Proposers_Day_Presentation_FBO_Distribute.pdf

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Control of Revolutionary Aircraft with Novel Effectors (CRANE) Dr. Alexander “Xander” Walan Program Manager, DARPA TTO

Proposers Day Program Overview

26 August 2019

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DARPA X-Planes: A Brief History Program Vision Active Flow Control (AFC) Defined Previous DoD AFC Efforts Program Overview Potential AFC Designs and Mission Space Program Technology Challenges Proposal Information and Dates Expectations of Performers Nominal Program Plan and Schedule Phase 0: Concept Design Phase 1: Preliminary Design Phase 2: Detailed Design Phase 3: Build, Integration, Test Program Management Philosophy Other Considerations

CRANE: Proposers Day Outline

X-29 Grumman Forward-swept wing

Amber Leading Systems Tactical UAV

RQ-1

General Atomics Tactical UAV

1984 1988

1998 2003

NOTAR

Hughes No tail rotor

Tacit Blue NGC: Low RCS

X-45/46/47 Boeing/Northrop

UCAV

X-51 Hypersonic scramjet

Condor Boeing: HALE UAV

Global Hawk Teledyne Ryan

HALE UAV

ASTOVL/CALF

Boeing/Lockheed STOVL tech

X-31 Rockwell/MBB Maneuverability

X-50 Boeing Canard rotor wing

A-160 Frontier Systems Optimum speed rotor

HTV-2

Lockheed Hypersonic flight

1986 1988

1983-94

20111982

Historically, DARPA has developed disruptive air technologies on a consistent 2-4 year cadence

X-planes are technology demonstrations @ convincing scale; they are not prototypes & do not always have X designation

DARPA X-Planes arise in response to promising technology insights, not requirements pull

Why do experimental system demonstrations?

Rapidly demonstrate high risk / high payoff ideas Prove new enabling technologies that lead to revolutionary system concepts Extend and integrate new research & technologies to achieve significant military advantage

1990 2000 2010

DarkStar Boeing/Lockheed

LO UAV

DARPA X-Planes: A Brief History

HAWC

Hypersonic Cruise Missile

TBG

Hypersonic Cruise Missile

CRANE

Active Flow Control Aircraft

202?

Quantify Benefits:

Improved survivability Enhanced performance Novel platforms & geometries

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Compelling Capability

Stable of Enabling Tech

Demonstration Framework

Technology Mature & Demonstrated Actuators Proven CFD Codes Wind-tunnel & subscale demonstrations

Demonstration Framework:

Demonstrate Relevant Performance Scaling to Relevant Size & Environments Clean-Sheet Design / Modification

CRANE: Program Vision

Revolutionize next gen aircraft designs by incorporating active flow control (AFC) as the primary design consideration

Active Flow Control (AFC) Defined

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“Active flow control (AFC) is the on-demand addition of energy into a boundary layer for maintaining, recovering, or improving vehicle performance” - NASA Definition

Conventional Types of Flow Control − Pneumatic / Fluidic − Mechanical − Plasma

AFC Affects Flows in Numerous Ways − Alters the boundary layer of a flow − Alters the boundary conditions − Introduces / modifies vorticity − Increases circulation (Lift)

AFC Applies to both steady & unsteady flow conditions − Unsteady: Couple w/ fluid dynamic instabilities to cause a large change in pressure distribution

Small inputs into a flow {O(ε)} have large 1st order effects {O(1)}

Mechanical Vortex Generators

Plasma Dielectric Barrier Discharge (DBD) Plasma Actuator

Different actuation approaches to AFC

Different focuses on modifying flow field

AFC: Small inputs to the flow can impart large 1st order effects

Sweeping Jets Synthetic Jets

[1]

[1] Maines, Brant H. et. Al. “Comparison of Flow Control Actuators on a Diamond Wing Planform”. Lockheed Martin Corporation, Fort Worth, Texas. 2017.

[2] www.aerospaceweb.org/question/aerodynamics/q0228.shtml [3] www.semanticscholar.org/paper/Turbulent-boundary-layer-control-with-plasma- Choi-Jukes/93562f927c4d150b9f7a9af4df6456efacf54316 [4] Yang, et al. “Super-Lift Coefficient of Active Flow Control Airfoil:

What is the Limit?” AIAA, Grapevine, Texas. 2017.

