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US 7,350,752 B2Granted
Fairing and installation methodology for sensor pressure belts
AssigneeThe Boeing Company
InventorsLarry C. Paradis, Steven B. Brown, Matt R. Dickerson
Life of this patent
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AssigneeThe Boeing Company
InventorsLarry C. Paradis, Steven B. Brown, Matt R. Dickerson
Estimating the term…
A fairing system developed to reduce the flow disturbance around sensor elements allowing accurate measurement of the pressure distribution on an airplane exterior surface. The fairing also protects the sensors and electronics of the pressure belt from direct exposure to airflow.
A fairing system comprising:
A fairing assembly configured for use with a multisensor pressure measurement system having at least one pressure module, the fairing assembly comprising:
Dependencies are inferred from the claim text.
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From the US filing history. Foreign family members aren’t listed.
Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or…
Structures or fairings not otherwise provided for
Measuring force, stress, torque, work, mechanical power, mechanical efficiency, or fluid pressure
Aeroplanes
Term ended 3 Jan 2026 (estimated)
1. Field of the Invention
This invention relates generally to a fairing system developed to reduce the flow disturbance around sensor elements allowing accurate measurement of the pressure distribution on an airplane exterior surface.
2. Related Art
The accompanying drawings are included to provide further understanding of the invention, illustrate various embodiments of the invention, and together with the description serve to explain the principles and operation of the invention. In the drawings, the same components have the same reference numerals. The illustrated embodiment is intended to illustrate, but not to limit the invention. The drawings include the following Figures:
FIG. 1 is a simplified top view of the fairing system in accordance with an embodiment of the present invention;
FIG. 2 is a simplified sectional view of the fairing system of FIG. 1 in accordance with an embodiment of the present invention;
FIG. 1 is a simplified view of fairing system 100 in accordance with an embodiment of the present invention. Fairing system 100 includes a fairing assembly 102 having an outer fairing body 104 defined by aero wedges 106 and 108 formed about a central access portion 110. Fairing assembly 102 also includes a substrate 206 and CRES (corrosion resistant steel) sheet 208. Generally, disposed within central access portion 110 is at least one pressure sensing element 112 for analyzing physical parameters of flight data. In one embodiment, pressure sensing element 112 is coupled to belt segment 114, which locates at least one pressure sensing element 112 at the required measurement location.
Fairing assembly 102 is configured to cover pressure sensing element 112 and belt segment 114 by being made to contour to the electronics on belt segment 114. Fairing assembly 102 provides access at appropriate locations to allow for the measurement of pressure.
Fairing body 104 is shaped such that when installed on an airplane surface it minimizes the flow disturbance across pressure sensing element 112 allowing an accurate measurement of the local pressure. Fairing body 104 can be made of any suitable material, for example, stainless steel shim stock.