apparatus.
Claims (1)
1. a kind of rotation of airplane radome and attachment structure, it is characterised in that including radome (1), gear wheel (2), little
Gear (3), reductor (4), hydraulic motor (5), bearing (6), the bearing that topples (7), transition piece (8), bolt (9), bolt (10),
Support (11), reinforcement (12), wherein, support (11) is designed for double airfoil type, the transition piece (8) added by an integrated machine is even
Pick up and, form bearing structure, select a bearing that topples (7), the bearing that topples (7) outer ring connection radome (1), inner ring connection
Transition piece (8), gear wheel (2) size is mutually coordinated with the bearing that topples (7) outer ring, and hydraulic motor (5) is power source, connects little gear
(3), little gear (3) is engaged with gear wheel (2), and reductor (4) is connected with hydraulic motor (5) and little gear (3), starts hydraulic pressure horse
Up to (5), reductor (4), gear wheel-train, drive gear wheel (2) transmission, radome (1) is driven and then to rotate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611217520.3A CN106628109A (en) | 2016-12-26 | 2016-12-26 | Rotating and connecting structure of aircraft radome |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611217520.3A CN106628109A (en) | 2016-12-26 | 2016-12-26 | Rotating and connecting structure of aircraft radome |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106628109A true CN106628109A (en) | 2017-05-10 |
Family
ID=58828411
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611217520.3A Pending CN106628109A (en) | 2016-12-26 | 2016-12-26 | Rotating and connecting structure of aircraft radome |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628109A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN107748102A (en) * | 2017-11-29 | 2018-03-02 | 中国航空工业集团公司济南特种结构研究所 | It is a kind of to apply the balanced method for drawing load to radome |
| CN108100219A (en) * | 2017-11-16 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of radome of fighter elevating mechanism |
| CN109484620A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3026516A (en) * | 1957-12-02 | 1962-03-20 | Lockheed Aircraft Corp | Rotatable radome for aircraft |
| US5049891A (en) * | 1990-02-23 | 1991-09-17 | Grumman Aerospace Corporation | Radome-antenna installation with rotating equipment rack |
| CN203589212U (en) * | 2013-12-06 | 2014-05-07 | 贵州振华天通设备有限公司 | Full-range rotating antenna pedestal |
| CN103770930A (en) * | 2012-10-18 | 2014-05-07 | 埃姆普里萨有限公司 | Assemblies for external attachment of airborne sensor pods to an aircraft fuselage |
| 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 |
-
2016
- 2016-12-26 CN CN201611217520.3A patent/CN106628109A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3026516A (en) * | 1957-12-02 | 1962-03-20 | Lockheed Aircraft Corp | Rotatable radome for aircraft |
| US5049891A (en) * | 1990-02-23 | 1991-09-17 | Grumman Aerospace Corporation | Radome-antenna installation with rotating equipment rack |
| CN103770930A (en) * | 2012-10-18 | 2014-05-07 | 埃姆普里萨有限公司 | Assemblies for external attachment of airborne sensor pods to an aircraft fuselage |
| CN203589212U (en) * | 2013-12-06 | 2014-05-07 | 贵州振华天通设备有限公司 | Full-range rotating antenna pedestal |
| 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 |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108100219A (en) * | 2017-11-16 | 2018-06-01 | 中国航空工业集团公司西安飞机设计研究所 | A kind of radome of fighter elevating mechanism |
| CN107748102A (en) * | 2017-11-29 | 2018-03-02 | 中国航空工业集团公司济南特种结构研究所 | It is a kind of to apply the balanced method for drawing load to radome |
| CN109484620A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
| CN109484620B (en) * | 2018-03-16 | 2022-05-13 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
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Application publication date: 20170510 |