[5] Viktorovich, Bulat “About the Detonation Engine”, Saint-Petersburg National Research University of Information Technologies, Saint-Petersburg, Russia, 2014.

[2] [3]

Coflow

[4]

Pulse Detonation Actuator

[5]

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Historically, AFC has been a patch fix for aircraft designs − Wake reduction (F-16 ventral fin) − Download reduction (XV-15) − Supersonic weapons separation (DARPA HIFEX) − Aero-optics (DARPA/AFRL tactical laser studies)

Previous DoD AFC Efforts

Army XV-15 Tiltrotor Download ReductionDARPA/AFRL Airborne Aero-Optical Laboratory - Transonic

AFRL Wake Reduction

DARPA HIFEX Experiment

DARPA HIFEX

AFRL Wake ReductionDARPA HIFEX

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CRANE: Program Overview

1) AFC As Primary Design Consideration Inject disruption tech into the A/C design process Fully explore the AFC trade space Address tech challenges associated w/ full scale design & integration (manned or unmanned platform) Early & frequent risk reduction Mature the tools for aircraft configuration & design

2) Affordable Approaches Leverage existing technologies / Use COTS where possible Avoid developing new non-AFC subsystems Systematic airworthiness approach

− Risk based military flight release for experimental aircraft

3) Demonstration Want An Innovative & Novel X-Plane Demonstration Fly tactically relevant maneuvers at relevant scale [1] Warsop, et Al., NATO AVT-239: Flight Demonstration of Fluidic Flight Controls on the MAGMA Subscale

Demonstrator Aircraft, AIAA SciTech, 2019 [2]. Shi, Zhiwei, Zhu, et. Al “Aerodynamic Characteristics and Flight Testing of a UAV without Control Surfaces Based on Circulation Control” ASCE, Nanjing, China, 2019.

[3] Glezer, et Al., Dynamic Flight Maneuvering Using Virtual Control Surfaces Generated by Trapped Vorticity, AFOSR Final Report, 2010

1,000

10,000

100,000

0.0 0.2 0.4 0.6 0.8 1.0

GT

OW

, l b

Mach

AVOCET MURI[3]

Rudderless UAV[2]

MAGMA [1]

CRANE area of exploration

Weight vs. Speed for Previous AFC Enabled Aircraft

Options for CRANE flight demonstration profile

A compelling demonstration of the art of the possible in 21st century aircraft design

CRANE: Potential Active Flow Control Mission Space Optimize Low Observables

No moving control surfaces − Remove need for gap seals and treatments − Maintain signature throughout flight envelope

Reduce/eliminate Outer Mold Line (OML) protrusions Enable unique unstable configurations

High Lift Applications Enhanced maneuverability

− Separation control at high angles of attack Extreme Short Takeoff and Landing (ESTOL)

− Enable “lilly padding” and mobile runway options for UCAVs or Tactical transports

Very low speed flight

Airfoil Efficiency Thick airfoil efficiency Increased lift/decreased drag Structural efficiency - reduced empty weight fraction Fuel efficiency and range improvement

Extreme High Altitude ISR Very high altitude flights (up to ~90,000 ft)

− Circulation control, lift augmentation Aircraft quieting / Maximize laminar flow, control turbulence

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X-31 - Short takeoff

With AFC

No AFC

Novel Design Space AFC enabled (S&C) Size Weight & Power (SWaP) Reliability, Maintainability &

Sustainability

[1] You, D. and Moin, P. “Study of flow separation over an airfoil with synthetic jet control using large-eddy simulation” Center for Turbulence Research, Stanford, CA, 2007.

[1] aviation.stackexchange.com/questions/15341/what-trade-offs-are-being-made-in-the-design-of-the-planform-alignment-of-stealt www.lockheedmartin.com/en-us/capabilities/c4isr/case-study-the-importance-of-intelligence-surveillance-reconnaissance.html

[2]

[2] Thomas, Flint O. “Plasma Actuators for Cylinder Flow Control and Noise Reduction.” University of Notre Dame, Notre Dame, Indiana. 2008.

