# Presentation: 259897

## Technology Integration and Flight ExperimentsSATS Steering Group MeetingJune 13, 2002

**Mitch Thomas**
**Manager, TIFE Element**

## Technical Focus-SATS Operating Capabilities

- _Higher Volume Operation at Non-Towered/Non-Radar Airports._
- Enable simultaneous operations by multiple aircraft in non-radar airspace at and around small non-towered airports in near all-weather.
- _Lower Landing Minimums at Minimally Equipped Landing Facilities_
- Provide precision approach and landing guidance to small airports while avoiding land acquisition and approach lighting costs, as well as ground-based precision guidance systems such as ILS.
- _Increase Single-pilot Crew Safety and Mission Reliability._
- Increase single-pilot safety, precision, and mission completion
- _En Route Procedures and Systems for Integrated Fleet Operations._
- Provide simulation and analytical assessments of concepts that integrate SATS-equipped aircraft into higher en route air traffic flows and controlled airspace.

## 2005 Demonstration Planning

**    ****Partnership Dialogue**

**What-**
**NASA-led technical demonstration of integrated operating capabilities **
**NCAM-led public demonstration of SATS transportation services**
**Where-**
**NASA demonstration to Congress, FAA, industry  convenient to DC**
**NCAM demonstrations in states/regions funded by members**
**Why-**
**Support for certification & regulatory needs**
**Decisions on next steps on the Roadmaps**

## Roadmap

## TIFE Objectives

**Flight Test and Demonstration capability for SATS Enabling Technologies**
**SATS equipped aircraft**
**SATS ground support **
**Approved operational procedures**
**Conduct system qualification/checkout and flight test operations and acquire flight research data**
**Technology validation flight experiments**
**Proof-of-concept/integrated flight experiments**
**SATS demonstration flights**
**Facilitate Airworthiness and Safety Reviews**

## Operations Safety

**“****All NASA aircraft operations will be accomplished in airworthy aircraft by qualified flight crews in accordance with approved operational procedures.” (NPD 7900.4)**
_**Flight Test Operations and Safety Report**_
**Flight test operations will be conducted in day VMC.  Simulated IMC will accomplished with hood or foggles and flights conducted with a safety pilot.**
**Airborne research systems are ‘isolated’ from standard aircraft systems**

## Deliverables

**SATS equipped Cirrus SRXX and Lancair CXXX**
**SATS equipped Mobile Ground Support Facility**
**Flight safety releases**
**Flight research data**
**Flight demonstration of enabling technologies for HVO & LLM & SPS operating capabilities**

## TIFE WBS

**3.1** **System Engineering**
**	**3.1.1 Reviews
- 	3.1.2 AirSC Coordination
**3.2 Vehicle Integration**
**	**3.2.1 Research Flight Deck
- 	3.2.2 Telemetry and DAS
**3.3 Airspace Integration**
**	**3.3.1 CNS Architecture
- 	3.3.2 ATC Integration
- 	3.3.3 Airport Requirements
**3.4 Software and Simulation**
**	**3.4.1 Aircraft & Subsystems
- 	3.4.2 Software Reviews
**3.5 Flight Test Operations**
- 	3.5.1 Safety & Airworthiness
- 	3.5.2 Flight Test Plans

## Lancair Columbia 300  LC-40

## Cirrus SR-22

**Cirrus SR-22**

## Implementation Plan

- Start Phase I Implementation on both composite aircraft
-        At least through the experimental power installation point
-   Down select to a single aircraft for SATS HVO 1 experiment
- - July 18th : Based on workload, personnel, task difficulty,
-  parts availability, ASB & QA recommendations, aircraft availability, etc.
-   Complete first aircraft Phase I implementation
-   ICF 1st aircraft
-   Conduct SATS HVO 1 experiment
-   Complete 2nd aircraft through Phase II
-   ICF 2nd aircraft
-   Conduct SATS LLM 1 experiment

## Overall Architecture

- CAIS
- Data Acquisition
- System

- CAN Aerospace / AGATE Bus

- Video Camera(s)

