Cockpit pressurization and oxygen warning system
View Patent ↗A cockpit pressurization and oxygen warning system includes a cabin pressure input and an aircraft pressure input. A pilot interface includes a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic esthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted. A control circuit that is responsive to the cabin pressure input and the aircraft pressure input determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude. The control circuit asserts the first signal when the cabin altitude is within the acceptable range and asserts the second signal when the cabin altitude is not within the acceptable range.
1. A cockpit pressurization and oxygen warning system in an aircraft flown by a pilot and having an aircraft altitude and a cabin altitude, comprising:
(a) a cabin pressure input;
(b) an aircraft pressure input;
(c) a pilot interface including a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic aesthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted; and
(d) a control circuit that is responsive to the cabin pressure input and the aircraft pressure input that determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude and that asserts the first signal when the cabin altitude is within the acceptable range and that asserts the second signal when the cabin altitude is not within the acceptable range,
wherein the pilot interface further comprises an electronic display and a manual mode input, and
wherein mode input comprises a button that, when depressed, asserts a mode signal sensed by the control circuit, wherein when the mode signal is asserted the control circuit causes the electronic display to cycle to a display mode selected from a plurality of display modes including: a numerical cabin altimeter; a numerical cabin altimeter with rolling numbers; and a bar graph representation of cabin altitude over time.
2. A cockpit pressurization and oxygen warning system in an aircraft flown by a pilot and having an aircraft altitude and a cabin altitude, comprising:
(a) a cabin pressure input;
(b) an aircraft pressure input;
(c) a pilot interface including a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic aesthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted; and
(d) a control circuit that is responsive to the cabin pressure input and the aircraft pressure input that determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude and that asserts the first signal when the cabin altitude is within the acceptable range and that asserts the second signal when the cabin altitude is not within the acceptable range,
wherein the pilot interface further comprises an electronic display and a manual mode input, and
wherein the control circuit generates an indicator shown on the electronic display that indicates a cabin altitude state selected from a list of states consisting of: acceptable signified by the letters “OK”, fluctuating signified by the letters “FLUC,” above desired range signified by the letters “HI” and below desired range signified by the letters “LO.”
3. The cockpit pressurization and oxygen warning system of claim 1 , wherein the electronic display comprises an organic light emitting display.
4. The cockpit pressurization and oxygen warning system of claim 1 , further comprising an integrated pressure transducer that inputs a signal indicative of cabin pressure to the cabin pressure input.
5. The cockpit pressurization and oxygen warning system of claim 1 , wherein the aircraft includes a static pressure port and wherein the aircraft pressure input is configured to be coupled to an air line from the static pressure port.
6. The cockpit pressurization and oxygen warning system of claim 1 , wherein the aircraft includes an electronic static pressure sensor and wherein the aircraft pressure input is configured to receive a signal from the electronic static pressure sensor.
7. The cockpit pressurization and oxygen warning system of claim 1 , wherein the first visual indicator comprises a first light emitting device that emits light of a cool color and wherein the second visual indicator comprises a second light emitting device that emits light of a warm color.
8. The cockpit pressurization and oxygen warning system of claim 1 , wherein the first visual indicator comprises a first light emitting device that emits light in a first shape and wherein the second visual indicator comprises a second light emitting device that emits light in a second shape different from the first shape.
9. The cockpit pressurization and oxygen warning system of claim 8 , wherein the first shape includes a circular shape and wherein the second shape includes a triangular shape.
10. The cockpit pressurization and oxygen warning system of claim 1 , wherein the electronic display is configured to display a numerical cabin altimeter.
11. The cockpit pressurization and oxygen warning system of claim 1 , wherein the electronic display is configured to display a hatched region in a region in which information is not displayed, thereby facilitating recognition of low values by the pilot.
12. The cockpit pressurization and oxygen warning system of claim 2 , wherein the first visual indicator comprises a first light emitting device that emits light of a cool color and wherein the second visual indicator comprises a second light emitting device that emits light of a warm color.
13. The cockpit pressurization and oxygen warning system of claim 2 , wherein the first visual indicator comprises a first light emitting device that emits light in a first shape and wherein the second visual indicator comprises a second light emitting device that emits light in a second shape different from the first shape.
14. The cockpit pressurization and oxygen warning system of claim 13 , wherein the first shape includes a circular shape and wherein the second shape includes a triangular shape.
15. The cockpit pressurization and oxygen warning system of claim 2 , wherein the electronic display is configured to display a numerical cabin altimeter.
16. The cockpit pressurization and oxygen warning system of claim 2 , wherein the electronic display is configured to display a hatched region in a region in which information is not displayed, thereby facilitating recognition of low values by the pilot.
17. The cockpit pressurization and oxygen warning system of claim 2 , wherein the electronic display comprises an organic light emitting display.
18. The cockpit pressurization and oxygen warning system of claim 2 , further comprising an integrated pressure transducer that inputs a signal indicative of cabin pressure to the cabin pressure input.
19. The cockpit pressurization and oxygen warning system of claim 2 , wherein the aircraft includes a static pressure port and wherein the aircraft pressure input is configured to be coupled to an air line from the static pressure port.
20. The cockpit pressurization and oxygen warning system of claim 2 , wherein the aircraft includes an electronic static pressure sensor and wherein the aircraft pressure input is configured to receive a signal from the electronic static pressure sensor.