A Low Cost Modular Approach to Avionics Upgrade and CNS/ATM Compliance for the C-130 Hercules

Transcription

1 A Low Cost Modular Approach to Avionics Upgrade and CNS/ATM Compliance for the C-130 Hercules By David Green Innovative Solutions and Support

2 Typical C-130 Display Architecture

3 C-130 EIDS EIDS (Engine Instrument Display System) architecture: Two (2) 6 x 8 XGA 10.4 Diag. Viewable Displays One (1) Engine Data Concentrator Unit (EDCU) One (1) Engine Display Control Panel (EDCP) One (1) Mounting Frame EIDS can be configured as a standalone subsystem or a part of the Fully Integrated Cockpit Display System Engine Data Concentrator Unit (EDCU) is a triple redundant subsystem that supports aircraft Engine and Hydraulic interfaces EDCU interfaces with T-56A Dash 7, 9, 15 and 16 Engines DVI / RGB RS-170 Video Input Engine Sensors / GPS / Discretes DVI / RGB RS-170 Video Input Dual ARINC-429 Recorder Outputs EDCU EDCP ARINC-429 ARINC-429

4 A Modular Approach Incremental Steps to Avionics Upgrade: Phase 1 Engine Instrument Display System (EIDS) Reduce weight by 80% Replace 43 components with 4 Increase dispatch reliability Provide video display capability forward center between pilots Phase 2 Primary Flight Display System (PFD/ND) Mission Computer Information Displayed through Video input Consolidate avionics functions into Cockpit information portal Full Aircraft Systems Graphics AOA, RNP/ANP, CNS/ATM, CPDLC capability Patented zoom feature essential with complex display formats Threat Warnings Displayed during all phases of flight Including Take-off and Landing

5 A Modular Approach (Continued) Phase 3 Electronic Flight Bag (EFB) Displayed on EIDS and ND screen Maps, Charts, and Approaches Checklist execution for both normal and abnormal Phase 4 Flight Management System (FMS) Fully Integrated FMS and MCDU in a Single LRU inclusive of a modular Beta 3 WAAS GPS Receiver Control and Display for 8 External Subsystems Coupled WAAS LPV Approach and RNP to 0.1 nm

6 System Attributes Significant weight savings Reduced power consumption No forced air cooling required. Enhanced cross cockpit readability +/- 80 deg. Modular design 30% more affordable. Minimum wire changes reduces installation cost and time. Reduced software development effort and cost by factor of three (3X)

7 Patented Advanced Display Features Patented Zoom feature Enhances Readability Simplifies use of highly complex integrated display formats Patented Integrity Monitoring System tests 1,000 Critical parameters on every frame Integrity Monitoring permits integration of Critical Flight Data with Mission Situation Awareness Display Reduces Software Development Effort and Cost by factor of three (3X)

8 Primary Flight Display (PFD) PFD Functions ADI/HSI Altimeter Setting Vref Indications EGPWS/Taws Flight Plan Navigation Data Bearing Pointers Angle of Attack RNP Indications Chronograph Flight Path Vector Air Data TIS/TCAS Weather Radar

9 Navigation Display (ND) ND Functions Navigation Display HSI TIS/TCAS Weather Radar EGPWS/TAWS Flight Plan Navigation Data Bearing Pointers RNP Indications Chronograph Charts Display Video Display

10 Data Concentrator Units / Mission Computers Compact mechanical design uses latest electronic component technology and SMT printed circuit boards (3MCU or 6MCU) 100 Mbit Ethernet link to Integrated Flat Panel Display System (IFPDs) 200 v/m HIRF, Lighting MIL-STD-461, and DO-160E Section 20 Digital/Analog IOP Boards Independent Power Supplies w/ EMI suppression Configuration Module Microprocessor Usage: less than 30%; spare capacity for growth of new applications Power consumption less than 25 watts (28 VDC) Weighs less than 10 lbs Mechanical capacity exists for future growth Level A HW/SW DO254/DO178B Certified EFB Server for Airport Charts, Approach plates and En Route Charts with Ship Position