**Experimental Power**

**Experimental**
**Instrumentation**

- Alternator
- Battery
- Dist. Box

- Video Recording
- &
- Distribution

- Seagull
- ADAHRS

- Pitot

- Static

- OAT

- Misc. Sensors

- CPTs
- Engine MAP, RPM

- TCP/IP

- Ashtech
- GPS/DGPS

- VHF
- D-Link

- High End
- General Purpose
- Research PC

- Network
- HUB/Switch

- AI-VDL
- Mode-SATS

- RS232

- Video

- RS232

- I/F Pending
- Development

- RS232

- Airborne Internet
- VDL
- Mode-SATS

## Status

- Structural Engineering started
- Rack design and Fab technique planned, most materials on hand
- Boom design
- Antenna design
- Camera mount design
- Preliminary drawings prepared
- Dual Frequency GPS Antennas Already Installed
- Most components ordered and some in-hand
- Seagull ADAHRS In-Hand (4), Flight Hardened
- Ashtech Z-Xtreme In-Hand (2), Flight Hardened
- RFM96 DGPS Radio Modem In-Hand, Flight Hardened
- Computers Delivered
- Some Video Equipment Available From Other Projects
- Data bus equipment ordered
- CAIS Data System – Ordered
- 	- Limited Development System In-hand
- Ready to purchase Displays
- Ready to purchase power Implementation

## Cockpit Layout

- SATS HITS cockpit

- Lancair Columbia 400
- Dual Display Cockpit

- Cirrus SR-22 Cockpit

## Instrument Panel Configuration

**Baseline Requirements: 3.11.2 calls for modular approach accommodating Flat Panel Displays**
**Panels will be different for each aircraft (landscape, portrait)**
**Additional Stock Panels available for purchase from Airframe Manufacturers – for Buy then modify approach**
**Phase 1 Panel**
**Replace existing MFD with one that we can utilize for research**
**Add research power control, distribution**
**Event markers, Data Recording switches, Annunciators**
**Phase 2 **
**Wait for the good stuff – Engineering underway**
**Avidyne is developing a dual display STC for both aircraft**

## Architecture - Computers

- KVM
- Switch

- High End
- General Purpose
- Research PC #2

- VGA-LVDS

- High End
- General Purpose
- Research PC #1

- Flat
- Panel
- Display

- Display
- Computer

**Avidyne EX5000**

- VGA-LVDS

- Keyboard
-  / Mouse

- A

- B

- Normal / Research

- CAN Aerospace / AGATE Bus

**Aft Cabin Workstation**

- RS232
- Bezel Buttons

## Avidyne FlightMax EX5000

- Available in Landscape and Portrait display
- 28VDC, 6.4 pounds
- RS232, ARINC 429
- FAA awarded a Supplemental Type Certificate (STC) to install in Cirrus SR20 and SR22 aircraft
- Avidyne is developing displays for Eclipse 500 Jet
- Customizable for NASA by Avidyne
- Access to bezels buttons via serial bus
- Display can be externally driven
- Native / Research Mode Selectable

## Airborne Internet Preliminary Demonstration

**Airborne Internet Preliminary Demonstration**

- Accomplishment
- Development and demonstration of evaluation testbed for integrated communications, navigation, and surveillance architecture
- Benefits
- TTestbed enables evaluation of candidate architectures to meet future communications requirements for all NAS users
- M-service priority communications
- S-secure network communications
- P-point-to-point, point-to-multipoint, and broadcast addressing
- B-based on open standards and protocols.
- M-minimizes number of radios and antennas on an aircraft—goal is single radio for all data communications
- Plans
- UUse testbed to develop and evaluate candidate communication architectures to meet the future needs of the NAS

## Architecture – Computers (cont.)

- Net HUB

- High End
- General Purpose
- Research PC #2

- Ships GPS
- W/Flt Plan

- High End
- General Purpose
- Research PC #1

- Aural
- Annunciations

- RS232

- Ships Audio
- Panel

- TCP/IP

**VDL **
**MODE SATS**

- Pending Glenn I-CNS
- Contract

- Research Part

- CAIS
- Data Acquisition
- System

- RS232

## Cirrus Cabin Layout

- Research Pallet
- Location

- Research Power Breaker Panel

- Left rear seat
- Removed
- Save 22 lbs

## Lancair Cabin Layout

- Second shelf
- staggered for seat
- clearance

**Research Power Breaker Panel**

-  The Cargo Bay area for both aircraft is close enough
- that we can make a common sized pallet to fit both.

