DE1481684A1 - Device for folding down a protective covering for an aircraft device - Google Patents
Device for folding down a protective covering for an aircraft deviceInfo
- Publication number
- DE1481684A1 DE1481684A1 DE19661481684 DE1481684A DE1481684A1 DE 1481684 A1 DE1481684 A1 DE 1481684A1 DE 19661481684 DE19661481684 DE 19661481684 DE 1481684 A DE1481684 A DE 1481684A DE 1481684 A1 DE1481684 A1 DE 1481684A1
- Authority
- DE
- Germany
- Prior art keywords
- protective cover
- fuselage
- support
- pivot point
- protective
- 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
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
Vorrichtung zum Abklappen einer Schutzverkleidung für ein Flugzeuggerät Die Erfindung betrifft eine Vorrichtung zurr Abklappen einer Schutzverkleidung für ein am Bug eines Flugkörpers, insbesondere eines Plugzeuges, angeordnetee Gerifit; z.B. ein Radargerät.Device for folding down a protective covering for an aircraft device The invention relates to a device for folding down a protective cover for a Gerifit arranged on the bow of a missile, in particular a plug-in tool; e.g. a radar device.
Bei bekannten Vorrichtungen dieser Art wird die Schutzverklcdung durch Verschlüsse gehalten, deren an der Schutzverkleidung sitzende Teil durch Verschieben in Längsrichtüng von dem an Rumpf sitzenden Teil entfernbar ist. Bei dieser Vorrichtung bleibt die Schutzverkleidune nicht am Rumpf, sondern muf nach dem Abziehen auf den Boden gelegt werden.In known devices of this type, the Schutzverklcdung is through Locks held, the part sitting on the protective cover by moving can be removed in the longitudinal direction from the part seated on the fuselage. With this device the protective fairing does not stay on the fuselage, but has to be on the after removal Ground.
Der Erfinder hat sich die Aufgabe gestellt, eine Vorrichtung zu schaffen, bei der die Sehutzverkleidung auch nach den Verschieben in Längsrichtung am Rumpf verbleibt.The inventor set himself the task of creating a device in which the protective cover also after moving in the longitudinal direction on the fuselage remains.
Erfindunzgsgemäß wird dies erreicht durch eine am Rumpf angelenkte Stütze, deren freies Ende an der Innenseite der Schutzverkleidung angelenkt ist, und eitlen Lenker, der hinter der erstgenannten Stutze am Rumpf angelenkt ist und oberhalb des Anlenkpunktes der Stütze an der Innenseite der Schutzverkleidung angreift, wobei die Verschlußlage des Lenkers durch ein elastisches Glied, z.B. eine Zugfeder, gesichert ist, so daß beim Abziehen der Schutzverkleidung zünhchst eine angenäherte Horizontalverschiebung der Schutzverkleidung und erst anschließend ihre Verschwenkung erfolgt. Die Erfindung ist in der Zeichnung in einem Ausführungsbeispiel dargestellt. Es zeigen: Fig. 1 einen Schnitt durch die Schutzverkleidung im eingefahrenen Zustand; die aasgefahrene Stellung, ist strichpunktiert angedeutet; Fig. 2 einen schnitt durch die Befestigung der Schutzverkleidung am Rumpf, die an sich bekannt ist; Fit. 3 eine Ansicht in verkleinertem Eaßstab in Richtung auf die Schutzverkleidung von innen gesehen, die drei Befestigungspunkte gemäß Fig. 2 erkennen läßt. Am vorderen Teil des Rumpfes 1 ist ein Tragblech 1a vorgesehen, an dem drei Verschlüsse angeordnet sind, deren an der Schutzverkleidung 3 sitzende feil von dem am Rumpf sitzenden Teil durch Verschieben in Längsrichtung entfernbar ist. Solche Verschlüsse sind bekannt. Die Schutzverkleidung 3 ist von einer Stütze 2 g ehalten, die an einer am Tragblech 1a. befestigten Konsole 6 angelenkt ist. Die Stütze 2 ist an ihrem freien Ende an der Innenseite der Schutzverkleidung angelenkt. An der Konsole 6 ist ferner ein Lenker 4 gelagert, der oberhalb des Anlenkpunktes der Stütze 2 an der Schutzverkleidung an,greift. Der Lenker 4 ist zwischen der Stütze 2 und der Tragblech 1a angeordnet. Eine Zugfeder 5, die an der Konsole 6 befestigt ist, greift am Lenker 4 an. Die Wirkungsweise ist folgende: r das von der Schutzverkleidung abgedeckte Gerät besichtigt werden soll, zieht die Bedienungsperson die Schutzverkleidung in horizontaler Richtung nach vorn, bis die Verschlüsse gelöst sind. Dann schwingt die Schutzverkleidung un die Stütze 2 und wird dabei durch den Lenker 4 geführt.According to the invention this is achieved by a hinged on the fuselage Support, the free end of which is hinged to the inside of the protective cover, and vain handlebar, which is hinged behind the first-mentioned support on the trunk and engages above the pivot point of the support on the inside of the protective cladding, whereby the locking position of