Oryol - next generation Russian crewed spacecraft - development

[fregate]

I decided to open a new topic. Unfortunately on this forum news about spacecraft itself are mixed with news about
LV for a spacecraft (an existing topic). 

This week Russian Federal Space Agency (RSA) announced a new tender "Prospective Manned Transportation System. First Stage. Detailed Technical Project" under R&D program "PPTS".

Results of tender would be announced on 29th of November 2010, but it seems that RSC Energia most likely will be a winner: company completed a Preliminary Design of the manned spacecraft in June.
 
Technical Requirements Documentation available here (in Russian) 

TO BE CONTINUED...

[Lars_J]

Is there a viable competitor to RSC Energia for this?

[zaitcev]

No, there is no alternative. The winner is predetermined, but as I understand the law requires to carry out a formal contest before assigning the money.

Note that "PPTS", e.g. the "PPT System" includes (Space-)Ship and Booster. This topic is for the spaceship, like Fregat said. But the co-joined booster contest is suddenly made hilarious to watch as Energia knifed Progress in the back and submitted Energia-KV with bizarro SRBs as an alternative to what's known as "Rus-M" in the west. Angara-5P is formally back in the running too. That alone makes it worth running the one for the capsule as well, even with Energia alone.

Note that Progress makes quasi-manned spaceships: Foton and Bion. It would be a real riot if they submitted a project for PPTK just to spite Energia. Khrunichev keep resubmitting TKS, but that's just pathetic. Without a deep modification TKS cannot satisfy the requirements. It's far too heavy, only seats 3 etc etc.

[Lars_J]

Can someone give a short summary (in english) of the requirements document? How specific is it? Are things such as crew size, cargo capacity, mission duration spelled out?

EDIT: I managed to run google translate on the technical requirement section:

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.

So the things I noticed, if I understand the mangled translation:
 - capable of lunar flights
 - capsule should be partially reusable - 10 times
 - capable of supporting up to 4 people for a 30 day flight (no mention of capacity for station ferry flights)
 - an optional orbital module (??), the "DPP", for use on longer flights?

Please correct me if I am not understanding things correctly.

[Lars_J]

Upon initial reflection those requirements seem awfully... "Orion"-ish. I'm surprised that they are specifying this level of initial capability to begin with, when lunar flights are nowhere close. Receiving proper funds will be a continuing struggle throughout its development.

It would seem to be more prudent to start with something more basic - a roomier and more modern Soyuz replacement capable of seating 6, and then evolve it from there as needed. (Just like Soyuz has evolved over the years)

[zaitcev]

Heh, orionish. You are going  to be even more amused when you learn that the Orbital Compartment (DPP above) is launched below the common PTK, and not on top like in Soyuz. This way a common LAS is used for all versions.

[fregate]

Can someone give a short summary (in english) of the requirements document? How specific is it? Are things such as crew size, cargo capacity, mission duration spelled out?

My sincere apologies - I did not have time to translate key requirements in English.     

So the things I noticed, if I understand the mangled translation:
 - capable of lunar flights
 - capsule should be partially reusable - 10 times
 - capable of supporting up to 4 people for a 30 day flight (no mention of capacity for station ferry flights)
 - an optional orbital module (??), the "DPP", for use on longer flights?

Please correct me if I am not understanding things correctly.

Lars_J,
- Another configuration of manned transport spacecraft (PTK NP) would be capable of lunar flight (PTK-L) with crew of 4 cosmonauts; deferred to the second stage of Technical Project;
- Capsule (VA) should be partially reusable - 10 times (only in case of non-emergency landings);
- capable (VA) of supporting up to 4 people for a 30 day flight (no mention of capacity for station ferry flights).
I am sorry but you are mixing here 2 different spacecraft configurations: 
* PKK-Z is a manned spacecraft for autonomous missions (crew 2 cosmonauts, duration up to 30 days or crew 4 cosmonauts, duration up to 14 days). This is a BASE spacecraft configuration across whole project; 
* PKK-S is a manned transportation spacecraft to deliver 6-cosmonaut crew and 500 kg cargo to the LEO manned Orbital Station; Spacecraft could fly up to one year docked to OS.  This configuration is a modification of a base spacecraft PKK-Z; 

- An optional orbital module (??), the "DPP", for use on longer flights? Mission Module DGO (similar but larger than Soyuz Orbital Module) is planned for a base configuration.
Mission module should have at least 6 cubic meters for internal payload up to 1000 kg. There could be an external payload in unpressurized compartment and optionally a manipulator arm.
I could speculate that design would be quite similar to POISK ISS module. Most likely mission module would be situated in LV under spacecraft on top of upper stage and spacecraft after reaching LEO will execute Appollo-style maneuvers in order to retrieve a module (similar to LM retrieval for Lunar Program and Docking Module in ASTP)   
 
