Oriol - Le nouveau vaisseau russe

Firnas2 a écrit:J’ai des preuves :megalol: que Patchfree discute avec des russes. Alors s’il veut nous éclairer, il peut :D

patchfree a écrit:

Firnas2 a écrit:J’ai des preuves :megalol: que Patchfree discute avec des russes. Alors s’il veut nous éclairer, il peut :D

Le seul russe avec lequel j'ai eu quelques échanges (modestes) c'est Anatoly Zak. Pour le reste je n'ai pas plus d'infos que vous tous.

patchfree a écrit:
le PTS est prévu pour des missions dans un cadre très précis:

- l'habituel ascenceur pour l'ISS (ou autre station)
- des missions autonomes autour de la Terre en orbite basse (jusqu'à 1 mois)
- des vols vers la lune (AUTOUR de la lune) (une dizaine de jours).

Les russes concoivent ce vaisseau pour qu'il dure au moins 50 ans. Donc il doit être spécifié pour remplir des missions variables. La durée autour de la terre et le vol circumlunaire fixent les règles en matière de design et de poids.

Advanced Crew Vehicle to Provide Landing Accuracy Better than Soyuz
:: 13.10.2010

Advanced crew vehicle developed by RSC-Energia will provide landing accuracy 10 times better than Soyuz due to parachute and propulsion landing system, RSC-Energia president Vitaly Lopota told news media.
It is planned to open the parachute during in the low altitudes during the descent, together with jet engines.
"Since some landing areas in Russia have uneven terrain, both systems are used to maintain proper safety. Landing accuracy will also improve up to 2 km, from 20 of Soyuzes”, Lopota said.
Energia has won a tender to develop the advanced vehicle in April 2009. The contract implies several modifications, including LEO and LLO options, repair and deorbiting of the failed satellites and space debris. Flight tests of the new vehicle are to commence in 2015, RIA Novosti informs.

patchfree a écrit:
Le système de retour sur la terre: les parachutes ne s'ouvriront que dans la toute dernière partie du retour et seront assistés de rétrofusées

Firnas2 a écrit:

patchfree a écrit:
Le système de retour sur la terre: les parachutes ne s'ouvriront que dans la toute dernière partie du retour et seront assistés de rétrofusées

C’est nouveau, au par avant, les parachutes ne s'ouvriront qu’en cas de secours. Il redevient plus classique et moins révolutionnaire ce PTS :???:

Roskosmos posted on the site of the new conditions of competition on state contract
:: 10/27/2010

The site of the Federal Space Agency published the tender documentation for the next open competition on state contract:

Subject of a contract

"Creating the perspective of manned transport system in the first phase of design development"

Code: ROC "PCA" (Stage 1)

The initial (maximum) contract price 2,000,000,000 rubles

Terms of the contract: December 2010 - December 2012

For more information on the tender documentation, clarifications and additions thereto may be found in the "Contests" on the official website of the Federal Space Agency on the Internet - http://www.federalspace.ru/main.php?id=15, as well as on the official site Russia to place information about placing an order - http://www.zakupki.gov.ru/

The agency's requirements for the Technical Project instructed the industry to focus on two versions of the next-generation spacecraft -- PTK-Z designed for long-duration autonomous missions in the Earth orbit, and PTK-S intended to service the Earth-orbiting station, such as ISS. Other "flavors" of the PTK spacecraft, which were drafted during the preliminary design, including a lunar orbiter, were deferred to the second stage in the PPTS development program.

