Apparatus for supporting instruments in an instrument panel
View Patent ↗According to one embodiment, a bracket configured to hold a pressure transducer comprises a body, a face plate, and one or more pressure fitting connectors. The body has a rear portion and a front portion that meet to form an angle less than 180 degrees. The face plate is coupled to the front portion of the body, and has a surface defining a plate aperture configured for a cable to pass through. The pressure fitting connectors are coupled to the rear portion of the body. Each pressure fitting connector is configured to receive a pressure hose.
1. An apparatus comprising:
a body comprising:
a rear portion having a rear portion axis; and
a front portion having a front portion axis, the front portion axis and the rear portion axis forming an angle greater than zero degrees but less than 180 degrees, the front portion comprising a brace configured to hold a pressure transducer;
a face plate coupled to the front portion, the face plate having a surface defining a plate aperture configured for a cable to pass through; and
one or more pressure fitting connectors coupled to the rear portion and the pressure transducer, each of the one or more pressure fitting connectors configured to receive a pressure hose.
2. The apparatus of claim 1 , further configured to be installed into and removed from an instrument pedestal of an aircraft cockpit, the instrument pedestal comprising a plurality of pedestal apertures, the pedestal apertures facing the aircraft cockpit, the installation and removal done from the pedestal apertures.
3. The apparatus of claim 1 , the body having:
a body height less than a pedestal aperture height; and
a body width less than a pedestal aperture width.
4. The apparatus of claim 1 , the body having:
a body height less than 3 inches; and
a body width less than 2 inches; a body width less than 2 inches.
5. The apparatus of claim 1 , the cable comprising a display connector.
6. The apparatus of claim 1 , the angle angling the rear portion towards the plate aperture.
7. The apparatus of claim 1 , the angle being between 135 and 175 degrees.
8. The apparatus of claim 1 , the one or more pressure fitting connectors comprising:
a pressure fitting connector configured to receive a static pressure hose.
9. The apparatus of claim 1 , the one or more pressure fitting connectors comprising:
a first pressure fitting connector configured to receive a static pressure hose; and
a second pressure fitting connector configured to receive a pitot pressure hose.
10. The apparatus of claim 1 , the bracket having a bracket length between 8 to 12 inches.
11. The apparatus of claim 1 , the face plate having:
a face plate height between 2 to 4 inches; and
a face plate width between 1 to 2 inches.
12. The apparatus of claim 1 , the pressure hose extension having a diameter of 1/16 to ¼ inches.
13. The apparatus of claim 1 , the bracket further comprising aluminum alloy, titanium alloy, zinc alloy, or corrosion resistant steel.
14. An avionics instrument pedestal comprising:
an altimeter bracket and an airspeed bracket, the altimeter bracket and the airspeed bracket each comprising:
a body comprising:
a rear portion having a rear portion axis; and
a front portion having a front portion axis, the front portion axis and the rear portion axis forming an angle greater than zero degrees but less than 180 degrees, the front portion comprising a brace configured to hold a pressure transducer;
a face plate coupled to the front portion, the face plate having a surface defining a plate aperture configured for a cable to pass through; and
one or more pressure fitting connectors coupled to the rear portion and the pressure transducer, each of the one or more pressure fitting connectors configured to receive a pressure hose.
15. The avionic instrument pedestal of claim 14 , the one or more pressure fitting connectors of the altimeter bracket further comprising:
a pressure fitting connector configured to receive a static pressure hose.
16. The avionic instrument pedestal of claim 14 , the one or more pressure fitting connectors of the airspeed bracket further comprising:
a first pressure fitting connector configured to receive a static pressure hose; and
a second pressure fitting connector configured to receive a pitot pressure hose.
17. The avionic instrument pedestal of claim 14 , the altimeter bracket and the airspeed bracket each having:
a body height less than a pedestal aperture height; and
a body width less than a pedestal aperture width.
18. The avionic instrument pedestal of claim 14 , the cable comprising a display connector.
19. The avionic instrument pedestal of claim 14 , the angle angling the rear portion towards the plate aperture.
20. A method comprising:
installing an apparatus into an instrument pedestal of an aircraft, the instrument pedestal comprising a plurality of pedestal apertures, the pedestal apertures facing a cockpit of the aircraft, the apparatus comprising:
a body comprising:
a rear portion having a rear portion axis; and
a front portion having a front portion axis, the front portion axis and the rear portion axis forming an angle greater than zero degrees but less than 180 degrees, the front portion comprising a brace configured to hold a pressure transducer;
a face plate coupled to the front portion, the face plate having a surface defining a plate aperture configured for a cable to pass through; and
one or more pressure fitting connectors coupled to the rear portion and the pressure transducer, each of the one or more pressure fitting connectors configured to receive a pressure hose; and
inserting the apparatus into a particular one of the plurality of pedestal apertures.