Adsys Controls Proprietary Information

September 13, 2017

Brian S. Goldberg

Beaconless FSO Challenges and Terminal Design

2

Company Summary

• Founded in 2003

• Commercial and government services & products

• Focused on cutting edge enabling technology

• Headquarters in Irvine, CA

• System concept to product delivery

Sensing – Controls – Autonomy

3

Company Technology Areas

Payloads and Laser Systems Aircraft Flight Control

HWIL Simulation & Test Systems Avionics, Processors, Sensors

CUAS

Systems

Precision

Pointing Gimbals

High

Energy

Laser

Weapons

Ground/Air

Laser

Nav/Comm

Systems

Autopilots

Full Vehicle

Automated

HWIL Test

21

Thermal_Out

20

Elec_Out

19

Fuel_Out

18

Payload_Out

17

Comm_Out

16

Altim_Out

15

AOAAOS_Out

14

AirData_Out

13

IRU_Out

12

NAV2_Out

11

NAV_Out

10

Net_Out

9

Launcher_Out

8

ACT_Out

7

EOM_Out

6

Envir_Out

5

Ground_Out

4

Control_Out

3

Mass_Out

2

Engine_Out

1

Aero_Out

EOM

Mass

Sim

uBlox_out

uBlox Navigator

Elec

Engine

Sim

Thermal_Out

Thermal Management

ACT

Sim

Env ir

control

Pilot Control

EOM

Sim

Pay load_Out

Payload

EOM

Mass

Sim

Nov Atel_out

Novatel OEMV-3 NavigatorEOM

Sim

Net_Out

Net Recovery

Engine

Control

Sim

Mass_Out

Mass Model

Sim

Aero

Engine

Mass

EOM

Launcher_Out

Launcher

EOM

Mass

IRU_out

IRU

[Net]

[Aero][Sim]

[Ground]

[Control]

[Envir]

[EOM]

[Therm]

[Elec]

[Mass]

[Payload]

[Comm]

[AirData]

[Altim]

[AOA_AOS]

[Fuel]

[IRU]

[NAV]

[NAV2]

[Launch]

[ACT]

[Engine]

Ground_Out

Gear Model

Env ir

Engine

Sim

Fuel_Out

Fuel System

[Engine]

[Therm]

[Elec]

[Sim]

[Engine]

[Aero]

[Elec]

[Fuel]

[Payload]

[Comm]

[Altim]

[AOA_AOS]

[AirData]

[IRU]

[Engine]

[Comm]

[Ground]

[Payload]

[Fuel]

[Sim]

[Engine]

[Envir]

[Sim]

[Sim]

[Sim]

[EOM]

[EOM]

[Sim]

[Sim]

[Sim]

[Sim]

[EOM]

[Envir]

[Sim]

[Envir]

[Control]

[EOM]

[Envir]

[ACT]

[Control]

[NAV2]

[Sim]

[Mass]

[EOM]

[Sim]

[NAV]

[Mass]

[EOM]

[Net]

[Sim]

[Sim]

[EOM]

[Launch][Launch]

[Mass]

[Engine]

[Envir]

[Mass]

[EOM]

[Envir]

[Sim]

[Ground]

[Control]

[Envir]

[EOM]

[Aero]

[Engine][Mass]

[Engine]

[Mass]

[EOM]

[ACT]

[EOM]

[Aero]

[Control]

[Engine]

[Envir]

[Sim]

[Aero]

[Sim]

[EOM]

[Mass]

[Sim]

Aero

Engine

Launch

Ground

Mass

Env ir

SimInit

EOM_Out

Equations of Motion

EOM

Sim

Env ir_out

Environmental Model

Control

Env ir

EOM

Sim

Engine_Out

Engine Model (fwB)

Engine

Comm

Pay load

Fuel

Sim

Elec_Out

Electrical Power1

EOM

Sim

Comm_Out

Comm System

EOM

Sim

Altimeter_Out

Altimeter

Env ir

Sim

Air_Data_out

Air Data

Env ir

Control

Engine

EOM

Mass

Aero_out

Aero Model (fwB)

Sim

hinge_mom

Actuators_Out

Actuators

Env ir

Sim

AOA_AOS_Out

AOA AOS

6

Engine Inputs

5

Nav Inputs

4

Envir Inputs

3

Discrete Events

2

Initial Conditions

1

Actuator Inputs

<sim_eng>

Sim

<sim_nav >

<sim_ev ents>

<sim_init>

<sim_act>

<sim_env ir>

High Fidelity

Aircraft

Simulation

Models

High Definition

Video

Processors

Aquila Flight Control

System Design

Many Other

Fixed Wing &

Rotorcraft FCS

Developments

Low SWaP Airborne

DAA Sensors

Optical

Simulators

Target Signature Model

Atmospheric Radiometric

Model

Background/Clutter-clear sky-clouds-terra in

RadianceDue to atmosphereAnd background

Transmittance

RadianceNoise:

