US20030131916A1

US20030131916A1 - Heat resistant pitot tube cover

Info

Publication number: US20030131916A1
Application number: US10/047,756
Authority: US
Inventors: Michael Alexander
Original assignee: Individual
Current assignee: Individual
Priority date: 2002-01-15
Filing date: 2002-01-15
Publication date: 2003-07-17

Abstract

The present invention relates to a pitot tube cover which can be easily and securely emplaced on a hot pitot tube, and which is composed of material capable of withstanding the high temperatures found on such a pitot tube. The disclosed pitot tube cover can be formed from a multilayer laminate of heat resistant materials and a weather resistant material. The disclosed pitot tube cover also has a fastening mechanism which secures the pitot tube cover to the pitot tube. The disclosed pitot tube cover substantially covers the entire pitot tube and its associated fuselage mounting structure.

Description

BACKGROUND OF THE INVENTION

1. Technical Field

The present invention relates generally to heat resistant covers for projecting devices, and more particularly to pitot tube covers for use with pitot tubes as commonly found on aircraft.

2. Related Art

Pitot tubes are used on aircraft to measure speed and altitude. A typical pitot tube found on an aircraft measures around 25 centimeters long and has a 1 centimeter diameter. Several small holes are drilled around the outside of the pitot tube and a center hole is drilled down the long axis of the pitot tube. The outside holes are connected to one side of a pressure transducer. The center hole in the tube is kept separate from the outside holes and is connected to the other side of the pressure transducer. The pressure transducer measures the difference in pressure in the two groups of tubes by measuring the strain in a thin element using, for example, an electronic strain gauge. The pitot tube is mounted on the aircraft so that the center of the pitot tube is always pointed in the direction of travel and the outside holes are perpendicular to the center tube. On some airplanes the pitot tube is put on a longer boom sticking out of the nose of the plane, or affixed to the wing.

Pitot tubes are delicate instruments and are generally covered when the aircraft is on the ground for a significant amount of time to prevent introduction of foreign matter into the pitot tube. Pitot tube covers must be removed before the aircraft is flown to ensure proper operation of the pitot tube measurement system.

Aircraft are typically provided with means to heat the pitot tube to prevent ice formation inside the pitot tube or along the outside holes. During flight, the flow of air past and through the pitot tube can also generate high temperatures, such as, for example, up to 800° F. These temperatures pose a threat to aircraft maintenance personnel and equipment. Moreover, a pitot tube must be protected from ground based debris as soon as possible after the aircraft has landed, reflecting an appreciable concern in today's increasingly crowded airports. Therefore, there exists a need for a pitot tube cover which can be easily and securely emplaced on a hot pitot tube, and which is composed of material that capable of withstanding the high temperatures found on a pitot tube.

SUMMARY OF THE INVENTION

It is therefore a feature of the present invention to overcome the above shortcomings related to known pitot tube covers, by providing a pitot tube cover which can be easily and securely emplaced on a hot pitot tube, and which is composed of material capable of withstanding the high temperatures found on a pitot tube.

In a first general aspect, the present invention provides a heat resistant pitot tube cover comprising: a body of heat resistant material; an opening for accommodating an end of the pitot tube; a fastening mechanism to secure said body to the pitot tube; and wherein said body covers substantially the entire pitot tube.

In a second general aspect, the present invention provides a method of protecting a pitot tube with a heat resistant pitot tube cover, said method comprising: providing a body of heat resistant material and of sufficient size to substantially cover the entire pitot tube; providing an opening for accommodating an end of the pitot tube; and providing a fastening mechanism to secure said body to the pitot tube.

In a third general aspect, the present invention provides an aircraft comprising: a pitot tube assembly; and a heat resistant pitot tube cover, wherein said pitot tube cover further comprises a multilayer body including heat resistant material; an opening for accommodating an end of the pitot tube; a fastening mechanism to secure said multilayer body to the pitot tube; and wherein said body covers substantially the entire pitot tube.

