MH-60R - DH/C&D Subsystem Flashcards
(18 cards)
Describe the operator system interface function
The operator-system interface allows for the input of data to the system by the aircrew, and for the output of data to the aircrew via the Mission and Flight Displays.
What major functions does the system perform?
- Operator system interface.
- Avionics system monitoring
- Operational control
- Information control
Describe the avionics system monitoring function
Many of the units in the avionics system have provisions for Built-In Test (BIT) and/or performance monitoring. The MC continually polls those avionics units and receives results of the BIT or performance monitoring. The MC then displays the results to aircrew in the form of equipment status, window displays, and equipment Warnings, Cautions, and Advisories (WCA). Equipment status is downlinked to the ship.
Describe the operational control function
Control commands are received by the mission display from bezel key selections (in helicopter control mode) or from the data link (in ship control mode). The MC decodes the control commands by the Avionics Operational Program (AOP), which generates instructions that are sent over the system 1553B bus to the applicable mission equipment. Typical instructions could include mode selection, tuning frequency, BIT initiate, and request for transfer of data.
Describe the information control function
The system 1553B bus provides for information ow in the avionics system. The MC acts as master bus controller, while all other avionics units tied to the system 1553B bus are considered Remote Terminals (RTs). The MC polls each RT at a prescribed interval of time. The polled RT will send data in addition to its poll response, when data is ordered by the bus controller.
List the subsystem components
Data Handling:
– Primary Mission Computer (Mission Computer)
– Backup Mission Computer (Backup Computer)
– Data Transfer Storage
– Control Monitor Panel
– Fiber channel hub
Controls and data display:
– Mission Displays
– Flight Displays
– Electronic ight instrument system (EFIS) avionics junction box
– Data concentrators (DTC)
– Control Indicator Set/Control Display Unit/Pointing Device (See Chapter 2)
– Collective grips (see MH-60R NATOPS Flight Manual)
– Cyclic grips (see MH-60R NATOPS Flight Manual)
Briefly describe the Mission Computer
The MC runs the AOP providing both mission and ight management capabilities. The MC employs two single board computers; one to handle I/O processing and one that executes the AOP. A single board graphics processor (one for each station) supports mission display and keyset/CDU/PD displays for all operators.
What are e three processors in the MC?
The Stores and Self Defense Computer (SSDC), Data Fusion Computer (DF), and the Acoustic Mission Planner computer (AMP)
How is the MC connected to other avionics equipment?
Via the 1553B bus, fiber network, ARINC 429 bus, ARINC 582 bus, and RS 422 bus.
What does the 1553B bus do?
Carries command and control information from the MC to the avionics equipment, and data and status information back to the MC.
What does the fiber channel network do?
The fiber channel provides high speed connectivity between the MC and BC. The normal operation data transfer is to back-up data to the BC in case of MC failure, plus provides data from the MC and BC to the ight displays.
What does the ARINC 582 bus do?
The ARINC 582 bus provides the data connection for the TACAN to the ight displays.
What does the RS 422 bus do?
The RS 422 bus provides connection to the keysets/CDU/PD and MC and BC. It also connects all mission displays to the MC and BC.
What does the ARINC 429 bus do?
It provides data connection for the following:
• Flight displays to each other
• Embedded GPS Inertial Navigation Systems (EGI) to the flight displays
• Air data between the flight displays and the MC and BC
• Data concentrators to the flight displays.
Briefly describe the Backup Mission computer
It is a partial backup to the MC. It consists of a single board computer that executes the flight management program (FMP) and performs I/O processing. The backup computer contains two graphics processors that provide pilot and copilot mission display and keyset/CDU/PD support (no support for SO) during MC casualty situations.
In the event of a MC failure, the system will automatically switch to the BC within one second to allow essential flight management and navigation functions to continue.
Briefly describe the Data Transfer System
houses two operator installed PC cards used to load the mission plan, data and store system diagnostics data. The mission card is used exclusively for the mission plan and the AOP, and is treated as a read only memory device by the helicopter. This is to avoid inadvertent data deletion during flight. The recovery card is used for in-flight updates of the mission plan, and as storage for the mission analysis replay data and is a read/write memory device. The DTS communicates with the BC and MC via a SCSI bus. The DTS is located on the cockpit center console.
What does the control monitor panel do?
controls power to selected mission avionics subsystems. The CMP loads, initiates, and restarts data handling subsystems. The CMP is located on the left side of the center console. The CMP provides:
• Control power to MC, BC, EGIs, mission avionics, and ASE subsystems.
• Receive status alert and fault signals from the DTS.
• Data Zero function to mission systems.
• Lamp test function.
What does the EFIS Avionics Junction box do?
The EFIS avionics junction box provides the direct interface from the ight displays to the two air data computers (ADC), two EGI, two DTC, the MC, and the BC. Fully redundant operation of each FD is accomplished through ARINC 429 interfaces such that an FD can access and display ight data in the event of a single FD, EGI, DTC or ADC failure.