CRANE Anticipated Program Technology Challenges

1) System Design Tools: Expand Aircraft Design Tool Box to Include AFC Existing CFD tools capture AFC accurately & AFC modeling/sizing tools are available Need to add AFC to Multi Domain Optimization of Alternatives (MDOA) tools Need to add AFC to flight control design tools

2) Full Scale Design & Integration: Design Based on AFC Initial design & configuration centered around AFC S&C

3D geometry & time effects need to be considered in planform design & layout AFC scaling to higher Mach # & physical sizes than previously demonstrated for aircraft S&C AFC Airworthiness: Robust & Failure Tolerant Design

3) Incorporated AFC into Flight Controls: Basic Aircraft Maneuvers Achieved with AFC CFD / Wind tunnel data needs to be accurately modeled in flight control simulations Control loop must account for hysteresis nature of active flow control & full 3D flow field Cross coupling of effectors & transient effects

Risks: Aircraft design tools, scaling to tactically relevant size & performance, flight control loop

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Draft BAA Posting: 12 August 2019 Proposers Day: 26 August 2019 Draft BAA Feedback Due Date: 02 September 2019, 11:59 (Midnight), EST Anticipated BAA Posting Date 6 September 2019 Anticipated questions Due Date: 18 September 2019, 11:59 PM (Midnight), EST Anticipated Proposal Due Date and Time: 8 November 2019 at 2 pm EST

CRANE BAA Information and Dates

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Team appropriately − Know your strengths and weaknesses − Partnerships can build excellent products

Use streamlined approaches to achieve technical, cost, and schedule objectives Work collaboratively with government

− Succeed as a team…”Program Management is a team sport” − Maturation of conceptual design − Informing testing and risk reduction plans in subsequent phases

Early identification and mitigation of realized risks Quantification of unknown technical aspects of design and how to solve them

CRANE: Expectations of Performers

CRANE: Nominal Program Plan and Schedule

Phase 0: Conceptual Design -- Focus on Clean Sheet “Art of the Possible” AFC Design Exploration (Go/No Go @ CoDR) Robust configuration exploration & trades among several concepts Focus on maturing AFC tools & design process

Phase 1: Preliminary Design -- Go/No Go @ PDR Phase 2: Detailed Design -- Go/No go prior to assembly Phase 3: Build, Integration, & Test NOTE: Multiple Awards anticipated for Phase 0 & Phase 1, exact number TBD.

FY20 FY21 FY22 FY23 FY24

Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4

Phase 0:

Conceptual Design

Phase 1:

Preliminary Design

Phase 2: Detailed Design

Phase 3: Fabrication, Assembly, & Flight Test

BAA Ph 0

Ph 3

CDR

1st FlightTRR

Ph 0 Ph 0

Ph 2

CoDR

Award PDR

Ph 1 Ph 1

Go / No Go Go /No Go

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Objective Robust conceptual design process and understanding of the trade space

− Focus on maturing the ideas − Conduct trade studies on optimal methods of implementing AFC − Extensive laboratory and simulation work to prove feasibility

Modeling and Simulation (M&S) tool Verification and Validation (V&V) Entry Criteria Phase 0 budget is $21M, awards contingent upon the quality of submissions and available funding Tentative plan is to choose up to 3 performers Exit Criteria CoDR

May include multiple concepts Identify known knowledge gaps and understanding of how to fill them

Achievable path to PDR

CRANE: Phase 0-Concept Design

FY20 FY21 FY22 FY23 FY24

Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4

Phase 0:

Conceptual Design

Phase 1:

Preliminary Design

BAA Ph 3 CDR 1st Flight

Ph 0

TRRPh 0 Ph 0

Ph 2 CoDR

Ph 1 Ph 1 PDR

Award

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Objectives Performer will present system conceptual baseline Review the results of any trade studies completed Review system-level specification(s)

Tasks Technology conceptual design is complete and the approach is shown to be feasible through initial analysis A pathway to the preliminary design is identified System baseline technologies for flow control are identified System baseline approach to flight control loop is identified Model and Simulation methods to verify the 3D flow field are identified and required enhancements or modifications required are identified Initial multi-disciplinary analysis and optimization (MDAO) results are presented Design support analysis and data from all design disciplines, to support the selected final design Projected performance capabilities against demonstration profile Release the final conceptual design drawing package (3-view, inboard profiles) Initial program schedule to include planned testing and analysis timelines and envisioned phase 1, 2, and 3 demonstration methodology

CRANE: Phase 0 Concept Design Review (CoDR)

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Wind tunnel and bench testing as required to support preliminary design Develop system demonstration plan Requirement and design reviews Updated BAA for phase 2 & 3 Conduct subsystem tests at relevant scales for V & V