**Left rear seat removed **
**to Save 16 lbs**

## Summary

**These charts have only highlighted the preparation of LaRC’s two aircraft to participate in the joint NASA/NCAM flight activities**
**NCAM member organizations are equipping similarly---aircraft and ground support systems**
**A coordinated demonstration will be crafted to show the effectiveness of 4 operating capabilities to enable a future SATS**
**This is the primary product of the Program**

## Preliminary Rack Layout (Trapezoidal)

## Phase III

- Proposed Phase III
- NO Requirements delivered.

- Requirements not yet defined

- * New STC’d Displays from
- Avidyne will be available soon.
- Get engineering free
- ** Soon to be available

**SATS HVO 1 ****(high volume ops)**
- 1st Aircraft** = **Phase** **I  +  Capstone ADS-B position + Researcher Provided software

**SATS LLM 1 ****(lower landing min)**
- 2nd Aircraft = Phase II + Researcher Provided software

- 2002

- 2003

- 2004

- GA BASELINE Requirements v1.0

**Phase II**
- * Full Cockpit Impl
-  (multiple displays)
-  DAS - AGATE bus
-    Full Data List
-    TM – Data & Video
- --------------------------
-  Convert Lancair to all
- electric  instrumentation?
- ** FADEC -auto throttle
-   Get Engine params free

**Phase I**
- Basic Research Power
- Basic A/C state data-
*     **Attitude, 3-axis angular rates, *
*     **Heading, 3-axis accelerations,*
*     **Air Data, Cntl.position & trim pos*
- Generic Research Computer(s)
- Datalink -  Capstone, AInternet
- 1st Research Display MFD
- Video
- DAS – most parameters

**Phase III**
- Autopilot -Flight Controls
-                Interface

- Requirements defined but not signed

- A/C Down
- selection

**Cirrus / Lancair Implementation Phases**

## TIFE Organization

**Flight Test Operations Lead-Eric Roback**
**Planning, integration, and implementation of all flight logistics in support of flight experiment requirements including safety reviews and approvals**
**Coordinate flight activities with SATSLabs**
**Manage flight operations processes**
**Software & Simulation Lead-Victoria Chung**
**Planning, integration, and implementation of system-level modeling and simulation**
**Coordinate development of demonstration systems architecture with SATSLabs**
**Manage software processes**
**Systems Manager-Charles Howell**
**Integration of all NASA aircraft and ground systems**

## TIFE Organization

**Vehicle Integration Lead-Kevin Shelton**
**Planning, integration, and implementation of aircraft modifications and research systems for NASA aircraft**
**Coordinate aircraft avionics architecture with SATSLabs**
**Manage flight system assets**
**Airspace Integration Lead-Richard Grube**
**Planning, integration, and implementation of NASA ground systems**
**Coordinate aircraft CNS architecture with SATSLabs**
**Manage ground system assets**
**Flight Experiments Manager-Bruce Fisher**
**Systems Engineering support , including project reviews**
**Coordination with Airborne Systems Competency**
**Coordination with Airworthiness and Safety Review Board**

## FADEC – Full Authority Digital Engine Control

-  Available to both Aircraft
-  Single lever power control
-  No Mixture control

