WO2016088086A1 - A data concentration unit for helicopters - Google Patents
A data concentration unit for helicopters Download PDFInfo
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- WO2016088086A1 WO2016088086A1 PCT/IB2015/059343 IB2015059343W WO2016088086A1 WO 2016088086 A1 WO2016088086 A1 WO 2016088086A1 IB 2015059343 W IB2015059343 W IB 2015059343W WO 2016088086 A1 WO2016088086 A1 WO 2016088086A1
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- WIPO (PCT)
- Prior art keywords
- data
- signals coming
- warning
- discrete
- concentration unit
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/382—Information transfer, e.g. on bus using universal interface adapter
- G06F13/387—Information transfer, e.g. on bus using universal interface adapter for adaptation of different data processing systems to different peripheral devices, e.g. protocol converters for incompatible systems, open system
Definitions
- the present invention relates to a data concentration unit which enables to convert sensor and discrete input/output warning signals coming from engine, transmission, fuel, electric and hydraulic systems on AH- IS helicopter into digital data, and to be transmitted to the mission computer of an aircraft through MIL- STD-1553 data bus for digital display on a multi-function display.
- Cockpit configurations comprising analog/mechanic indicators require the pilot to follow separate indicator for each platform data of the aircraft. Furthermore, each one of the indicators should be tested and calibrated in certain intervals in terms of flight safety. In addition, since it is very difficult to repair several air platforms, acquiring indicators that have to be changed can be very difficult of impossible. For this reason, aircraft may have to wait in completely or partially unusable way during supply/repair processes of the indicators. All these problems and requirements cause extra spare part, labor and maintenance costs. Therefore both reducing sustenance and maintenance costs of the aircraft, and the pilot following up the platform data in an ergonomic and easy way get difficult.
- the objective of the present invention is to provide a data concentration unit which enables to control all information exchange on the air platform from a single center by converting sensor and discrete input/output warning signals coming from engine, transmission, fuel, electric and hydraulic systems. Therefore, weight and wiring load created by analog/mechanic indicators provided in the cockpit for each platform data and also the material supply/maintenance/labor costs are eliminated.
- the inventive data concentration unit is designed compatible with the environmental requirements determined by military standards (MIL-HDBK-5400, MIL-STD-810, MIL-STD-704 and MIL-STD-461), furthermore the former air platforms having analog cockpit can be transformed into digital cockpit used in modern air platforms of today by means of the data concentration unit, and it can be enabled that the additional functions are integrated in a fast way by means of software design realized with open architecture techniques.
- Figure 1 is the schematic view of the data concentration unit.
- Warning panel discrete warning signal inputs 4. Warning light discrete warning signal inputs
- a data concentration unit (1) which is adapted to convert the analog signals coming from various sensors into digital data and to transmit these digital data to the central unit in order to control all information exchange on an air platform from a single central unit (for example from a mission computer (T)), essentially comprises
- At least one MIL-STD- 1553 data bus (7) which provides a connection interface for transmitting parametric flight data converted into digital data to a mission computer (T) that will process these data,
- test and software interface (8) which provides a connection interface for performing software update and test.
- inventive data concentration unit (1) there are analog indicator signal inputs (2) for various analog signals related with the flight parameters coming from various sensors provided on an aircraft (for example AH- 1S helicopter).
- twenty two signals coming from a main warning panel which is a different display panel from the multi-function display (MFD) on the pilot and copilot panel, and four signals coming from pilot metal chip detector panel enter through the warning panel discrete warning signal inputs (3).
- MFD multi-function display
- pilot metal chip detector panel there is an engine chip detector, XMSN chip detector, 42° chip detector and 90° chip detector, and these detectors send warning signals in case the broken metal parts due to the wearing of moving parts exceed a certain limit.
- warning lamp discrete warning signal input having four discrete signal inputs, and signals coming from fire warning lamp to be shown in multi-function display as on/off (for example as 28V/GND) enter through two of these inputs. Signals coming from low RPM warning lamp as on/off enter through the other two of the said four discrete signal inputs when the cycle of the rotor is under a certain RPM or it is normal.
- auxiliary discrete warning inputs and outputs (5) in order to meet the various number of warning signal requirements of different air platforms using a jet turbine engine, and five auxiliary discrete signals enter through these outputs and four auxiliary discrete signals go out.
- RS-232 communication channels (6) there are two RS-232 communication channels (6), and these channels can be used for data communication for different purposes and applications in different air platforms.
- the digital data converted by the data concentration unit (1) are transmitted to a mission computer (T).
- These incoming helicopter data are processed by the said mission computer (T), and shown on the multi-function displays (MDF).