11 RNP Scales

12 Electronic Chart Server Unit Eliminates the need for onboard Laptops Displays data in the forward field of view on crew selectable Display SATCOM Interface including Datalink Weather User Customizable Normal / Abnormal Checklists and Emergency Procedures Hosts multiple 3 rd party SW applications including: PFPS Falconview Harris Map (Flight Scene) Seamless interface with IS&S FPDS and FMS Utilizes IS&S FMS for Data Entry and Cursor Control via integrated FMS touch pad Optional interface with external HMI devices FAA certified chart server for XM WXR, Jeppesen Charts, and E-Checklists

13 Caution Warning & Advisory Panel (CWAP) Co-Pilot Attention Getters Pilot Attention Getters Warning Caution FIRE Warning Caution FIRE FIRE 1 FIRE 2 FIRE 3 FIRE 4 Annunciators 60 Discrete Inputs 28VDC Prim 28VDC Sec NACELLE 1 NACELLE 2 NACELLE 3 NACELLE 4 APU FIRE SMOKE TURBINE 1 TURBINE 2 TURBINE 3 TURBINE 4 CABIN ALT PITOT HEAT 1 DOOR OPEN PITOT HEAT 2 ATVAD EIDS EWMS EDP 1 EDP 2 EDP 3 EDP 4 ANTI SKID UTIL SUCT BOOST SUCT OXY 1 OXY 2 LOX PROP OIL EGPWS TERR INOP MODE 4 AT CARP SATCOM ELEV TRIM INU FAN 2 INU FAN 2 SELCAL 1 SELCAL 2 SMOKE INHIB ELT INHIB Master Warning Master Caution Caution (LowLevel) Advisory Lighting Discrete Automatic Tone and Voice Alerting Device (ATVAD) Day / Night (NVIS) LED Technology Dual processor Technology ensures redundancy 60 discrete inputs Supports Master Caution, Master Warning and Audio (Tone) Interfaces NVIS Compatible Configuration Module Configuration Module

14 Integrated Air Data Display System CNS/ATM compliance for the C Short Term 3 hardware devices in 1 Altimeter (RVSM) Altitude Alerter Digital Air Data Computer. Air data output on Arinc 429, RS422, data and analog formats. Dedicated display of baro and static source error corrected altitude (SSEC) Digital back to analog conversion signal can be used to drive analog auto pilot. Communicates seamlessly with enhanced mode S, ADSB, mode 5 transponders Form and fit of original altimeter.

15 Data Sheets

16 Air Data Products Air Data Equipment Air Data Module (ADM) provides full digital air data computer capability with TSO C-106 and Encoded Altitude Output, TSO C-88a. Integrated Air Data Display System (IADDS) is a self-sensing RVSM compliant, digital air data computer altimeter with selectable altitude alerting. Air Data Sensors (ADS) supply an error signal to the flight control system that is proportional to HOLD or pre-selected altitude errors related to ascent and descent. The Analog Interface Unit (AIU) is used in conjunction with the Air Data Display Unit (ADDU) to provide analog interface to the autopilot, navigation systems, and other equipment. 16

17 IS&S Certifications Past and Current Military Certifications to MIL-Q-9858A, MIL-I-45208A, MIL-STD-2000A, MIL-STD , MIL-STD-498, MIL-STD-882D, DOD-STD 2167A, DOD-STD 2168, DOD-STD-2000 FAA Issued Approval to FAA FAR Part 21, Subpart O for TSO Authorizations Software Capabilities / Development to RTCA/DO-178B, Level A FAA NYACO Conducts RTCA/DO-178B Software Audits Hardware Capabilities / Development to RTCA/DO-254, Level A, Qualification to DO-160F FAA has Issued on IS&S Products More Than: 112 Technical Standard Orders (TSO) 13 Supplemental Type Certificates (STC) 12 Parts Manufacturing Approvals (PMA) FAA 14 CFR FAA Part 145 Air Agency Certificate for a Limited Instrument and Limited Accessory Repair Station, number I72R916X EASA Repair Station Number EASA Successful Aircraft Certification Systems Evaluation Program (ACSEP)

18 Thank you. Dave Green Director Business Development Military Programs