Pressurized air systems for aircraft and related methods
US-2019383220-A1 · Dec 19, 2019 · US
Systems and methods for gas generator for pneumatic deicer
US12134477B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-12134477-B2 |
| Application number | US-202217856334-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jul 1, 2022 |
| Priority date | Mar 30, 2022 |
| Publication date | Nov 5, 2024 |
| Grant date | Nov 5, 2024 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.
First claim
Opening claim text (preview).
What is claimed is: 1. A pneumatic deicing system, comprising: a deicing boot assembly, wherein the deicing boot assembly comprises a pneumatic deicing boot; and a gas generator fluidly coupled to a pressure regulator of the deicing boot assembly and electrically coupled to a power supply, wherein the power supply is configured to send a first electric pulse into the gas generator, and wherein the gas generator comprises: a propellant storage unit further comprising a sodium-based propellant, and a combustion chamber further comprising an ignitor, the ignitor configured to contact the propellant and to supply a second electric pulse to the propellant, wherein the second electric pulse is configured to pass through the propellant, and a residual collector coupled to the combustion chamber, wherein the sodium-based propellant is configured to be transferred from the propellant storage unit to the combustion chamber, wherein the propellant is configured to decompose in response to the second electric pulse passing through the propellant, and wherein the decomposed propellant is configured to be liberated as a high pressure gas. 2. The pneumatic deicing system of claim 1 , wherein the high pressure gas is a high pressure nitrogen gas, wherein the gas generator is configured to direct the high pressure gas from the combustion chamber to the deicing boot assembly. 3. The pneumatic deicing system of claim 1 , wherein the pneumatic deicing boot is coupled to a leading edge of an aircraft wing. 4. The pneumatic deicing system of claim 1 , wherein the pneumatic deicing boot of the deicing boot assembly further comprises a plurality of ridges.
Assignees
Inventors
Classifications
- B64D15/04Primary
Hot gas application · CPC title
- B64D15/166Primary
using pneumatic boots · CPC title
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Frequently asked questions
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- What does patent US12134477B2 cover?
- Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and m…
- Who is the assignee on this patent?
- Goodrich Corp
- What technology area does this patent fall under?
- Primary CPC classification B64D15/04. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Nov 05 2024 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 6 related publications on this page (citations in our corpus or others sharing the same primary CPC).