3. Technical requirements.
PCA is designed to meet the challenges of development near-Earth space (NES), transport and logistics (TTO) of the elements-Earth space infrastructure (space stations, independent laboratories, unmanned spacecraft), maintenance and repair (TOR) automated spacecraft, perform a wide range of scientific and Applied Research (NPI), and experiments, as well as to implement the manned missions to the moon and to provide transportation on the tracks "Earth-Moon system."
PCA is created in stages.
3.1. The composition of the first phase of PCA:
3.1.1. Prospective manned transport system of Step 1 in the provision set forth in the Federal Space Program objectives include space complexes of the following composition:
1) Manned space complex for autonomous operations, and conducting experiments in near-Earth space (PAC-W) - Base PAC;
2) Manned space complex for transport and logistics space station (PAC-C) (Transportation and gruzovozvraschayuschaya set) - modification of the basic PAC;
3.1.2. Space complexes should be as unified and have a maximum amount of borrowed elements together in order to use them to solve problems of PCA as a whole.
3.2. Requirements for appointment
3.2.1. Requirements of the destination components of PCA of the first stage:
3.2.1.1. Manned space complex for autonomous operations, conducting applied research and experiments in near-Earth space (PAC-W).
3.2.1.1.1. Manned space complex for autonomous operations and conduct applied research and experiments in near-Earth space (PAC-W) must include a partially reusable (use the recovery vehicle up to 10 times) manned transport spaceship (PTC-W), which is the base and other elements complex, providing a solution to all scientific, technical and technological issues for the implementation of the relevant flight.
3.2.1.1.2. Ship PTC-W is designed for autonomous flight crew of up to 4 people for up to 30 days (see Table 1) and run with the wide range of scientific and applied research experiments.
3.2.1.1.3. To perform these tasks in the design of the ship PTC-W shall include:
 recovery vehicle reusable (up to 10 times) application (BA);
 engine compartment (DO);
 additional sealed compartment (DPP).
3.2.1.1.4. Complete DPP can have variable composition, depending on the task of a particular flight, and determined by the program of flight tests (flight program).
In the basic configuration DPP must ensure that placement of the standard (uniform) racks of scientific equipment and hardware parts of life support systems (LSS).
Mass output of experimental equipment (payload is placed on the DPP) should not be less than 1000 kg. The main part of the payload (not less than 800 kg) should allow its removal during the flight, transfer to the recovery vehicle (WA) and return to Earth. The volume to be allocated to the payload in the DPP should be no more than 6 cubic meters
Power supply payload DPP should not be less than 2 kW of power on average for the round.
Habitable volume of the compartment DPP in conjunction with the habitable volume of BA, as well as zoning habitable space must enforce hygiene standards are not worse than those of habitat out in GOST 50804-95.
The outer part of the bay DPP should include the installation of variable composition Attachment (seed) equipment.

The technical design should be worked out possible improvements to the DPP in order to assemble (dismantling) of the necessary equipment in the air at the surface of the compartment, including the use of robotic vehicles.
In the basic configuration DPP must be equipped with at least two portholes, the sight line of which should be directed along perpendicular axes.

montmein69 a écrit:
Je n'ai pas vu beaucoup de projets russes pour aller en orbite lunaire, ni pour des voyages plus longs sauf ceux déjà évoqués.
Ce qui donnait un concept d'assemblage de bidons, avec sur des noeuds de jonction le module d'atterrissage et la capsule.

Mais ils doivent bien avoir des idées de ce genre , et donc conçoivent leur nouvelle capsule pour qu'elle puisse remplir ces différents rôles. Elle sera peut-être moins optimisée pour le LEO basique, mais si leur lanceur peut lancer cette masse où est le problème ?

Technical Requirements Summary for RKA Oct 2010 Spacecraft Tender.
Prospective Manned Space Transportation system. Technical Project. Stage One
R&D Program Codename PPTS (Stage One)

PPTS objectives includes the following mission types:
- LEO exploration missions;
- Supply missions to LEO infrastructure (Orbital Stations, Autonomous Laboratories, Robotic Spacecrafts);
- Maintenance and repair missions of Robotic Spacecrafts;
- Science and technology missions;
- Lunar missions logistical support by means of Manned and Cargo transportation from LEO to LLO.

Stage One prioritizes the following PPTS spacecraft configurations:
- PKK-Z Base configuration manned spacecraft for autonomous missions;
- PKK-S Manned transportation spacecraft for Orbital Station supply missions;
- GVK-S Unmanned transportation spacecraft for Orbital Station cargo supply and return missions;

PKK-Z Base configuration manned spacecraft for autonomous missions
Base configuration PKK-Z consists of the following modules:
- VA Reusable Return or Descent Module - to sustain at least 10 missions;
- DO Engine or Service Module (expendable);
- DGO Complimentary Pressurized Module - Mission Module.

PKK-Z Autonomous Mission duration
- up to 30 days (2 cosmonauts crew)
- up to 14 days (4 cosmonauts crew)

Mission Module configuration has to be flexible to meet a particular mission requirements:
- Pressurized compartment to hold portable scientific payload (up to 1000 kg, including 800 kg of removable payload);
- Pressurized compartment to hold live support system components;
- Pressurized compartment to have at least 6 cubic meters of volume for payload storage;
- Power supply at least 2 Kwh per orbit (seems to be DGO would have separate solar panels, similar to Shenzhou Orbital Module);
- External Payload might be stored in unpressurized compartment (optional);
- Some equipment could be installed or removed on external surface during flight either manually or with robotic assistance;
- DGO would have 2 illuminators (90 degrees apart), one of them allows observation in ultraviolet range;
- Docking: PKK-Z should be able to dock with OS with or without Mission Module (it seems to be that it should have 2 docking units - active and passive along module vertical axis)

PKK-Z Standard LEO orbits:
- Altitude in range of 200-500 km, orbit inclination 51,7 degrees;
- Feasibility study for 3 days missions to orbit with altitude below 1000 km (orbit inclination 51,7 degrees);
- Feasibility study for missions with inclinations 63.0;72.0; 83.0; 98.0 degrees;

Associated launch vehicle - Middle class (with extended capability) LV RUS M. G-forces as following (no changes since last year):
- Launch - 4g;
- Landing - 3g (nominal) and 5g (controllable side maneuver during descent) ;
- Launch Emergency System - 7g (going away from LV);
- Atmospheric descent during emergency landing - 12g.

