Integrated smart sensing systems and methods
US-2019308721-A1 · Oct 10, 2019 · US
Aeronautical equipment
US11772830B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11772830-B2 |
| Application number | US-202016824857-A |
| Country | US |
| Kind code | B2 |
| Filing date | Mar 20, 2020 |
| Priority date | Mar 27, 2019 |
| Publication date | Oct 3, 2023 |
| Grant date | Oct 3, 2023 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment.
First claim
Opening claim text (preview).
The invention claimed is: 1. An aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, wherein the aeronautical equipment includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment when the pressure in the loop drops and is at about ambient atmospheric pressure. 2. The aeronautical equipment for an aircraft according to claim 1 , wherein the closed circuit further comprises at least one evaporator associated with heating means and at least one compensation chamber. 3. The aeronautical equipment for an aircraft according to claim 2 , wherein the heating means comprise at least one heating resistance. 4. The aeronautical equipment for an aircraft according to claim 2 , wherein the compensation chamber is associated with the monitoring means. 5. The aeronautical equipment for an aircraft according to claim 4 , wherein the monitoring means comprise a pressure sensor. 6. The aeronautical equipment for an aircraft according to claim 5 , wherein the pressure sensor is located in the compensation chamber. 7. The aeronautical equipment according to claim 1 , wherein the aeronautical equipment comprises an aerodynamic measuring probe.
Assignees
Inventors
Classifications
- B64G1/506Primary
Heat pipes · CPC title
- B64D15/02Primary
by ducted hot gas or liquid · CPC title
using sensors, e.g. sun-sensors, horizon sensors · CPC title
Thermal protection, e.g. heat shields · CPC title
- B64D15/12Primary
by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title
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- What does patent US11772830B2 cover?
- This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equi…
- Who is the assignee on this patent?
- Thales Sa
- What technology area does this patent fall under?
- Primary CPC classification B64G1/506. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Oct 03 2023 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 4 related publications on this page (citations in our corpus or others sharing the same primary CPC).