ANTI-ICING SYSTEM FOR AIRCRAFT
Assignee
Boeing
Filed as: BOEING COMPANY, THE
Filed
Dec 29, 1989
Granted
May 19, 1992
Location
SEATTLE WA US
Abstract
An anti-icing system for leading edges of an aircraft. Hot compressed air is discharged from a cavity behind the leading edge, through a multitude of small holes in the leading edge skin into the airflow impinging on the leading edge. In a first embodiment the anti-icing system utilizes part of the air distribution system in existence for a laminar flow control system. Instead of sucking air into the wing, as is done in the laminar flow control mode, the flow is reversed in the anti-icing mode, blowing hot compressed air out of the wing. In a second embodiment the anti-icing system is used solely in the anti-icing mode.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Sep 14, 1990
Rescinded
Dec 31, 1990
Duration
3 months
Inventor
- 1PETER K. C. RUDOLPH
Record Details
- Patent number
- US 5114100
- Application
- 07458847
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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