Hybrid Cartesian and orbit element feedback law for formation flying spacecraft

Journal of Guidance, Control, and Dynamics

Volumn 25, Issue 2, 2002, Pages 387-393

  Schaub, Hanspeter ^a   Alfriend, Kyle T ^b  

^a ORION International Technologies Inc   (United States)

^b Texas A and M University   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

APPROXIMATION THEORY; COMPUTER SIMULATION; ORBITS; SATELLITES; TRACKING (POSITION);

CARTESIAN COORDINATES;

SPACECRAFT;

EID: 0036494036     PISSN: 07315090     EISSN: None     Source Type: Journal    
DOI: 10.2514/2.4893     Document Type: Article

References (19)

1. 2 invariant reference orbits for space-craft formations
2. State transition matrix for terminal rendezvous studies: Brief survey and new example
3. Non-gaussian error propagation in orbital mechanics
4. Elliptic elements in terms of small increments of position and velocity components
5. Hybrid cartesian and orbit element feedback law for formation flying spacecraft
6. Spacecraft formation flying control using mean orbit elements
7. Spacecraft formation flying: Dynamics and control
8. Along track formationkeeping for satellites with low eccentricity
9. Time-explicit representation of relative motion between elliptical orbits
10. Asymptotic stability theorem for autonomous systems
11. Solution of the problem of artificial satellite theory without drag