AIRCRAFT CABIN COMFORT CONTROL SYSTEM

• US 3,861,624 A
• Filed: 02/16/1973
• Issued: 01/21/1975
• Est. Priority Date: 02/16/1973
• Status: Expired due to Term

• Current Assignee: William P. Lear
• Original Assignee: William P. Lear
• Inventors: Lear, William P.
• Primary Examiner(s): Blix, Trygve M.
• Assistant Examiner(s): Barefoot, Galen L.
• Application Number:
  US05/333,146
• Time in Patent Office: 704 Days
• Field of Search: 244/118P,118R,1R 236/91E,91G,78C 62/DIG.5 98/1.5
• US Class Current: 244/118.5
• CPC Class Codes: B64D 13/08 the air being heated or cooled
• CPC Class Codes: Y10S 62/05 Aircraft cooling

Abstract

An automatic temperature control system that maintains passenger comfort levels in aircraft when flying at high altitude. A fuselage skin sensor relays significant temperature changes of the ambient air about the plane to the system temperature controller. Heat transfer into the cabin is thereby smoothly compensated and controlled to predetermined level, during sustained operation in very cold environments. The amount of compensation is adjustable; its operation and control, close with comfortable results.

Claims

1. An automatic control system for conditioning air ducted into the cabin section of a high altitude Flying plane, comprising:

a heat sensor bridge that includes first and second units located in the cabin section that are responsive to the temperature therein;

a third sensor unit attached to a portion of the fuselage skin that is directly responsive to the temperature of the very cold air outside of the plane and is substantially insulated from cabin temperature;

control means responsive to the electrical output of said sensor bridge and of said third sensor unit, said control means including a reversible motor-actuator operable in accordance with a preset temperature condition for the ducted air; and

heat exchange means responsive to the operation of said motor-actuator to effect and substantially maintain the air at said preset temperature in the cabin section during flight;

said third sensor unit being circuitally connected in said bridge in a manner to anticipate inside air control action for said motor-actuator in accordance with outside air temperature change, said heat exchange means including first ducting for engine hot bleed air, a cross-counterflow heat exchanger coupled with said first ducting, second ducting routing cold ram air into said heat exchanger, a damper in the second ducting for controlling the rate of ram air flow into the heat exchanger under control of said motor-actuator, and third ducting coupling the heat exchanger output as conditioned air to the cabin section.