Atv rendezvous mission 1 jules verne
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ATV Rendezvous Mission 1: Jules Verne. Brian Rishikof Odyssey Space Research 281-488-7953 March 24, 2004. Outline. ATV (Automated Transfer Vehicle) Program ATV Vehicle ATV Trajectory and GN&C Demonstration. ATV Program. ESA (European Space Agency) ISS Partner

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ATV Rendezvous Mission 1: Jules Verne

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Atv rendezvous mission 1 jules verne

ATV RendezvousMission 1: Jules Verne

Brian Rishikof

Odyssey Space Research

281-488-7953

March 24, 2004


Outline

Outline

  • ATV (Automated Transfer Vehicle) Program

  • ATV Vehicle

  • ATV Trajectory and GN&C

  • Demonstration

Odyssey Space Research


Atv program

ATV Program

  • ESA (European Space Agency)

    • ISS Partner

  • EADS (European Aeronautic Defence & Space)

    • Flight Segment Prime Contractor

  • CNES (Centre National D’Etudes Spatiales)

    • Operations Prime Contractor

  • RSC- E (Rocket and Space Corporation - Energia)

    • ESA Integration Sub-contractor

  • NASA (National Aeronautics & Space Administration)

    • Prime ISS Integrator

  • RASA (Russian Aviation and Space Agency)

    • Integrator

Odyssey Space Research


Atv international

ATV International

Korolev(Moscow)

MCC-HHouston

MCC-M

Moscow

ESTEC

Noordwijk(Amsterdam)

ATV-CC

Toulouse

Les Mureaux

(Paris)

Odyssey Space Research


Atv rendezvous mission 1 jules verne

ITAR

  • International Traffic in Arms Regulations

    • ATV has been designated as a “defense article”

    • Subject to Export Control restrictions

    • Complicates support

  • Perils of International cooperation

Odyssey Space Research


Atv mission

ATV Mission

  • Dock to ISS Service Module aft

  • Deliver Cargo

    • Russian Water

    • Fuel

    • Gases

    • Other

  • ISS Propulsion

    • Reboost

    • Attitude control

    • Debris avoidance

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Jules verne launch date

MAY 2005

Jules Verne - Launch Date

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Vehicle configuration

Vehicle Configuration

*400 km, 51.6 deg inclination

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Vehicle comparison

Vehicle Comparison

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Vehicle systems

Vehicle Systems

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Communication

Communication

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Rendezvous safety rqmnts

Rendezvous Safety Rqmnts

  • “1 Fail Op”

  • “2 Fail Safe”

  • 24 hour safe free-drift trajectory

  • Approach Ellipsoid

    • 2 km x 2 km x 4 km

  • Keep Out Sphere (KOS)

    • 200 m sphere

Odyssey Space Research


Rendezvous constraints

Rendezvous Constraints

  • Russian Ground Station Visibility

  • ISS attitude and array feathering limits

    • ATV/ISS: Communication

    • ATV/ISS: Common GPS satellites and visibility

    • ISS: Power

    • ISS configuration dependent

  • Lighting for visual monitoring

  • Lighting for sensors

  • Power

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Atv trajectory 1 2

Fixed Phasing Duration

~ 7.3 hours

AI

3.5 km

Variable Phasing Duration

49 - 97 hours

Fixed Initial Drift

~ 3 hours

KOS

AE

V-Bar

S-S Comm

S2

Phase 6

Phase 5

Phase 4

Phase 3

Phase 2

Phase 1

S-1/2

S1

R-Bar

S0

dV6

0.5 rev

>20 min

>10 min

S-1

S-2

dV4

dV5

S-3

dVMC12

MC  ATV-CC computes Mid-Course transfers dVMC11 and dVMC12

S-4  ATV-CC computes dV3 and dV4

S-3  ground computes dV5 and dV6

S-2  reference point; half orbit after dV6

S-1  point where 1st correction (trim) maneuver is initiated; 1 orbit after S-2

S-1/2  phasing targeted point; 1 orbit after S-1

dV3

S-4

dV2

dVMC11

MC

dV1

CAM test 1

ATV Trajectory (1/2)

Odyssey Space Research


Atv trajectory 2 2

Omni-directional Space-to-Space

Comm Range (~3km)