Please note that last year tender RKA envisioned at least 6 configurations of PTK NP spacecraft. This year tender established a priority for Technical Detail Design of the following configurations:
- PKK-Z Base manned configuration for autonomous missions;
- PKK-S Manned configuration for Orbital Station supply missions;
- GVK-S Unmanned configuration for Orbital Station cargo supply and return missions; (Progress cargo replacement, this configuration functionally  identical to ESA ARV spacecraft); 
 
I highly recommend you to visit the the most comprehensive site about history of New Generation Manned Transportation Spacecraft (PTK NP) and Prospective Manned Space Transportation System (PPTS) development, thanks to Anatoly Zak 
RUSSIANSPACEWEB.com 

[Lars_J]

Thanks for the info, fregate - It is very much appreciated!

[fregate]

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)

That's ALL, folks! (C)

[fregate]

LEO version 2008

LLO version 2008 with a stretched service module (DO) and cryogenic EDS for TLI maneuver.

[fregate]

[Proponent]

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.

The last of the diagrams you've posted shows landing engines with what seems to be a total delta-V (at least I presume that's what "Vx" is) of 300 m/s.  I would have thought that would be enough to land without parachutes.

Oh, and thanks--this is very interesting!

Are the landing engines powered by liquid propellants?

[fregate]

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.

The last of the diagrams you've posted shows landing engines with what seems to be a total delta-V (at least I presume that's what "Vx" is) of 300 m/s.  I would have thought that would be enough to land without parachutes.

Oh, and thanks--this is very interesting!

Are the landing engines powered by liquid propellants?

This was original design of landing system (in 2008) - Power Landing on Solid Motor Engines (12 SMEs are shown on this picture). Each SME suppose to have a variable thrust and variable thrust vector control systems. Design had been evolved since completion of preliminary design by Energia:
- first, a 3 canopy (similar to Apollo CM) parachute system had been introduced as a BACKUP landing (it had been designed to provide safety landing of Crew Compartment with mass 4,500 kg, while power landing provided capsule re usability, total VA capsule mass for LEO configuration is 7,700 kg);
- later on in Aug 2010 Energia PR machine came up with quite vague statement about landing system design changes; IMHO they decided to design landing system similar to Marsian probes - in first stage braking parachute(s) and in second stage - powered landing on SOLIDS. Most likely another parachute(s) would be used for a backup system.

With RKA requirement to keep spacecraft docked to station for a duration up to one year it'll be impossible to utilize a liquid propellant in power landing system.

Please note that we already have a dedicated thread for prospective Russian spacecraft power landing on this forum. 

Cheers,           

[fregate]

Images from RussianSpaceWeb site:
An Earth-orbiting configuration of the PTK NP (PPTS) spacecraft as of August 2009.

The 16.5-ton lunar version of the PPTS spacecraft could feature a "stretched" service module, which could carry increased load of propellant for maneuvers in the vicinity of the Moon.

[fregate]

Scale Model of PTK NP Spacecraft on MAKS 2009 Airspace show

[fregate]

A possible configuration of the PTK NP spacecraft with an additional mission module, which could be based on the Docking Compartment or a node module of the ISS. The head of the Russian space agency Anatoly Perminov first mentioned such option in April 2010.

[fregate]

OS Manned transportation spacecraft PKK-S (2008 version)

[fregate]

Novosti Komonavtiki Magazine, N9 2008 First article about PPTS:

[Lars_J]

I am a bit curious about the heat shield or insulation around the capsule. Perhaps it is just artistic licence - But it looks like the color of the insulation 'tiles' (or whatever they may be) indicate that the capsule is designed for a lifting reentry at a pretty extreme angle - more than Apollo or Soyuz, it seems.

But if that is the case, the G forces for the 3 of the crew (in the layout for 6) should be quite uncomfortable, since the essentially are riding upside down.

Or is there another idea behind the blacker coating of one side of the capsule?

[fregate]

AFAIK an aerodynamic factor for VA (L/D ratio) should be comparable with Apollo CM.
3G - for a controlled descent, 12G for ballistic.
By design there is a offset between vertical axe and center of mass location to make sure that VA enters atmosphere with right attack angle, to guarantee that heat would affect the "right" side of VA, please note that opposite side has a block of RCS engines.