Deployable floor panel arrangement for aircraft cabin area
US-9511847-B2 · Dec 6, 2016 · US
Control unit device for an aircraft seat
US2016264247A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016264247-A1 |
| Application number | US-201415036074-A |
| Country | US |
| Kind code | A1 |
| Filing date | Nov 7, 2014 |
| Priority date | Nov 13, 2013 |
| Publication date | Sep 15, 2016 |
| Grant date | — |
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- Title
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- Abstract
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- Assignees and inventors
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- Key dates
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- First independent claim
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- CPC / IPC classifications
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- Citations and related patents
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Abstract
Official abstract text for this publication.
The invention concerns a control unit device for an aircraft seat, with a control and/or regulating unit, with at least one actuator unit coupled to the control and/or regulating unit, and with at least one additional unit. According to the invention, the additional unit is coupled via the actuator unit to the control and/or regulating unit.
First claim
Opening claim text (preview).
1 . A control unit device for an aircraft seat, having a control and/or regulation unit, having at least one actuator unit which is coupled to the control and/or regulation unit, and having at least one additional unit, wherein the additional unit is coupled to the control and/or regulation unit via the actuator unit. 2 . The control unit device as claimed in claim 1 , wherein the actuator unit comprises at least one plug element, via which the actuator unit is coupled to the control and/or regulation unit, wherein the additional unit is connected to the actuator unit via the plug element. 3 . The control unit device as claimed in claim 1 , wherein the plug element has at least one pin via which the actuator unit is connected to the control and/or regulation unit, and has at least one further pin, via which the additional unit is connected to the actuator unit. 4 . The control unit device as claimed in claim 1 , wherein the actuator unit has an integrated control unit which has at least one input, via which the pin for the additional unit is connected. 5 . The control unit device as claimed in claim 1 , wherein the additional unit is embodied as a sensor element. 6 . The control unit device as claimed in claim 1 , wherein the additional unit is embodied as an actuator element. 7 . The control unit device as claimed in claim 1 , wherein the plug element is embodied as an aviation-approved plug element. 8 . The control unit device as claimed in claim 1 , wherein the plug element is embodied as a D-sub 9-pin plug. 9 . A method for connecting an actuator unit and an additional unit to a control and/or regulation unit, wherein the additional unit is connected to the control and/or regulation unit via the actuator unit. 10 . An aircraft seat having a control unit device as claimed in claim 1 . 11 . The control unit device as claimed in claim 2 , wherein the plug element has at least one pin via which the actuator unit is connected to the control and/or regulation unit, and has at least one further pin, via which the additional unit is connected to the actuator unit. 12 . The control unit device as claimed in claim 2 , wherein the actuator unit has an integrated control unit which has at least one input, via which the pin for the additional unit is connected. 13 . The control unit device as claimed in claim 2 , wherein the additional unit is embodied as a sensor element. 14 . The control unit device as claimed in claim 2 , wherein the additional unit is embodied as an actuator element. 15 . The control unit device as claimed in claim 2 , wherein the plug element is embodied as an aviation-approved plug element. 16 . The control unit device as claimed in claim 2 , wherein the plug element is embodied as a D-sub 9-pin plug. 17 . An aircraft seat having a control unit device as claimed in claim 2 . 18 . The control unit device as claimed in claim 3 , wherein the actuator unit has an integrated control unit which has at least one input, via which the pin for the additional unit is connected. 19 . The control unit device as claimed in claim 3 , wherein the additional unit is embodied as a sensor element. 20 . The control unit device as claimed in claim 3 , wherein the additional unit is embodied as an actuator element.
Assignees
Inventors
Classifications
- B64D11/0639Primary
with features for adjustment or converting of seats · CPC title
characterised by the arrangement of electric motors for adjustment · CPC title
Arrangements of seats, or adaptations or details specially adapted for aircraft seats (crew seat constructions for emergency purposes B64D25/04) · CPC title
- B60N2/02246Primary
Electric motors therefor · CPC title
using sensors or detectors for detecting the position of seat parts · CPC title
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Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US2016264247A1 cover?
- The invention concerns a control unit device for an aircraft seat, with a control and/or regulating unit, with at least one actuator unit coupled to the control and/or regulating unit, and with at least one additional unit. According to the invention, the additional unit is coupled via the actuator unit to the control and/or regulating unit.
- Who is the assignee on this patent?
- Recaro Aircraft Seating Gmbh & Co Kg
- What technology area does this patent fall under?
- Primary CPC classification B64D11/0639. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Thu Sep 15 2016 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).