Closed-loop cabin pressure control system test method with actual pressure feedback

• US 7,686,680 B2
• Filed: 11/14/2007
• Issued: 03/30/2010
• Est. Priority Date: 06/26/2007
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Hilzendeger, Timothy J., Biss, Timothy C., Horner, Darrell W.
• Primary Examiner(s): Patel; Ramesh B
• Application Number:
  US11/940,151
• Publication Number:
  US 20090006056A1
• Time in Patent Office: 867 Days
• Field of Search: 700/203, 700/301, 454 70- 74, 244/59, 244/90.B, 244/99.6
• US Class Current: 454/71
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems

Abstract

Testing of an aircraft pressure control system may be performed without use of an altitude chamber. Aircraft cabin configuration date may be modeled and used, along with high resolution positional feedback from a simulated valve, to produce a high resolution electrical signal that may represent a simulated cabin pressure. A voltage-to-pressure transducer may convert the electrical signal to a pneumatic signal. The pneumatic signal may be employed to operate a cabin-pressure controller under test. The controller may operate an outflow valve actuator and an attached potentiometer. The potentiometer may produce a feedback signal and closed-loop testing of the aircraft pressure control system may thus be performed. The outflow valve actuator may be operated without being attached to an outflow valve because a simulated aerodynamic load may be applied to the actuator.

Claims

1. A method for testing aircraft cabin-pressure controllers, comprising the steps of:

simulating cabin-pressure;

producing an electrical cabin-pressure signal;

converting the electrical cabin-pressure signal to a pneumatic cabin-pressure signal;

applying the pneumatic cabin-pressure signal to a controller-under-test;

operating the controller-under-test responsively to the pneumatic cabin-pressure signal; and

producing an electric feedback responsively to operation of the controller-under-test to provide closed-loop testing of the controller-under-test.

2. The method of claim 1 wherein the step of simulating cabin pressure is performed without use of an altitude chamber.

3. The method of claim 1 further comprising:

producing an electrical altitude simulation signal; and

producing pneumatic signaling to the controller-under-test so that it operates responsively to both the pneumatic cabin pressure signal and the altitude simulation signal.

4. The method of claim 1 further comprising:

modeling aircraft configuration data in digital format; and

wherein the step of producing the electrical cabin-pressure signal is performed responsively to the configuration data and positional feedback from an outflow valve simulator.

5. The method of claim 1 wherein step of producing an electric feedback comprises operating an actuator of an outflow valve and an attached potentiometer to produce an electrical signal that is responsive to operation of the controller-under-test.

6. The method of claim 5 wherein:

the step of operating the actuator is performed with a simulated aerodynamic load applied to the actuator; and

the step of operating the actuator is performed without actual operation of an outflow valve.

7. Apparatus for performing testing of aircraft cabin-pressure controllers comprising:

a cabin pressure simulator for producing an electrical simulated cabin-pressure signal;

a self-contained transducer for converting the electrical simulated cabin-pressure signal to a pneumatic cabin-pressure signal for application to a controller-under-test,

an outflow valve actuator that is operated by the controller-under-test;

a detector for producing a detector signal responsive to position of the output valve actuator; and

wherein the detector signal is directed to the cabin pressure simulator so that closed-loop testing of the controller-under-test is provided.

8. The apparatus of claim 7 wherein:

the cabin pressure simulator has at least 16-bits of analog resolution; and

the detector can receive an analog signal with at least 16-bits of analog resolution.

9. The apparatus of claim 7 further comprising:

a processor that models aircraft configuration data; and

wherein the cabin-pressure simulator produces the electrical simulated cabin-pressure signal responsively to the aircraft configuration data and positional feedback of the outflow valve actuator.

10. The apparatus of claim 7 wherein the transducer comprises;

a proportioning valve to receive an electrical pressure signal;

a jet pump for producing vacuum in the proportioning valve;

an inlet for positively pressurized air; and

an outlet for a pneumatic pressure signal.