Please note that landing precision for manned missions had been increased (comparing with 2009 tender requirements) from 2 km m to 5 km. IMHO this is indirect indication that landing would be done by means of Parachutes Deployment (primary landing system) as well as Power SME Landing (secondary landing system). RKA was not in favor of 100% Power Landing system announced in 2008 by Energia. As a result 3-canopy chute system had been introduced on completion of Preliminary Design as a backup system and now it's seems to be an integral part of landing system.

PKK-S Manned transportation spacecraft for Orbital Stations
This configuration consists of the following modules:
- VA Reusable Return or Descent Module - to sustain at least 10 missions;
- DO Engine or Service Module (expendable);

Standard Payload: 500 kg Up/Down;
Crew - 6 cosmonauts;
Objective: transportation spaceship to supply Orbital Stations and Stand-alone (autonomous) lab modules;

Mission duration:
- Autonomous flight - to perform 2 docking attempts and return to Earth;
- As a part of Orbital Station after docking - up to 1 year;

Standard mission orbits
- ISS supply - altitude 200-450 km inclination 51.6 degrees
- Prospective OS supply - altitude 200-500 inclination 51.7 degrees
- Prospective Stand-alone (autonomous) lab module supply - altitude 200-400 km inclination 72.0 degrees

Associated launch vehicle - Middle class (with extended capability) LV RUS M or commercial LV qualified for a manned flight. Parking orbit - 200 km inclinations 51.6, 51.7 or 72 degrees.
G-forces and landing precision - refer to PKK-Z base configuration requirements.

GVK-S Unmanned transportation spacecraft for Orbital Station cargo supply and return missions
IMHO this configuration is identical to PKK-S, however because spacecraft is unmanned, it might have a bigger payload capacity (LV LES/SAS to be discarded)
Return payload - up to 2000 kg

For all configuration
- Mission safety probability factor - 0.995
- VA lifetime expectancy - at least 5 years
- Heat Shield and other heat protected surface should be replaceable
during service operations between missions;

Tender results would be announced on 29th of November, 2010, most likely project would be awarded to RSC Energia. ;)
Project Duration 2010-2012
Project Budget allocation: total RUB 2 billions (US$ 64.97 million)
2010 RUB 500 millions (US$ 16.24 million)
2011 RUB 700 millions (US$ 22.74 million)
2012 RUB 800 millions (US$ 25.99 million)

patchfree a écrit:Un schéma sur le forum NK qui montre le processus de type "Apollo" après le lancement du PTS: retournement et extraction du module orbital.

montmein69 a écrit:

patchfree a écrit:Un schéma sur le forum NK qui montre le processus de type "Apollo" après le lancement du PTS: retournement et extraction du module orbital.

Les russes ont-ils déjà eu l'occasion d'utiliser une telle technique (lors d'anciens vols) ?
Une telle manoeuvre peut-elle être commandée en automatique (avec un système Kurs modifié) où cela nécessite-t'il une commande par un pilote ?

A new spaceship "Russia" will build, not waiting until the end of its technical design


Construction of the first spacecraft of a new generation of "Russia" will start before the completion of its technical design, which should end in 2012, told Interfax-AVN on Saturday at the Mission Control Center Russian Federal Space Agency deputy head Vitaly Davydov.
"We have until this date has something to do" - he said.
"Engineering design is not only development of technical documentation, but also the development of individual units, their working out," - said Vladimir Davydov.
Thus, according to him, even before the completion of the technical design perspective of the transport complex of new generation to create the first sample had already started.
Preliminary design of the new ship began in 2009, technical - in 2010 (it is given two years), then to begin development of design documents (including two years). The first test launch of the ship "Russia" in an unmanned version is scheduled for 2015 and for 2018 is planned organization of manned flight.

montmein69 a écrit:Est-on capable d'évaluer le potentiel technique des russes en terme de "modélisation informatique" de ce qu'ils veulent créer ?
En occident les développements, dans le domaine automobile, aéronautique etc... ont été notablement modifiés par cette conception sur logiciel de développement. Disposent-ils d'outils logiciels équivalents et d'ordinateurs de puissance comparable ?

tatiana13 a écrit:il y avait ceci


et ici
http://www.russianspaceweb.com/lunar_base.html


http://www.russianspaceweb.com/los.html



et je crois que récemment une présentation du future programmme lunaire russe a eu lieu à ce symposium
XXXV Annual Academic Korolev's Proceedings (Moscow, 25-28 January 2011)
en auriez-vous des précisions?