- the said mission computer (T) examines all helicopter sensor and warning information supplied by the data concentration unit (1), and generates required audio and visual warnings for the data outside the usual limits to the pilot. Therefore, the pilot can follow all warnings related with the helicopter from a single display without requiring examining all indicators one by one. By this means, it becomes easier for pilot to follow the data and the work load is decreased.
- test and software interface (8) for testing data concentration unit (1) and software upload/update in a preferred embodiment of the invention.
- test and software interface (8) it is possible to upload the up-to-date software directly through the air platform without demounting the inventive data concentration unit (1).
- the data concentration unit (1) By means of the design of the data concentration unit (1) realized with open architecture techniques, it is enabled that the additional functions can be integrated fast in future.
- the data concentration unit (1) is essentially designed for AH- IS helicopter; it can also be used in other similar air platforms after a software change through test and software interface (8). Therefore it enables to convert the older air platforms with analog cockpit into digital cockpit used in modern air platforms of today.
- Cooling process in the inventive data concentration unit (1) is realized with natural convection. By this means, it is enabled that the energy consumption and failure rate of the product is less that the similar products (Mean Time Between Failure - MTBF being high). Since there is no fan in the designed data concentration unit (1), there is no risk that the air channels close during the placement of the unit in the aircraft. Therefore, it provides more flexible placement possibility to the designer. Furthermore, since there is no fan in the data concentration unit (1), acoustic noise is not generated which will negatively affect the sound level.
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Abstract
The present invention relates to a data concentration unit (1), which is adapted to convert the analog signals coming from various sensors into digital data and to transmit these digital data to the central unit in order to control all information exchange on an air platform from a single central unit, essentially comprising analog indicator signal inputs (2) for analog indicator data entry related with various flight parameters to be converted into digital data, at least one warning panel discrete warning signal inputs (3) for the entry of discrete warning signals coming from a main warning panel and/or a pilot metal chip detector panel, at least one warning lamp discrete warning signal input (4) for the entry of the signals coming from low RPM and/or fire warning lamp, at least one auxiliary discrete warning signal input and output (5) for meeting various numbers of warning signal requirements of different air platforms, at least two communication channels (6), at least one MIL-STD-1553 data bus (7) which provides a connection interface for transmitting parametric flight data converted into digital data to a mission computer (T) that will process these data, at least one test and software interface (8) which provides a connection interface for performing software update and test.
Description
DESCRIPTION
A DATA CONCENTRATION UNIT FOR HELICOPTERS Field of the Invention
The present invention relates to a data concentration unit which enables to convert sensor and discrete input/output warning signals coming from engine, transmission, fuel, electric and hydraulic systems on AH- IS helicopter into digital data, and to be transmitted to the mission computer of an aircraft through MIL- STD-1553 data bus for digital display on a multi-function display.
Background of the Invention Sensor and discrete input/output warning signals coming from engine, transmission, fuel, electric and hydraulic systems of aircrafts are directly connected to analog and/or mechanical indicators in pilot/copilot cockpits. However, these data are not suitable to be directly used in Multi-Function Displays that are being used in cockpits of modern aircrafts.
Cockpit configurations comprising analog/mechanic indicators require the pilot to follow separate indicator for each platform data of the aircraft. Furthermore, each one of the indicators should be tested and calibrated in certain intervals in terms of flight safety. In addition, since it is very difficult to repair several air platforms, acquiring indicators that have to be changed can be very difficult of impossible. For this reason, aircraft may have to wait in completely or partially unusable way during supply/repair processes of the indicators. All these problems and requirements cause extra spare part, labor and maintenance costs. Therefore both reducing sustenance and maintenance costs of the aircraft, and the pilot following up the platform data in an ergonomic and easy way get difficult.
The Problems Solved with the Invention
The objective of the present invention is to provide a data concentration unit which enables to control all information exchange on the air platform from a single center by converting sensor and discrete input/output warning signals coming from engine, transmission, fuel, electric and hydraulic systems. Therefore, weight and wiring load created by analog/mechanic indicators provided in the cockpit for each platform data and also the material supply/maintenance/labor costs are eliminated.
The inventive data concentration unit is designed compatible with the environmental requirements determined by military standards (MIL-HDBK-5400, MIL-STD-810, MIL-STD-704 and MIL-STD-461), furthermore the former air platforms having analog cockpit can be transformed into digital cockpit used in modern air platforms of today by means of the data concentration unit, and it can be enabled that the additional functions are integrated in a fast way by means of software design realized with open architecture techniques.
Detailed Description of the Invention
A data concentration method developed to fulfill the objectives of the present invention is illustrated in the accompanying figure, in which:
Figure 1 is the schematic view of the data concentration unit.
