IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0508620
(2006-08-22)
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등록번호 |
US-7334467
(2008-02-26)
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발명자
/ 주소 |
|
출원인 / 주소 |
- Honeywell International, Inc.
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대리인 / 주소 |
Ingrassia Fisher & Lorenz
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인용정보 |
피인용 횟수 :
8 인용 특허 :
11 |
초록
▼
An air data module is provided that is relatively small, lightweight, low cost, uses relatively low power, and is relatively easy to install, test, and maintain. The air data module includes a housing that is adapted to be mounted to an external surface of an aircraft, and includes at least a sensor
An air data module is provided that is relatively small, lightweight, low cost, uses relatively low power, and is relatively easy to install, test, and maintain. The air data module includes a housing that is adapted to be mounted to an external surface of an aircraft, and includes at least a sensor compartment and an interface electronics compartment formed therein. A pitot-static probe is coupled to the housing and extends therefrom, and has a static pressure passageway that is in fluid communication with the sensor compartment. A plurality of static pressure ports are formed in the pitot-static probe and are in fluid communication with the static pressure passageway. A pitot pressure inlet port is formed in a distal end of the pitot-static probe. A static pressure sensor and a differential impact or absolute pitot pressure sensor, for example, may be mounted within the module and used to sense static pressure and impact or pitot pressure, respectively. The disclosed configuration makes the module less sensitive to a relatively high pressure pulse.
대표청구항
▼
What is claimed is: 1. An integrated air data module, comprising: a housing adapted to be mounted to an external surface of an aircraft, and including at least a sensor compartment and an interface electronics compartment formed therein, the sensor compartment isolated from the interface electronic
What is claimed is: 1. An integrated air data module, comprising: a housing adapted to be mounted to an external surface of an aircraft, and including at least a sensor compartment and an interface electronics compartment formed therein, the sensor compartment isolated from the interface electronics compartment; a pitot-static probe coupled to the housing and extending therefrom, the pitot-static probe having at least an inner surface, an outer surface, and a distal end spaced apart from the housing, the inner surface defining a static pressure passageway that is in fluid communication with the sensor compartment a plurality of static pressure ports extending between the pitot-static probe inner and outer surfaces, and in fluid communication with the static pressure passageway; a pitot pressure inlet port in the pitot-static probe distal end. 2. The module of claim 1, further comprising: a pitot pressure conduit disposed at least partially within, and at least partially surrounded by, the pitot-static probe static pressure passageway, the pitot pressure conduit having a passageway formed therein that fluidly couples the pitot pressure inlet port to the sensor compartment. 3. The module of claim 1, wherein: the housing further includes an upstream end and a downstream end; and the pitot-static probe extends from the housing at least proximate the housing upstream end and at a predetermined angle relative to the surface on which the housing is adapted to mount. 4. The module of claim 3, wherein: the surface on which the module is adapted to mount is configured to be disposed over a range of angles of attack when the aircraft is in flight; and the predetermined angle is at least substantially equal to the mean of the range of angles of attack range. 5. The module of claim 3, wherein: the surface on which the module is adapted to mount is configured to be disposed over a range of angles of attack when the aircraft is in flight; and the predetermined angle is at least substantially equal to the median of the range of angles of attack range. 6. The module of claim 1, further comprising: an absolute pressure sensor mounted within the housing sensor compartment and configured to sense static pressure in the housing sensor compartment; and a differential pressure sensor mounted within the housing sensor compartment and configured to sense a differential pressure between the static pressure in the housing sensor compartment and total pressure in the pitot pressure passageway. 7. The module of claim 6, further comprising: a circuit extending between the sensor compartment and the interface electronics compartment and electrically coupled to both the absolute pressure sensor and the differential pressure sensor. 8. The module of claim 7, wherein the circuit is configured to determine at least one or more of static pressure (Ps), impact pressure (Qc), total pressure (Pt), mach number, calibrated airspeed, and altitude based at least in part on the sensed static pressure and the sensed differential pressure. 9. The module of claim 6, further comprising: an input/output (I/O) connector extending through the housing and into the interface electronics compartment, the I/O connector coupled to the circuit and configured to electrically couple the circuit to a data interface external to the housing. 10. The module of claim 1, wherein the pitot pressure conduit comprises a substantially flexible tube. 11. The module of claim 1, wherein the housing is constructed at least partially of a polymer material. 12. The module of claim 1, wherein the housing is at least partially plated with a material that provides electromagnetic shielding. 