-   Access to Engine parameters
-   No Prop control

**FADEC**

**Standby**
**Alt**

## RESEARCH ANTENNAS

## GPS System

- General
- Purpose PC

- AGATE/CAN Bus

- GX-60 GPS or
- MX-20

- 1:4
- Splitter

- VHF
- D-Link

- CAIS DAS

- Video Time
- Inserter

- Ashtech
- GPS Receiver

- GPS L1/L2
- Antenna

- GPS RF
- Signal

- VHF Comm
- Antenna

- RS-232

- Seagull
- ADAHRS

- 40 db
- Amp

- General
- Purpose PC

- AGATE/CAN
- Data Bus
- Interface

- RS-232
- Data

- RS-232

- 1:2
- Splitter

- 5 VDC

- Ant Amp
- Power

## Architecture – Data Bus

- High End
- General Purpose
- Research PC #2

- High End
- General Purpose
- Research PC #1

- Seagull
- ADAHRS

- VHF
- D-Link

- NECSMini
- I/F Box

- Ashtech
- GPS/DGPS

- RS232

- RS232

- CAN Aerospace / AGATE Bus

- CAIS DAS

- I/F Pending
- Development

- NECS Micro
- I/F Box

- Expansion
- Capability

## Research Displays

**10.4” LCD -**** ****Emerging Industry Standard Size**
**High Resolution SVGA (600 x 800) Minimum**
**Sun Light Readable**
**Ruggedized for flight environment**
**Low Power (DC)**
**Programmable - Requires Software Development Support & Tools**
**Internally/Externally Driven**
**Interchangeable With Similar Size Units**
**Bezel Buttons**
**Uses: MFD, PFD, HITS, CDTI, SVS, EVS**

- What we are looking for:

## General Purpose Computer Features

- Pentium PIII 1Ghz 512MB RAM
- 2 - Compact Flash Hard Drives
- PC - EBX form factor
- small footprint - 5.75” x 8”
- low power, mobile operations
- Integrated Interfaces (Req 3.4.1.1-7)
- AGP 3D graphics Accelerator
- Dual Network 10/100 base-T
- 4 -  RS232/422 serial ports
- PCI and PC104 expansion capability
- NTSC Video output for recording
- IDE HD / FD
- Sound

## Airborne Internet - VDL Mode-SATS

**--------------------- FEATURES ---------------------**
**Freq****: ****118–137 MHz Tx, 108–137 MHz  Rx**
**Integrated CNS**
**Standard Protocols**
**250 Aircraft, 50nm Radius**** **
**Bit Rate****: ****19.2 Kbps per active channel**
**Modulation: Binary GFSK/FM**
**Message length: 192 bits**
**Address: 24+3 (ICAO addr+source desig)**
**ADS-B: Yes; resolution to 1 meter**
**Tx Power: 43-44.5 dBm hi, 39-40.5 dBm low**
**Receiver MTL: < -103 dBm**
**Polarization: Vertical**
**Mess Tx rate: 1, 2, 5, or 10 per sec. Per chan**
**Access Techniq: TDMA (75 slots/sec/chan)**
**RF Channel: 2 Chans defined (min config)**

**------------- AI APPLICABILITY ------------**
**Real-time critical communications: Yes**
**Broadcast Capability: Yes**
**Point-to-point: Yes**
**Air-to-air: Yes**
**TCP/IP protocol: Yes**
**ATN protocol: Yes, under ICAO validation**
**Remote operation w/o ground station: Yes,  all comm services, including air-to-air comm relay defined**
**Other: Data compression, encryption and authentication services supported. Multiple channel operation permits applications to be assigned to independent 25 KHz channels with channel resource assignment conducted on the global common signaling and position reporting channels.**

## Seagull ADAHRS Installation

- Lancair - Electronic Equipment Bay
- Cirrus - Equipment Rack
- Magnetometer Location -
- Bonded in wings near access panels

