CN106828926A - Can folding and unfolding hull bottom faulted-stage radome fairing - Google Patents
Can folding and unfolding hull bottom faulted-stage radome fairing Download PDFInfo
- Publication number
- CN106828926A CN106828926A CN201510896344.XA CN201510896344A CN106828926A CN 106828926 A CN106828926 A CN 106828926A CN 201510896344 A CN201510896344 A CN 201510896344A CN 106828926 A CN106828926 A CN 106828926A
- Authority
- CN
- China
- Prior art keywords
- radome fairing
- hull bottom
- stage
- faulted
- chute
- 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
- B64C35/00—Flying-boats; Seaplanes
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
The present invention provide a kind of seaplane with can folding and unfolding hull bottom faulted-stage radome fairing, it includes integrating rear on the radome fairing of faulted-stage profile, radome fairing and be connected with hull bottom bearing and carries the short beam of chute, the anterior ears bearing being connected with actuator of radome fairing, be fixed on actuator that hull bottom can stretch, be fixed on the bearing that hull bottom is connected with radome fairing short beam.When radome fairing is put down, actuator operating bar is stretched out, and the radome fairing front that promotion is attached thereto sinks to is alignd with faulted-stage, and radome fairing rear short beam chute is relative with the ears bearing of hull bottom to be slided, and rear is pressed close to hull bottom, realizes from faulted-stage to the rectification of rear hull bottom；When radome fairing is packed up, actuator operating bar is retracted, and to being fitted with hull bottom, radome fairing rear short beam chute is relative with hull bottom double support to be slided, and faulted-stage is exposed in the radome fairing front that pulling is attached thereto.This retractable radome fairing meets the seaplane landing hull bottom profile demand different with the airflight stage.
Description
Technical field
The present invention is applied to landing aircraft waterborne, particularly the landing aircraft waterborne with hull bottom faulted-stage structure.
Background technology
Overwater flight device, in order to smoothly leave the water surface, typically sets hull bottom faulted-stage structure when taking off.Aircraft
When the water surface takes off, faulted-stage can destroy " suction " of the water surface to hull bottom so that aircraft can be relatively easy to and leave the water surface,
But in the air during flight, faulted-stage brings many adverse effects to the aeroperformance of aircraft, increases flight resistance, and rear is not
The vortex of stabilization also has a certain degree of influence for the stability of aircraft.
The content of the invention
The deficiency of airflight poor performance for takeoff and landing performance on current landing aircraft hull bottom faulted-stage constitution water waterborne is good,
The invention provides it is a kind of can be with the faulted-stage radome fairing scheme of folding and unfolding so that landing waterborne can be met at hull bottom faulted-stage and aerial is flown
The row demand different for hull bottom profile.
In order to meet above-mentioned different demands, the present invention to set at hull bottom faulted-stage it is a kind of can be with the faulted-stage radome fairing of folding and unfolding.
The radome fairing is arranged on faulted-stage rear, and on the water during landing, radome fairing is upwards collected through, and total component is attached to behind faulted-stage
On hull bottom, expose faulted-stage structure, now aircraft normally can leave the water surface using faulted-stage；When leaving flight in the air after the water surface,
Radome fairing puts down, front connection faulted-stage, and laminating hull bottom in rear sentences rectification effect to faulted-stage.
The present invention provide can folding and unfolding hull bottom faulted-stage radome fairing, have the advantages that：In this scheme, flight
Device had both possessed good water surface takeoff and landing performance, and fairing aerodynamic configuration demand during airflight is met again.
Brief description of the drawings
Fig. 1 be the present invention provide can folding and unfolding hull bottom faulted-stage radome fairing one embodiment structure side schematic view；
Fig. 2 be the present invention provide can folding and unfolding hull bottom faulted-stage radome fairing one embodiment structure longitudinal direction schematic diagram.
Wherein：101 is the faulted-stage structure of aircraft；102 is the actuator being connected on aircraft hull bottom；103 is aircraft faulted-stage
The hull bottom at rear；104 are integrally fixed at the bearing with bearing pin on hull bottom；105 are integrally fixed at radome fairing rear carries the short of chute
Beam；106 is radome fairing；107 are integrally fixed on radome fairing the bearing being connected with actuator.
Specific embodiment
Accompanying drawing in implementing below in conjunction with present example, is purged, complete to the technical scheme in the embodiment of the present invention
Whole description, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.Based on this
Embodiment in invention, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belongs to the scope of protection of the invention.