The components shown in the figures are each given reference numbers as follows:
1. Data concentration unit
2. Analog indicator signal inputs
3. Warning panel discrete warning signal inputs
4. Warning light discrete warning signal inputs
5. Auxiliary discrete warning signal inputs and outputs
6. Communication channel
7. MIL-STD- 1553 data bus
8. Test and software interface
T. Mission computer
A data concentration unit (1), which is adapted to convert the analog signals coming from various sensors into digital data and to transmit these digital data to the central unit in order to control all information exchange on an air platform from a single central unit (for example from a mission computer (T)), essentially comprises
analog indicator signal inputs (2) for analog indicator data entry related with various flight parameters to be converted into digital data,
- at least one warning panel discrete warning signal inputs (3) for the entry of discrete warning signals coming from a main warning panel and/or a pilot metal chip detector panel,
at least one warning lamp discrete warning signal input (4) for the entry of the signals coming from low RPM and/or fire warning lamp,
- at least one auxiliary discrete warning signal input and output (5) for meeting various numbers of warning signal requirements of different air platforms,
at least two communication channels (6),
at least one MIL-STD- 1553 data bus (7) which provides a connection interface for transmitting parametric flight data converted into digital data to a mission computer (T) that will process these data,
at least one test and software interface (8) which provides a connection interface for performing software update and test. In a preferred embodiment of the inventive data concentration unit (1), there are analog indicator signal inputs (2) for various analog signals related with the flight
parameters coming from various sensors provided on an aircraft (for example AH- 1S helicopter). One of the signals coming from engine oil pressure sensor, signals coming from engine oil temperature sensor, signals coming from transmission oil pressure sensor, signals coming from transmission oil temperature sensor, signals coming from sensor measuring the fuel amount remaining in the fuel tank, signals coming from the fuel pressure sensor, signals coming from a torque meter for showing the horse power drawn from the engine as torque pressure, signals coming from a generator ampermeter and a generator voltmeter for determining over current and voltage, signals coming from turbine gas temperature sensor, signals coming from a double tachometer related to rotor RPM and engine RPM data, and signals coming from a gas generator tachometer related to RPM values of a gas generator turbine as percentage, or plurality of these enter from the said analog indicator signal inputs (2). In a preferred embodiment of the invention, twenty two signals coming from a main warning panel which is a different display panel from the multi-function display (MFD) on the pilot and copilot panel, and four signals coming from pilot metal chip detector panel enter through the warning panel discrete warning signal inputs (3).
In one embodiment of the invention there are twenty two discrete warning signals; Engine Oil Press ", "Caution_l ", "Engine Oil Bypass", "Caution 2 ", "FWD Fuel Boost", "Aft Fuel Boost", "Engine Fuel Pump ", "%10 Fuel", "Fuel Filter", "Gov Enter", "XMSN Oil Bypass", "XMSN Oil Press", "XMSN Oil Hot", "Hyd Press #1 ", "Hyd Press #2 ", "Inst Inverter", "DC Generator", "Ext Power", "Chip Detector", "Caution_3 ", "Master Caution Light" and "Test Caution "; and discrete inputs are defined for these twenty two warning signals.
In one embodiment of the invention, on the said pilot metal chip detector panel; there is an engine chip detector, XMSN chip detector, 42° chip detector and 90°
chip detector, and these detectors send warning signals in case the broken metal parts due to the wearing of moving parts exceed a certain limit.
In one embodiment of the invention, there is a warning lamp discrete warning signal input (4) having four discrete signal inputs, and signals coming from fire warning lamp to be shown in multi-function display as on/off (for example as 28V/GND) enter through two of these inputs. Signals coming from low RPM warning lamp as on/off enter through the other two of the said four discrete signal inputs when the cycle of the rotor is under a certain RPM or it is normal.
In one embodiment of the invention, there are auxiliary discrete warning inputs and outputs (5) in order to meet the various number of warning signal requirements of different air platforms using a jet turbine engine, and five auxiliary discrete signals enter through these outputs and four auxiliary discrete signals go out.
In one embodiment of the invention, there are two RS-232 communication channels (6), and these channels can be used for data communication for different purposes and applications in different air platforms.
By means of the MIL-STD-1553 data bus (7) present in a preferred embodiment of the invention, the digital data converted by the data concentration unit (1) are transmitted to a mission computer (T). These incoming helicopter data are processed by the said mission computer (T), and shown on the multi-function displays (MDF). The said mission computer (T) examines all helicopter sensor and warning information supplied by the data concentration unit (1), and generates required audio and visual warnings for the data outside the usual limits to the pilot. Therefore, the pilot can follow all warnings related with the helicopter from a single display without requiring examining all indicators one by one. By this means, it becomes easier for pilot to follow the data and the work load is decreased.