## Capstone System

- MX-20
- MFD

- RS-422

- RS-232

- RS-232

- RS-232

- VHF

- GPS

- Static Port

- 966 MHz
- ADS-B
- TIS-B
- FIS-B
- WxR
- User Data

- Can be used as stand
- alone Data Link

- GBT

- UAT

- GX-60

- MX-20

## Capstone System – Cirrus SR-22

- MX-20
- MFD

- RS-422

- RS-232

- RS-232

- GPS

- Static Port

- 966 MHz
- ADS-B
- TIS-B
- FIS-B
- WxR
- User Data

- Equipment Rack

## Capstone System - Lancair

- MX-20
- MFD

- RS-422

- RS-232

- RS-232

- RS-232

- VHF

- GPS

- Static Port

- 966 MHz
- ADS-B
- TIS-B
- FIS-B
- WxR
- User Data

- Avionics Stack

- Equipment Rack

## Common Airborne Instrumentation System (CAIS)

**Designed by DoD for the purpose of facilitating commonality of flight instrumentation between aircraft types and interoperability between flight test facilities.**
**Commercial off the shelf (COTS) equipment**
**Available in several form factors**
**Modular**
**Scaleable**
**Flexible**
**Self contained data recorder.**
**Flight qualified hardware.**
**Environmental Specifications**
**Operating temperature:  -35****°**** C to +80****°**** C**
**Random Vibration:  15grms, 20 to 200Hz, 10 minutes any axis**
**Acceleration:  25g, indefinite duration, any axis**
**Humidity:  5-95% relative humidity, non-condensing**

## Instrumentation System Sensor Architecture

_**Surface Measurements**_
- Ailerons, Elevator, Rudder,   Flaps
- All CPT Transducers

- _Engine Parameters_
- Throttle (CPT)           Mixture (CPT)
- Engine RPM(MAG) Manifold Pressure

_**Pilot Control Input **__**(CPT’s)**_
- Pitch (Side Arm Controller)
- Roll (Side Arm Controller)
- Yaw (Rudder Pedals)

_**Air Data Boom**_
- Alpha, Beta
- Total and Static Pressure

_**Motion**__** – Pak**_
- 3-Linear Accelerations
- 3-Angular Rates

_**Aircraft Attitudes**_

- Discrete Inputs Inc. Data Rec. Functions (switch closure)

- Seagull ADAHRS

- OAT Sensor

- CAIS DATA SYSTEM

## Instrumentation Layout

- Eng. Manifold Pressure
- Throttle Setting (CPT)
- Prop Pitch Setting(CPT)
- Engine RPM(Mag. Pick-up)

- Surface Control Inputs (CPT)
- Pitch&Roll Stick, Rudder Peddles

- Flap Surface CPT

- Aileron Surface CPT

- Air Data Boom
- Inc. x-ducers

- Pallet

- Cabin Event Markers & Various Status Discretes

- DAS

- Rudder & Elevator Surface CPT’s

- Outside Air Temp. Sensor

## Cirrus Wingtip Boom Installation

-  Removable wing tip
-  Purchased another tip
-  Have installation plan
-    to mount boom in tip
-  Static Calibration
-     initially

## Video System Equipment Components

**Sony DSR-V10 MiniDV Digital Video Recorders (3)**
**Sekai Video Time Inserter (1)**
**Elmo MN30 CCD Camera/CCU Combination (3)**
**Miniature Video Distribution Amps (4)**
**Miniature Video Switches (1)**
**LANC Remote Controller (1)**
**Camera Cables**
**Variety of Lenses**
**Optional Hi Res Video Camera & CCU**

## Digital Video Recording System

- GPS RF

- Audio 1,2

- Research Display
- CGI Computer 1
- CGI Computer 2
- Aux NTSC Video

- 28 VDC

- Remote Control (LANC)

- 12 VDC

- NTSC Video

- Optional Hi Res Camera/CCU

- Tail

- Cabin 2

- Cabin 1

- Telemetry

- Video system is re-configurable
- by changing cable connections

## Architecture - Research Power

**Separate 28VDC research power bus for isolation from ships power**
**Req. 3.9.1-3**
**Single point shut off**
**Req. 3.9.4**
**Will use certified parts where possible**
**Selected North Coast Technologies to implement Experimental Power**

- Additional
- Alternator

- xVdc

- Alternator
- Controller

- Small 28V
- Battery

- Pilots
- Disconnect
- Switch

- Power Distribution
- / Breaker Panel

- Research Power
-  to Equipment

- 28V Experimental
- Ground Power

- 12Vdc