Utilisateur:Pline/Module lunaire

==> Conclusion : Utilisation du module dans la mission skylab, conservation des modules dans les musées, le ùodule lunaireAltair duprojet Constellation, les innovations technologiques.

Recours aux redondances (exemples, nbre de défaillances au cours de la mission X vs prévues, systèmes non redondants voir supra), abandon du principe des réparations in situ (circuits électriques scellés pour éviter la contamination humidité,...), simplicité et rapidité vs allégement, compatibilité avec le module CSM recherchée mais nbx obstacles liés à l'optimisation fonctionnelle et techniques (filtres CO2 Apollo13). Evolution du poids. Préférence pour les carburants hypergoliques et sans pièces mobiles. Risques de déséquilibre de l'étage de remontée lors de l'allumage de son moteur. Organisation en sous-sytèmes pour la conception et la fabrication. Existance d'une variante à partir d'Applo 15. Détailler les caractéristiques de l'ordinateur. Détailler les commandes de vol à disposition du pilote, le pilotage automatique. Profil de mission : durée, début du jour lunaire. Contamination biologique. Nature des tests réalisés : chambre à vide, ... Télémétrie (transmission continue des données de navigation, téléchargement à distance, contrôle du fonctionnement des différents équipements). Détermination du positionnement et de la trajectoire des vaisseaux par télémétrie à terre (retour expérience AP 10 et 11 ?).

A intégrer en partie

Major Considerations in the Design of the First Lunar Landing Mission

The first Apollo lunar mission will be "open ended," to capitalize on success and keep going as long as possible.
Launch will take place on [one of] only three days of any given month.
Lighting conditions on the moon at the time of arrival will be a major launch day constraint.
The mission will be flexible enough to land at any one of three selected landing sites.
Forthcoming information from the first two Orbiters and Surveyor landers will govern site selection.
The spacecraft will carry the maximum propellants and consumables that the Saturn V can handle.
A slow roll rate will avoid thermal extremes on the spacecraft.
The Manned Space Flight Network (MSFN) will be the primary source of navigation data, with onboard navigation as a backup.
The service propulsion system will use the lunar module descent engine as a backup.
The spacecraft will travel on a free-return trajectory.
Landmark sightings by the onboard systems will reduce uncertainties about altitude and tie the MSFN to the moon.
Landings will be made in three types of areas - one general and two specific.
The crew will be integral to the whole mission, particularly in site selection and landing maneuvers.
The first mission will have an 18-hour staytime and two joint excursions by the crew.
The LM will use a concentric flight plan for rendezvous with the CSM after liftoff from the moon.
If necessary, the CSM will be capable of rescuing the LM by descending to a lower orbit for rendezvous and docking.
The prime recovery zone will be in the Pacific Ocean.
There will be a continuous abort capability throughout the mission.
There will be at least five places during the mission where the spacecraft can "mark time" to change mission planning in case of trouble.
Redundant and backup systems will be available for most major systems; significant exceptions are environmental control, electrical power, and service propulsion systems.
Continuous communications between spacecraft and ground will be possible, except when the craft is behind the moon or in a thermal roll condition.
Design will incorporate reasonable precautions against contamination of either the earth or the moon
Major concerns still remaining are unforeseen environmental effects, calibration of guidance and navigation system, means of realistic simulation of lunar landing under the earth's gravity, and possibility of overloading crew workload.

From Manned Spacecraft Center, "Apollo Lunar Landing Mission Symposium: Proceedings and Compilation of Papers," 25-27 June 1966