The present invention provide one kind can folding and unfolding hull bottom faulted-stage radome fairing, including：Faulted-stage 101, actuator 102, hull bottom 103,
Bearing 104, short beam 105, radome fairing 106, bearing 107.
The one end of actuator 102 is connected on hull bottom 103, and the other end is ined succession the bearing 107 being fixed on radome fairing 106, Gu
The bearing 104 that is scheduled on hull bottom 103 is installed above a bearing pin, and this bearing pin can be stuck in and be fixed on radome fairing 106
In the chute of short beam 105, bearing 104 and short beam 105 relative can be slided.
When radome fairing will be packed up, the operating bar of actuator 102 withdraws, and pulls bearing 107 near hull bottom 103,
Until radome fairing 106 is close together with hull bottom 103.
With the relative sliding process of short beam 105, bearing pin will not skid off the chute of short beam 105 to the bearing pin of bearing 104.
In one embodiment, actuator 102 is fixed on above hull bottom 103, and the connected mode with bearing 107 is
Rotatably；In another embodiment, the connection of actuator 102 and bearing 107 be it is fixed, actuator 102 with
The connected mode of hull bottom 103 is rotatable.
In one embodiment, the position of short beam 105 and bearing 104 can exchange, i.e., the short beam 105 with chute
Alow on 103, the bearing 104 with bearing pin is fixed on radome fairing 106 for fixation.
The chute shape of short beam 105 needs design according to the movement locus of radome fairing, can be straight line, or curve.
Claims (8)
1. one kind can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：One piece can before transition faulted-stage and after faulted-stage hull bottom profile rectification
Cover, be connected to the actuator of hull bottom after faulted-stage, the bearing that actuator and radome fairing are linked together, be fixed on radome fairing rear portion
Short beam and short beam chute with chute are coupled together by bearing pin and are fixed on the bearing of hull bottom；When radome fairing is put down, start
Device push rod stretches out, and the radome fairing front that promotion is attached thereto sinks to and alignd with faulted-stage, radome fairing rear short beam chute and hull bottom
Ears bearing is relative to be slided, and is realized from faulted-stage to the rectification of rear hull bottom；When radome fairing is packed up, actuator pusher retracted is drawn
The dynamic radome fairing front being attached thereto is fitted with hull bottom, and radome fairing rear short beam chute is relative with hull bottom ears bearing to be slided, faulted-stage
It is exposed.
2. according to claim 1 can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：Described actuator one end is connected to hull bottom
Structure, the other end is connected on an anterior bearing of radome fairing；A short beam for having chute is fixed at radome fairing rear portion, and short beam leads to
Cross chute to be connected with a fixed bearing alow, there is a bearing pin that can be stuck in chute on the hold-down support of hull bottom.
3. according to claim 1 can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：Described actuator one end is connected to hull bottom
Structure, the other end is connected on radome fairing, and during actuator is flexible, the connection of actuator at least one end can be to turn
Dynamic.
4. according to claim 1 can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：At the front end of the radome fairing and faulted-stage
The hull bottom shape in front matches, and rear end matches with rear portion hull bottom shape；Received in radome fairing with plate of obturaging radome fairing side
Bag provides blocking for side when radome fairing puts down in hull both sides when rising.
5. according to claim 1 and 2 can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：The short beam with chute can
To allow that radome fairing rear portion in folding and unfolding is slided along the guiding of chute.
6. according to claim 1 and 2 can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：The fixation alow go up with it is short
There is a bearing pin on the bearing that the chute of beam is connected, bearing pin can be stuck in chute and slide freely.
7. according to claim 1,2,4 can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：The plate of obturaging of radome fairing both sides
Anterior wider, rear portion is narrower, and still overlap area after radome fairing puts down with hull sidepiece.