The foregoing and other features of the invention will be apparent from the following more particular description of embodiments of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

The features and inventive aspects of the present invention will become more apparent upon reading the following detailed description, claims, and drawings, of which the following is a brief description. [0012]
FIG. 1 is an exploded view of an unassembled pitot tube cover in accordance with the present invention. [0013]
FIG. 2 is a perspective view of a pitot tube cover with an open cover flap in accordance with the present invention. [0014]
FIG. 3 is a perspective view of a pitot tube cover with a closed cover flap in accordance with the present invention. [0015]
FIG. 4 is a perspective view of an outer layer of a pitot tube cover in accordance with the present invention. [0016]
FIG. 5 is a perspective view of an inner layer of a pitot tube cover in accordance with the present invention. [0017]
FIG. 6 is a perspective view of a typical pitot tube for an aircraft with a pitot tube cover, in accordance with the related art, in place.[0018]

DETAILED DESCRIPTION OF THE EMBODIMENTS

The following is a detailed explanation of the pitot tube cover, and a method for using the improved pitot tube cover in embodiments of the present invention with reference to the attached drawings. It should be noted that the same reference numbers are assigned to components having approximately the same functions and structural features in the following explanation and the attached drawings to preclude the necessity for repeated explanation thereof. [0019]
FIG. 6 shows an embodiment of a typical [0020] pitot tube assembly 600 having a pitot tube 610, wherein the proximal end of the pitot tube is mounted to a flange 630. The pitot tube/flange assembly is mounted to an aircraft fuselage via a mounting plate 620. The distal end of the pitot tube 610 is freestanding to facilitate contact with the air during flight. Also shown is a pitot tube cover 640 according to the related art.
Referring to FIG. 1, an embodiment of the heat resistant [0021] pitot tube cover 100 of the present invention is shown. Heat resistant pitot tube cover 100 is constructed of a multilayer construction comprising an outer layer 110, a first intermediate layer 120, a second intermediate layer 130, and an inner layer 140. Outer layer 110 is made of a pliable, weather resistant material, such as, inter alia, leather, vinyl, plastic, naugahyde, synthetic material, or the like, and further includes a folding tab section 160. Folding tab section 160 is designed to mate, when folded over, with stationary tab section 150. A fastening mechanism, such as, inter alia, a two-part fastening mechanism which includes a male snap 155 and a female snap 165, but which could also be a hook and loop fastening system (not shown) or a mechanical fastening system, is located on corresponding portions of stationary tab section 150 and folding tab section 160. The fastening mechanism is located so as to secure the heat resistant pitot tube cover 100 to a pitot tube (not shown).
First [0022] intermediate layer 120 is constructed of a heat resistant material such as, inter alia, KEVLAR fabric, silica fabric, or carbon fabric. Typical carbon fabrics are capable of withstanding temperatures up to about 3000° F., while typical KEVLAR fabric is able to withstand temperatures up to about 650° F. Typical silica fabric is capable of withstanding temperatures up to about 2300° F. Second intermediate layer 130 is also constructed of a heat resistant material such as, inter alia, KEVLAR fabric, silica fabric, or carbon fabric. Similarly, inner layer 140 is also constructed of heat resistant material such as, inter alia, KEVLAR fabric, silica fabric, or carbon fabric. The first intermediate layer 120, second intermediate layer 130, and inner layer 140 may be constructed from the same or different materials.
The heat resistant [0023] pitot tube cover 100 is formed when outer layer 110, first intermediate layer 120, second intermediate layer 130, and inner layer 140 are combined to form a single multilayer composite. These layers 110, 120, 130, 140 may be combined by known fastening methods, such as, inter alia, sewing, adhesive, thermal bonding, mechanical devices, or the like.
The multilayer composite is folded along axis A-A to form the heat resistant [0024] pitot tube cover 200 shown in FIG. 2. A fastening method, such as that used to combine the various layers 110, 120, 130, 140 into a single multilayer composite, is used secure the edge 210 of the heat resistant pitot tube cover 200 from about point 220 to about point 230. A pocket is thus formed into which a pitot tube may be inserted, which protects the pitot tube from damage and which also protects personnel and equipment from the high temperature surface of the pitot tube. This construction leaves an opening (not shown) under folding tab section 160 through which a pitot tube (not shown) can be inserted into the heat resistant pitot tube cover 200.
Once a pitot tube has been inserted into the heat resistant [0025] pitot tube cover 200, folding tab section 160 may be folded over and secured via a fastening mechanism as described supra, resulting in the heat resistant pitot tube cover 300 represented in FIG. 3. Thus, the pitot tube and its mounting flange are substantially completely enclosed by the heat resistant pitot tube cover 300, and potential damage to personnel or equipment from the hot surfaces of the pitot tube is minimized.
In one embodiment, the first [0026] intermediate layer 120, second intermediate layer 130, and inner layer 140 are each formed in the pattern shown in FIG. 5. The outer layer 110 is formed in the pattern shown in FIG. 4. Note that in this embodiment, the folding tab section 160 is formed only in the outer layer 110. In an alternative embodiment, any or all of the first intermediate layer 120, second intermediate layer 130, and inner layer 140 could be formed in the same pattern as the outer layer 110.
Embodiments of the present invention have been disclosed. A person of ordinary skill in the art would realize, however, that certain modifications would come within the teachings of this invention. Therefore, the following claims should be studied to determine the true scope and content of the invention. [0027]

