mubody.mission.Mission#
- class mubody.mission.Mission(**kwargs)#
Interface with the user.
This class includes high level functions and integrates Satellite class.
- name#
Name of the mission.
- Type:
str
- status#
Status of the mission.
- Type:
str
- mission_time#
Total mission time.
- Type:
str
- sat#
Satellite class object.
- Type:
class
- default_ROLE#
Default reduced osculating lissajous elements.
- Type:
list (4)
- __init__(**kwargs)#
Methods
AO([deltaT, frame, bar, mission_t])Generates orbit with the analytical solution from the CRTBP model
ETM([model, t_maneouver, ref_orbit, refine, ...])Computes required DV and resulting trajectory when Equiting Targeting Method for station keeping control is applied to a reference orbit.
HTM([model, ref_orbit, bar, frame])Computes reference orbit using the work in Formation Flying in the Sun-Earth/Moon Perturbed Restricted Three-Body Problem, Ingvar Out, based on Howell (1984).
IC([model, IC, IC_frame, frame, N, bar])Generates orbit from direct integration of model equations
OTM([model, N_segments, opt_iterations, ...])Optimizes an orbit applying iteratively a targeting method and a linear correction of the orbit positions.
__init__(**kwargs)adapt_IC(model_name, IC, IC_frame)Adapts the input initial conditions to the required frame for propagations
adim_tra()coordinate_frame_change(destination_frame)Changes coordinate frame of the trajectory
dim_tra()generate_IC(model_name)Generates IC vector for its propagation
generate_ref_orbit(crtbp_flag, refine, bar)load(file_name, dir_name)Load mission class data
plot_trajectory([fig, equal])save(file_name[, dir_name])Save mission class
setup_coordinate_frames()setup_dynamical_system()setup_orbit_parameters([stable, ...])- param stable:
bool
Attributes
Tdefargsframemt