There is a test and software interface (8) for testing data concentration unit (1) and software upload/update in a preferred embodiment of the invention. By means of the test and software interface (8), it is possible to upload the up-to-date software directly through the air platform without demounting the inventive data concentration unit (1).
By means of the design of the data concentration unit (1) realized with open architecture techniques, it is enabled that the additional functions can be integrated fast in future. The data concentration unit (1) is essentially designed for AH- IS helicopter; it can also be used in other similar air platforms after a software change through test and software interface (8). Therefore it enables to convert the older air platforms with analog cockpit into digital cockpit used in modern air platforms of today.
By means of the CBIT (Continuous Built-in Test) ability which the inventive data concentration unit (1) has, the said unit reports the status of the components thereon; therefore fast precautions can be taken for possible problems that can occur before and during flight.
Cooling process in the inventive data concentration unit (1) is realized with natural convection. By this means, it is enabled that the energy consumption and failure rate of the product is less that the similar products (Mean Time Between Failure - MTBF being high). Since there is no fan in the designed data concentration unit (1), there is no risk that the air channels close during the placement of the unit in the aircraft. Therefore, it provides more flexible placement possibility to the designer. Furthermore, since there is no fan in the data concentration unit (1), acoustic noise is not generated which will negatively affect the sound level.
Claims
A data concentration unit (1), which is adapted to convert the analog signals coming from various sensors into digital data and to transmit these digital data to the central unit in order to control all information exchange on an air platform from a single central unit, essentially characterized by
analog indicator signal inputs (2) for analog indicator data entry related with various flight parameters to be converted into digital data, at least one warning panel discrete warning signal inputs (3) for the entry of discrete warning signals coming from a main warning panel and/or a pilot metal chip detector panel,
at least one warning lamp discrete warning signal input (4) for the entry of the signals coming from low RPM and/or fire warning lamp, at least two communication channels (6),
at least one MIL-STD-1553 data bus (7) which provides a connection interface for transmitting parametric flight data converted into digital data to a mission computer (T) that will process these data.
A data concentration unit (1) according to claim 1, characterized by analog indicator signal inputs (2) from which one of the signals coming from engine oil pressure sensor, signals coming from engine oil temperature sensor, signals coming from transmission oil pressure sensor, signals coming from transmission oil temperature sensor, signals coming from sensor measuring the fuel amount remaining in the fuel tank, signals coming from the fuel pressure sensor, signals coming from a torque meter for showing the horse power drawn from the engine as torque pressure, signals coming from a generator ampere meter and a generator voltmeter for determining over current and voltage, signals coming from turbine gas temperature sensor, signals coming from a double tachometer related to rotor RPM and engine RPM data, and signals coming from a gas generator tachometer related to
RPM values of a gas generator turbine as percentage, or plurality of these enter.
A data concentration unit (1) according to claim 1, characterized by at least one auxiliary discrete warning signal input and output (5) for meeting the various number of warning signal requirements of different air platforms.
A data concentration unit (1) according to claim 1, characterized by at least one test and software interface (8) which provides a connection interface for software update and test.
A data concentration unit (1) according to claim 1, characterized in that it is adapted to report the status of the components thereon by means of its CBIT ability.
A data concentration unit (1) according to claim 1, characterized in that it is cooled via natural convection.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TR2014/14649 | 2014-12-04 | ||
| TR201414649 | 2014-12-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2016088086A1 true WO2016088086A1 (en) | 2016-06-09 |
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|---|---|---|---|
| PCT/IB2015/059343 WO2016088086A1 (en) | 2014-12-04 | 2015-12-04 | A data concentration unit for helicopters |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005106378A1 (en) * | 2004-04-26 | 2005-11-10 | Raytheon Company | Launcher with dual mode electronics |
| US20100070674A1 (en) * | 2008-09-15 | 2010-03-18 | Raytheon Company | Smart translator box for agm-65 aircraft "maverick" analog interface to mil-std-1760 store digital interface |
| US20110054721A1 (en) * | 2007-02-16 | 2011-03-03 | Intelligent Automation Corporation | Vehicle monitoring system |
-
2015
- 2015-12-04 WO PCT/IB2015/059343 patent/WO2016088086A1/en active Application Filing
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005106378A1 (en) * | 2004-04-26 | 2005-11-10 | Raytheon Company | Launcher with dual mode electronics |
| US20110054721A1 (en) * | 2007-02-16 | 2011-03-03 | Intelligent Automation Corporation | Vehicle monitoring system |
| US20100070674A1 (en) * | 2008-09-15 | 2010-03-18 | Raytheon Company | Smart translator box for agm-65 aircraft "maverick" analog interface to mil-std-1760 store digital interface |
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