− Analytical predictions, control loop analyses, M & S Entry Criteria Selected concept from CoDR Exit Criteria Systems Requirements Review (SRR) Preliminary Design Review (PDR) Achievable path to CDR

CRANE: Phase 1-Preliminary Design

FY20 FY21 FY22 FY23 FY24

Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4

Phase 0:

Conceptual Design

Phase 1:

Preliminary Design

BAA Ph 0 Ph 3 CDR 1st FlightTRRPh 0

Ph 0

Ph 2 CoDR

Award

Ph 1 Ph 1 PDR

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Objective Requirements Development - Requirements are complete and preliminary interfaces are defined Design Status - Current design status provides a feasible path to a PDR Cost - Initial cost estimates are documented, show a feasible path to a Bill of Materials (BOM) costs that meet metrics Updated program schedule to include testing and analysis timelines with feasible path to flight test program within established schedule metrics Tasks Preliminary airworthiness approach completed in consultation with the government Software Development - A software development plan, including verification and validation approach, is complete Trade Studies - The results of any trade studies completed to validate design approach are presented to include cost benefit analysis and military utility

CRANE: Phase 1 System Requirements Review (SRR)

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Requirements Development - Interface and requirements are complete Design Definition - Preliminary design is complete to the subsystem/configuration item level, closes around documented requirements, adequately demonstrates that performance achieves minimum and maximum threshold ranges, and meets SWaP-C constraints

Risks must include all design risks Cost - Revised BOM cost based on preliminary design is documented and within established cost metrics Tasks Updated airworthiness approach completed in consultation with the Government Software Development – A development plan with processes and metrics to measure progress is complete Updated program schedule to include testing and analysis timelines with feasible path to flight test program within established schedule metrics Technology Maturation - Test plans define objectives and expected results that will validate design proof-of-concept

CRANE: Phase 1 Preliminary Design Review (PDR)

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Subsystem testing Closed loop stability and control demonstration (glider, scaled flight vehicle, etc.)

Detail design and risk reduction testing Entry Criteria

SRR

PDR w/ Achievable path to Critical Design Review (CDR) Selected for phase 2 award Exit Criteria Component level testing to evaluate the configuration’s readiness & feasibility -- flight test program closes within cost & schedule Completion of integrated subsystem component testing and detailed design Test Evaluation Master Plan (TEMP) System level CDR Selected for phase 3 award

CRANE: Phase 2-Detailed Design

FY20 FY21 FY22 FY23 FY24

Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4

Phase 0:

Conceptual Design

Phase 1:

Preliminary Design

BAA Ph 0 Ph 3

1st FlightTRRPh 0 Ph 0

Ph 2 CoDR

Award

Ph 1 PDR CDR

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Airworthiness process/military flight release Test Readiness Review (TRR) Manufacturing readiness review (MRR) Ground testing Flight Test Entry Criteria

TEMP

CDR

Selected for phase 3 award Exit Criteria Completion of flight test series Possible transition opportunities

CRANE: Phase 3-Build, Integration, & Test

FY20 FY21 FY22 FY23 FY24

Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4 Q1 Q2 Q3 Q4

Phase 0:

Conceptual Design

Phase 1:

Preliminary Design

BAA Ph 0 Ph 3

1st FlightTRRPh 0 Ph 0

Ph 2 CoDR

Award

Ph 1 PDR CDR

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DARPA Program DARPA: Program Leadership, Funding, Go/No Go’s Multiple government organizations and SMEs are involved

− AFRL

− NASA

− ONR

Frequent Technical Interchange Meetings (TIMs) (teleconference or in-person) − Technical update (bi-weekly) − Program management review (monthly) − Vector check (quarterly)

CRANE: Program Management

Program Manager Alexander Walan

COR Program Advisor

IPT 1

Chief Engineer DARPA Support Staff

IPT 2 IPT 3 IPT N

Contracting Officer

CRANE Organizational Chart

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Encourage Use proven AFC technology where possible

- Minimize non value added technical risk Use/re-use of COTS components where possible Aligning risks w/ overall design philosophy Creative & novel approaches Early risk reduction activities Focus on fulfilling objectives

Discourage Patch and component fixes Development of novel systems not related to AFC

− Engines, avionics, materials, landing gear, etc.

Strap-on/attachment (wing glove, etc.) approaches Wing morphing Traditional thrust vectoring Control moment gyros

CRANE: Other Considerations www.darpa.mil

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