8. according to claim 1,2,4,7 can folding and unfolding hull bottom faulted-stage radome fairing, it is characterised in that：The envelope of radome fairing both sides
Tight plate width is slightly wider than hull, will not be interfered with hull when radome fairing folding and unfolding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510896344.XA CN106828926A (en) | 2015-12-07 | 2015-12-07 | Can folding and unfolding hull bottom faulted-stage radome fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510896344.XA CN106828926A (en) | 2015-12-07 | 2015-12-07 | Can folding and unfolding hull bottom faulted-stage radome fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106828926A true CN106828926A (en) | 2017-06-13 |
Family
ID=59150699
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510896344.XA Pending CN106828926A (en) | 2015-12-07 | 2015-12-07 | Can folding and unfolding hull bottom faulted-stage radome fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106828926A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720541A (en) * | 2018-11-12 | 2019-05-07 | 中航通飞研究院有限公司 | A kind of seaplane faulted-stage force transferring structure and aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2350314Y (en) * | 1998-12-09 | 1999-11-24 | 王绍雄 | Amphibious wing boat |
| US6042052A (en) * | 1998-09-25 | 2000-03-28 | Smith; Donald E. | Retractable step fairing for amphibian airplane |
| CN200985093Y (en) * | 2006-12-22 | 2007-12-05 | 中国科技开发院 | Water-driving arrangement for ground effect aircraft |
| US20080302908A1 (en) * | 2006-11-22 | 2008-12-11 | Gerald Filipek | Detachable hydrofoil trim tabs for use with seaplane floats for assisting with lower speed on-plane condition and stability during step turning/chine walk manuevers |
| CN104443388A (en) * | 2013-09-15 | 2015-03-25 | 南京大五教育科技有限公司 | Novel water-driving arrangement ground effect aircraft |
-
2015
- 2015-12-07 CN CN201510896344.XA patent/CN106828926A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6042052A (en) * | 1998-09-25 | 2000-03-28 | Smith; Donald E. | Retractable step fairing for amphibian airplane |
| CN2350314Y (en) * | 1998-12-09 | 1999-11-24 | 王绍雄 | Amphibious wing boat |
| US20080302908A1 (en) * | 2006-11-22 | 2008-12-11 | Gerald Filipek | Detachable hydrofoil trim tabs for use with seaplane floats for assisting with lower speed on-plane condition and stability during step turning/chine walk manuevers |
| CN200985093Y (en) * | 2006-12-22 | 2007-12-05 | 中国科技开发院 | Water-driving arrangement for ground effect aircraft |
| CN104443388A (en) * | 2013-09-15 | 2015-03-25 | 南京大五教育科技有限公司 | Novel water-driving arrangement ground effect aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720541A (en) * | 2018-11-12 | 2019-05-07 | 中航通飞研究院有限公司 | A kind of seaplane faulted-stage force transferring structure and aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7300021B2 (en) | Aerospace vehicle fairing systems and associated methods | |
| US11673653B2 (en) | Wingtip device | |
| US9845162B2 (en) | Protective finish for wing tip devices | |
| US8864083B1 (en) | Low noise wing slat system with a fixed wing leading edge and deployable bridging panels | |
| WO2011069887A3 (en) | High-lift system for an aircraft, method for displacing a lift flap, and aircraft having a high-lift system | |
| DE19925560A1 (en) | Additional wing for main wing of aircraft | |
| US10933976B2 (en) | Leading edge high-lift device | |
| CN103939216B (en) | Embedded type air inlet channel using combined opening surface vortex control method | |
| US7278609B2 (en) | Movable nose cap and control strut assembly for supersonic aircraft | |
| CN101492090A (en) | Posterior edge separation vortex high-lift force high speed laminar flow airfoil | |
| CN208882103U (en) | A kind of aircraft drag reduction vortex generator | |
| CA2719163C (en) | Improved slat configuration for fixed-wing aircraft | |
| US5178348A (en) | Contoured wing/flap assembly and method | |
| CN106828926A (en) | Can folding and unfolding hull bottom faulted-stage radome fairing | |
| RU2008138594A (en) | WING OF THE AIRCRAFT (OPTIONS), REJECTED WAGON AND AIRCRAFT | |
| US7216835B2 (en) | Aircraft with extendable leading edge of fuselage and wings | |
| US20180194482A1 (en) | Negative lift evacuation slide | |
| US8740139B1 (en) | Leading edge snag for exposed propeller engine installation | |
| CN211543875U (en) | Flow optimization device at junction of leading edge bending flap and leading edge slat | |
| CN115783236A (en) | Low-noise high-lift device for wing and airplane | |
| US20100038474A1 (en) | Aircraft horizontal stabilizer | |
| CN202541831U (en) | Small wing of airplane | |
| CN110539882B (en) | Method and device for optimizing flow at junction of leading edge bending flap and leading edge slat | |
| CN108190034A (en) | A kind of flexibility variant structure | |
| RU2594321C1 (en) | Aerodynamic profile of bearing surface of aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170613 |
|
| WD01 | Invention patent application deemed withdrawn after publication |