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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

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

slide5
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

Odyssey Space Research

jules verne launch date
MAY 2005Jules Verne - Launch Date

Odyssey Space Research

vehicle configuration
Vehicle Configuration

*400 km, 51.6 deg inclination

Odyssey Space Research

vehicle comparison
Vehicle Comparison

Odyssey Space Research

vehicle systems
Vehicle Systems

Odyssey Space Research

communication
Communication

Odyssey Space Research

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

Odyssey Space Research

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)

Odyssey Space Research

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

Odyssey Space Research

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

Odyssey Space Research

atv guidance
ATV Guidance

Odyssey Space Research

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

Odyssey Space Research

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

Odyssey Space Research

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

Odyssey Space Research

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)

Odyssey Space Research

demonstration
Safe!

Show

ATV is

Demonstration

Odyssey Space Research

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

Odyssey Space Research

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!

Odyssey Space Research

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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