Open Access
Table A.1
Nomenclature.
| Symbol | Description |
|---|---|
| Osculating orbital elements (OEs) | |
| (·)(s) | Secular parts of osculating OEs, rad |
| δ(·)(lp) | Long-period parts of osculating OEs, rad |
| δ(·)(sp) | Short-period parts of osculating OEs, rad |
| Orbital parameter for the chief | |
| a | Semimajor axis, m |
| e | Eccentricity vector (e = [ex, ey]T, e = ||e||) |
| I | Inclination, rad |
| Ω | Right ascension of the ascending node, rad |
| ω | Argument of perigee, rad |
| ϕ | Mean argument of latitude, rad |
| θ | Argument of latitude, rad |
| n | Mean motion, rad s−1 |
| nl | Long-period angular frequency, rad s−1 |
| ω | Orbital angular velocity vector, rad s−1 (ω = [ωx, ωy, ωz]T) |
| Reference formation parameter | |
| Θx,Θz | Phase angles for the perturbed motion, rad |
| ρx,ρy, ρz | Size parameters, m |
| αx,αz | Phase parameters, rad |
| ωt | User-defined target angular velocity, rad s−1 |
| rr | Position vector of the deputy with respect to the chief, m (rr = [xr, yr, zr]T) |
| Physical and environmental parameter | |
| μb | Third body’s gravitational constant, m3 s−2 |
| μe | Earth gravitational constant, m3 s−2 |
| Re | Mean equatorial radius of Earth, m |
| ρ | Atmospheric density, kg m−3 |
| Ps | Solar radiation pressure, Pa |
| Spacecraft parameter | |
| BD | Coefficient for drag, m2 kg−1 |
| δBD | Differential value of BD, m2 kg−1 |
| Bs | Coefficient for SRP, m2 kg−1 |
| δBs | Differential value of Bs, m2 kg−1 |
| Cs | Radiation pressure coefficient |
| Cd | Drag coefficient |
| S | Cross-sectional area, m2 |
| m | Spacecraft mass, kg |
| s | Unit Sun vector |
| Position | |
 |
Position vector of the third body, m |
| Rc | Position vector of the chief, m |
| Rd | Position vector of the deputy, m |
| r | Position vector of the deputy with respect to the chief, m (r = [x, y, z]T) |
| Acceleration | |
| Fc, fp, | Perturbing acceleration vectors, m s−2 |
| fo, ff | (see Table 1 for the definition.) |
| uc | Control acceleration vector applied to the chief, m s−2 |
| ud | Control acceleration vector applied to the deputy, m s−2 (ud = ux, uy, uz]T) |
| ur | Control acceleration vector to compensate for all relative perturbing accelerations, m s−2 |
Current usage metrics show cumulative count of Article Views (full-text article views including HTML views, PDF and ePub downloads, according to the available data) and Abstracts Views on Vision4Press platform.
Data correspond to usage on the plateform after 2015. The current usage metrics is available 48-96 hours after online publication and is updated daily on week days.
Initial download of the metrics may take a while.