the handlebar is provided by an elastic member, e.g. a tension spring, is secured, so that when pulling off the protective cover initially an approximate Horizontal shift the protective cover and only afterwards their pivoting takes place. The invention is shown in the drawing in one embodiment shown. The figures show: FIG. 1 a section through the protective covering in the retracted position State; the aasgefahrene position is indicated by dash-dotted lines; Fig. 2 a cut through the attachment of the protective covering to the fuselage, which is known per se is; Fit. 3 is a view on a reduced scale in the direction of the protective covering seen from the inside, the three attachment points according to FIG. 2 can be seen. At the front Part of the fuselage 1 is a support plate 1a on which three closures are arranged are, whose seated on the protective lining 3 for sale from the one seated on the fuselage Part can be removed by moving in the longitudinal direction. Such closures are known. The protective cladding 3 is held by a support 2, which is attached to a on the support plate 1a. attached console 6 is hinged. The support 2 is on her free end hinged to the inside of the protective cover. On the console 6 a link 4 is also mounted, which is above the point of articulation of the support 2 the protective cladding attacks. The handlebar 4 is between the support 2 and the Support plate 1a arranged. A tension spring 5, which is attached to the console 6, engages on the handlebar 4. The mode of action is as follows: r that of the protective covering covered device is to be inspected, the operator pulls the Protective cover forward in a horizontal direction until the locks are released. Then swings the protective cover un the support 2 and is guided by the handlebar 4.
Claims (3)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEV0031058 | 1966-05-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
DE1481684A1 true DE1481684A1 (en) | 1969-03-20 |
Family
ID=7586134
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE19661481684 Pending DE1481684A1 (en) | 1966-05-13 | 1966-05-13 | Device for folding down a protective covering for an aircraft device |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE1481684A1 (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2976909A1 (en) * | 2011-06-27 | 2012-12-28 | Airbus Operations Sas | METHOD FOR OPENING A PROTECTION DOME, IN PARTICULAR A RADOME, AND RADOME EQUIPPED WITH A PANTOGRAPH FOR IMPLEMENTATION |
CN104512556A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Four-link opening mechanism of radar cover of airplane |
EP3798114A1 (en) * | 2019-09-27 | 2021-03-31 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A radome cover shell and opening kinematic |
US11643182B2 (en) | 2020-10-22 | 2023-05-09 | Airbus Helicopters Deutschland GmbH | Radome cover shell and opening kinematic |
-
1966
- 1966-05-13 DE DE19661481684 patent/DE1481684A1/en active Pending
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2976909A1 (en) * | 2011-06-27 | 2012-12-28 | Airbus Operations Sas | METHOD FOR OPENING A PROTECTION DOME, IN PARTICULAR A RADOME, AND RADOME EQUIPPED WITH A PANTOGRAPH FOR IMPLEMENTATION |
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 |
CN103765672A (en) * | 2011-06-27 | 2014-04-30 | 空中客车运营简化股份公司 | Method of opening a protective dome, in particular a radome, and radome equipped with a pantograph for implementation thereof |
CN103765672B (en) * | 2011-06-27 | 2016-04-13 | 空中客车运营简化股份公司 | Open the method for protectiveness dome especially radome, and equipment is for implementing the radome of the pantograph of the method |
US9608320B2 (en) | 2011-06-27 | 2017-03-28 | Airbus Operations S.A.S. | Method of opening a protective dome, in particular a radome, and radome equipped with a pantograph for implementation thereof |
CN104512556A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Four-link opening mechanism of radar cover of airplane |
EP3798114A1 (en) * | 2019-09-27 | 2021-03-31 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A radome cover shell and opening kinematic |
EP3805094A1 (en) * | 2019-09-27 | 2021-04-14 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A radome cover shell and opening kinematic |
US11643182B2 (en) | 2020-10-22 | 2023-05-09 | Airbus Helicopters Deutschland GmbH | Radome cover shell and opening kinematic |
US11697488B2 (en) | 2020-10-22 | 2023-07-11 | Airbus Helicopters Deutschland GmbH | Radome cover shell and opening kinematic |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
SH | Request for examination between 03.10.1968 and 22.04.1971 |