13. The module of claim 1, wherein the pitot pressure inlet port has a cross section flow area that converges from a first cross sectional flow area to a second cross section flow area. 14. The module of claim 1, wherein: when the module is mounted on the external surface of the aircraft, the pitot-static probe has at least a top side, a bottom side, a left side, and a right side; and each static pressure port is located on the pitot-static probe right side, the pitot-static probe left side, or both. 15. An integrated air data module, comprising: a housing adapted to be mounted to an external surface of an aircraft, and including at least a sensor compartment and an interface electronics compartment formed therein, the sensor compartment isolated from the interface electronics compartment; a pitot-static probe coupled to the housing and extending therefrom, the pitot-static probe having at least an inner surface, an outer surface, and a distal end spaced apart from the housing, the inner surface defining a static pressure passageway that is in fluid communication with the sensor compartment; a plurality of static pressure ports extending between the pitot-static probe inner and outer surfaces, and in fluid communication with the static pressure passageway; a pitot pressure inlet port in the pitot-static probe distal end; an absolute pressure sensor mounted within the housing sensor compartment, the absolute pressure sensor in fluid communication with the housing sensor compartment and configured to sense static pressure therein; and a differential pressure sensor in fluid communication with the static pressure passageway and the pitot pressure inlet port and configured to sense a differential pressure there-between. 16. The module of claim 15, wherein the differential pressure sensor is mounted within the sensor compartment, and wherein the module further comprises: a pitot pressure conduit disposed at least partially within, and at least partially surrounded by, the pitot-static probe static pressure passageway, the pitot pressure conduit having a passageway formed therein that fluidly couples the pitot pressure inlet port to the differential pressure sensor. 17. The module of claim 15, wherein the differential pressure sensor is mounted within the pitot pressure inlet. 18. The module of claim 15, wherein: the aircraft on which the housing is configured to mount is designed for a predetermined flight profile; the absolute and differential pressure sensors are each exposed to a predetermined overpressure magnitude prior to the aircraft commencing flight; the absolute pressure sensor is designed for a full scale pressure range that is based on the predetermined overpressure magnitude; and the differential pressure sensor is designed for a full scale differential pressure range that is based on the predetermined flight profile of the aircraft and is not based on the predetermined overpressure magnitude. 19. The module of claim 15, wherein: the housing further includes an upstream end and a downstream end; and the pitot-static probe extends from the housing at least proximate the housing upstream end and at a predetermined angle relative to the surface on which the housing is adapted to mount; the surface on which the module is adapted to mount is configured to be disposed over a range of angles of attack when the aircraft is in flight; and the predetermined angle is at least substantially equal to the mean of the range of angles of attack range. 20. The module of claim 15, wherein: the housing further includes an upstream end and a downstream end; and the pitot-static probe extends from the housing at least proximate the housing upstream end and at a predetermined angle relative to the surface on which the housing is adapted to mount; the surface on which the module is adapted to mount is configured to be disposed over a range of angles of attack when the aircraft is in flight; and the predetermined angle is at least substantially equal to the median of expected angle of attack range. 21. The module of claim 15, further comprising: a circuit extending between the sensor compartment and the interface electronics compartment and electrically coupled to both the absolute pressure sensor and the differential pressure sensor, the circuit configured to determine at least mach number, calibrated airspeed, and altitude based at least in part on the sensed static pressure and the sensed differential pressure; and an input/output (I/O) connector extending through the housing and into the interface electronics compartment, the I/O connector coupled to the circuit and configured to electrically couple the circuit to a data interface external to the housing. 22. The module of claim 15, wherein the pitot pressure inlet port has a cross section flow area that converges from a first cross sectional flow area to a second cross section flow area. 23. A method of providing air data sensor performance from pressure sensors used with an aircraft having a predetermined flight profile, and following exposure of the sensors to a predetermined overpressure magnitude, the method comprising the steps of: using an absolute pressure sensor to sense static pressure at a position on the aircraft, the absolute pressure sensor being designed for a full scale pressure range that is based on the predetermined overpressure magnitude; using a differential pressure sensor to sense impact pressure at the position on the aircraft by sensing a differential pressure between total pressure and static pressure at the position on the aircraft, the differential pressure sensor being designed for a full scale pressure range that is based on the predetermined flight profile of the aircraft and is not based on the predetermined overpressure magnitude; and determining one or more air data parameters based at least in part on the sensed static pressure and the sensed impact pressure.
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