Directional Space-to-Space

Comm Range (~30km)

250 m

KOS

AE

V-Bar

AI

3.5 km

S3

S2

40 min

~5 km

Decision Point

45 min

S0

S1

S-1/2

R-Bar

S41

12m

S4

20m

>10 min

>20 min

S3

Start RGPS Navigation

Transition to VDM

Transition to VDM Relative Attitude

Absolute GPS Navigation

Crew Visual Assessment

ATV Trajectory (2/2)

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Atv navigation

2x GPS receivers/antennas

AGPS

RGPS

3x 2-axis accelerometers

4x 2-axis gyros

KURS

Range + range rate

2x Videometers

Range (range rate) & LOS

relative attitude

2x Telegoniometers

Range (range rate) & LOS

PRIME

MONITORING

SENSORS

AGPS

RGPS

KURS

TGM

VDM

VDM+ Rel Att

USOS Cameras

SM Camera

DOCKING

10 cm

1 m

10 m

100 m

1 km

10 km

100 km

ATV Navigation

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Atv control

S

4b

S

41

S

4a

V

ATV Control

  • “Yaw Steering”

    • For power and communication

  • “Earth Pointing”

    • Early phasing

    • LVLH (0,0,0)

    • Pointing sensors at ISS

  • Relative Attitude

    • Measurements start at 30 m

    • Transition occurs at 20 m

Odyssey Space Research


Atv control1

ATV Control

  • Phasing

    • Earth Pointed OCS major maneuvers

    • Otherwise Yaw steering

  • Rendezvous

    • ACS maneuvers

    • Yaw steering attitude

  • Final Approach

    • Earth Pointed (LVLH 0,0,0)

    • Relative Attitude (0,0,0)

    • Simultaneous control of CG and docking probe tip

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Atv guidance

ATV Guidance

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Safety

Safety

  • Tiered Approach

    • Ground and Crew as additional controls

    • Crew “in the loop” just prior to docking

Coarse State Monitoring

BACKUP FLIGHT Systems

Trajectory Monitoring

PRIMARY FLIGHT Systems

System/Subsystem FDIR

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Contingencies

ABORT

?

Contingencies

  • ABORT (CAM)

    • Backup H/W & S/W

  • ESCAPE

    • Nominal H/W & S/W

  • Also, during Final Approach

    • HOLD

    • RETREAT

  • Vehicle/Crew/Ground commands

ABORT

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Decision point

Decision Point

  • Distance at which momentum will overcome any propulsive reaction and result in contact

    • After this point, assumption is continuing is safer than executing “large” maneuver

  • “Decision” made by crew on-board ISS

    • ATV-CC communication lags result in earlier “ground” decision point

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Crew monitoring

No “Piloting”

Prescribed reactionon threshold detection by visual means

Single operator with all “critical” information and command access

Crew Monitoring

  • Visual target on ATV

    • Active illumination Camera on ISS

    • Prime

    • Backup (to be installed via EVA)

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Demonstration

Safe!

Show

ATV is

Demonstration

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Demonstration mission

Demonstration Mission

  • Philosophy

    • Demonstrate safety critical elements that cannot be fully tested on ground

    • Demonstrate safety critical elements before they are relied upon during flight for safety

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Demonstration plan

Demonstration Plan

  • Currently 3 day mission rendezvous mission

  • Progressively test and evaluate

  • Achieve incremental milestones

    • Demonstrate sensors as they come online (prime and monitoring)

    • Demonstrate communication and critical commanding

    • Demonstrate integrated vehicle GN&C performance

    • Demonstrate ALL contingency actions

  • After ALL demonstration objectives/criteria satisfied + Proceed to Docking attempt

    • Nominal rendezvous profile

Odyssey Space Research


Atv for fun

ATV: For Fun!

  • http://esamultimedia.esa.int/docs/atv_model/ATV_2002_Intro.htm

BUILD

YOUR

OWN!

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Acknowledgments

Acknowledgments

  • Jean-François Clervoy/ESA

  • Douglas Yazell/Honeywell

  • AIAA Houston

  • NASA-JSC-EG

  • NASA ATV Team

  • Congratulationsto ATV Team

Odyssey Space Research


The end

The End

Odyssey Space Research


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