Claims

What is claimed is:

1. A heat resistant pitot tube cover comprising:

a body of heat resistant material;

an opening for accommodating an end of the pitot tube;

a fastening mechanism to secure said body to the pitot tube; and

wherein said body covers substantially the entire pitot tube.

2. The heat resistant pitot tube cover of claim 1, wherein the body further comprises a laminated material.

3. The heat resistant pitot tube cover of claim 2, wherein the laminated material comprises:

an outermost layer of weather resistant material, having an inner surface;

an innermost layer of heat resistant material, having an inner surface;

a first mid layer of heat resistant material, said first mid layer located adjacent said inner surface of said outermost layer; and

a second mid layer of heat resistant material, said second mid layer located adjacent said inner surface of said innermost layer.

4. The heat resistant pitot tube cover of claim 3, wherein the outermost layer of weather resistant material is selected from the group consisting of leather, naugahyde, plastic, vinyl, or synthetic material.

5. The heat resistant pitot tube cover of claim 3, wherein the innermost layer of heat resistant material is selected from the group consisting of carbon fabric, silica fabric, and KEVLAR fabric.

6. The heat resistant pitot tube cover of claim 3, wherein the first mid layer of heat resistant material comprises carbon fabric, silica fabric, or KEVLAR fabric.

7. The heat resistant pitot tube cover of claim 3, wherein the second mid layer of heat resistant material comprises carbon fabric, silica fabric, or KEVLAR fabric.

8. The heat resistant pitot tube cover of claim 1, wherein the body comprises a single piece of material.

9. The heat resistant pitot tube cover of claim 1, wherein the fastening mechanism comprises a male snap piece and a female snap piece.

10. A method of protecting a pitot tube with a heat resistant pitot tube cover, said method comprising:

providing a body of heat resistant material and of sufficient size to substantially cover the entire pitot tube;

providing an opening for accommodating an end of the pitot tube; and

providing a fastening mechanism to secure said body to the pitot tube.

11. The method of claim 10, wherein said body comprises a laminated material.

12. The method of claim 11, wherein the laminated material comprises at least one layer of material selected from the group consisting of carbon fabric, silica fabric, and KEVLAR fabric.

13. The method of claim 10, wherein:

the pitot tube has a proximal end which is operatively attached to an aircraft;

the pitot tube has a distal end which is free standing; and further wherein

protecting the pitot tube further comprises placing the pitot tube cover over the pitot tube starting from the distal end and securing the pitot tube cover proximate the proximal end, so that the pitot tube cover encloses substantially all of the pitot tube.

14. The method of claim 13, wherein securing the pitot tube cover comprises closing said fastening mechanism, so that the pitot tube cover remains firmly in place.

15. An aircraft comprising:

a pitot tube assembly; and

a heat resistant pitot tube cover, wherein said pitot tube cover further comprises a multilayer body including heat resistant material; an opening for accommodating an end of the pitot tube; a fastening mechanism to secure said multilayer body to the pitot tube; and wherein said body covers substantially the entire pitot tube.

16. The aircraft of claim 15, wherein said multilayer body further comprises at least one layer of heat resistant material selected from the group consisting of carbon fabric, silica fabric, and KEVLAR fabric.