Patrick Moynihan

US Patent:

6915687, Jul 12, 2005

Filed:

Jul 1, 2003

Appl. No.:

10/611708

Inventors:

Roger D. Foster - Burnsville MN, US
Paul F. Heine - Eagan MN, US
Patrick J. Moynihan - Lakeville MN, US
David G. Owens - Bloomington MN, US

Assignee:

Rosemount Aerospace Inc. - Burnsville MN

International Classification:

G01P013/00

US Classification:

7317002

Abstract:

A static pressure sensing probe has an aerodynamically shaped cross section, and extends laterally from an aircraft surface sufficiently so that an outer end of the probe is a short distance outside the boundary layer on the aircraft surface on which the probe is mounted. The probe has surface corrugations or ridges along the probe, and the ridges include an upstream ridge adjacent the leading edge, and a downstream ridge spaced rearwardly from the upstream ridge. The ridges cause pressure disturbances along the probe surfaces. Static pressure sensing ports are positioned on the surfaces of the probe relative to the ridges in regions of pressure disturbances caused by the ridges. The probes can be mounted on opposite sides of the aircraft and pneumatically or electrically connected to average the pressures from selected sets of ports.

US Patent:

7597018, Oct 6, 2009

Filed:

Apr 11, 2007

Appl. No.:

11/786225

Inventors:

Scott Joseph Braun - Lakeville MN, US
Patrick John Moynihan - Lakeville MN, US
Timothy Thomas Golly - Lakeville MN, US
Alexander Nathan Reid - St. Louis Park MN, US

Assignee:

Rosemount Aerospace Inc. - Burnsville MN

International Classification:

B64D 43/00

US Classification:

738665, 73178 R

Abstract:

The invention provides a probe for an aircraft including a strut having an interior passage accommodating a plurality of pneumatic lines, a probe head extending from the strut and having at least one inlet opening communicating with the pneumatic lines, a baseplate situated below the strut for attaching the probe to the aircraft, and a manifold situated below the baseplate for communicating with the pneumatic lines, wherein the baseplate is adapted and configured so that the pneumatic lines communicating with the manifold are thermally isolated from the baseplate. The invention also provides a method of thermally isolating at least one pneumatic line in an aircraft probe.