-Shot noise-readout noise-fixed pattern noise-NEP-Dark Current

contrast signal

+

Camera Model

To Sensor Processing

MTF blur

CN2 Turbulence

SNRassociated

with

Synthetic Scene

÷

+fx

Mathematical Operation

Models

Optics Radiance

Applied to whole image

Atmospheric and Target Model

Input Model Parameters

Infrared Search

& Track (IRST)

Sensors

4

Laser System Heritage

High Energy Laser Weapon Systems Freespace Optical Communication

Laser SensorsLaser Navigation

Airborne Laser (ABL)

Tactical High Energy Laser (THEL)

Synthetic Aperture

LADAR for Tactical

Imaging (SALTI)

Integrated RF & Optical Communications (iROC)

Laser Aided Navigation

System (LANS)

Laser Aided Recovery

System

ABL Ranging

System

6” Laser

Designator

Payload

Laser DAA

Sensor

• Light transmission light times of

minutes requires beaconless

configuration

• Deep Space missions typically ONLY

require one-directional high

bandwidth datalinks for mission data

collection

• Pointing requirements of ~ 1urad

(jitter and biases)

• Minimal operational limitations

through sun/moon impingements

5

Needs for Deep Space FSO Applications

• NASA Phase III SBIR Program

• Team Composition

6

iROC Team

Prime Contractor

Optical Terminal Design & Analysis

Star Catalog generation, X-Ray Navigation Support

Orbital Dynamics Analysis

Requirements Support

7

iROC Optical Terminal Key Program Objectives

• Development of an integrated RF and Optical terminal design to

facilitate substantial comm. bandwidth gain with minimal mass

increase over RF-only system

• Stand-alone terminal that is modular allowing integration into a

number of spacecraft (relatively) independent of s/c bus

architecture

• Robust design offering high reliability for long term missions (>5

year mission objective: 2 year science objective + 3 year relay

objective)

• Initial focus on Mars mission, with extensibility to longer range

(e.g. Jovian) missions

8

Key Requirements and Design Constraints

• Integrated RF-Optical terminal places constraints on the optical design

envelope

– Use of the primary reflector design RF prescription constrains speed of

primary/secondary optical system

• < 4 µrad pointing accuracy (2 µrad objective) – dictated by link budget and

ground terminal capability

• Communication Laser output beam diffraction of 9 µrad

• Terminal mass objective ~30 kg

• Low cost design

9

Top-level Program Challenges / Risks

• High precision pointing requirements will be difficult to meet in the presence of error sources:

– Bias/drift from mechanical deformations induced by thermal environment

– Platform jitter disturbances (RW imbalance forces/torques, etc.)

– Launch environment mechanical shifts

– Inertial sensor bias/drift

• Pointing performance requirement compliance with a low-SWaP solution

• Stressing geometric scenarios will complicate tracking CONOPS and cause stray light issues:

– Sun near/in telescope FOV

– Small point-ahead angle puts Earth near/in telescope FOV

• RF reflector configuration constraint impacts design trade space:

– Secondary structure length/rigidity vs. secondary/primary obscuration size

– Comm beam shape dealing with telescope secondary mirror obscuration

10

What Was Performed by Adsys Controls

Optical Terminal

Architectural Design

Detailed Optical Design

Detailed Mechanical Design

Algorithmic Implementation

Dynamic Simulation

Performance Assessment

-400

-300

-200

-100

0

100

-300

-200

-100

0

100

200

300

400

500

-1500

-1000

-500 0

500

1000

1500

2000

2500

mm

mm

10 20 30 40 50 60 70 80 90 100

0

5

10

x 10-4 Roll, E

max = 8.1769e-07 rad, E

rms = 2.3338e-07 rad

,

rad

Star tracker

Matlab Estimate

True

Simulink Estimate

10 20 30 40 50 60 70 80 90 100

-2

0

2

4

6

8

x 10-4 Pitch, E

max = 9.9958e-07 rad, E

rms = 2.6663e-07 rad

,

rad

10 20 30 40 50 60 70 80 90 100

-4

-2

0

2

4

6

8x 10

-4 Yaw, Emax

= 1.5915e-06 rad, Erms

= 6.1835e-07 rad

,

rad

Time, s

Pointing Performance

Jitter Budgets

Pointing Bias Budgets

System Availability Analysis

11

Beaconless FSO Design Summary

• Innovative optical design performed

• Algorithm design for PAT/jitter control retired significant risks

• Validated required performance via high fidelity simulation

Summary

• Beaconless pointing via celestial referencing

• Incorporated low-SWaP-C star trackers on optical platform

• Efficient optical design

• Robust operations through Moon/Sun interference cases

Key Design Aspects