3 TACTICAL AND TECHNICAL REQUIREMENTS FOR PRODUCT
3.1 Composition Products
The structure of the AAC heavy class should include:
two-stage launch vehicle;
three-stage launch vehicle (base - heavy-class launch vehicle, produced in accordance with Presidential Decree of January 6, 1995);
DM and KVTK (functional);
standardized hardware solution pH;
uniform and technical complex ILV;
launch facility;
range of measuring instruments, data collection and processing of information (functional);
automated control system preparation and commissioning of LV;
range of transportation components of the launcher;
training aids.
Notes:
A. The complex of training facilities needed for training of personnel, may be brought from the other complexes.
Two. The composition of space-rocket complex can be refined in the development of conceptual design.
3.2 Requirements of destination
3.2.1 Requirements for AAC
3.2.1.1 CRC heavy class must be based on the AAC heavy class, created in accordance with Presidential Decree of January 6, 1995, and to be versatile for use in the prospective manned transport system (PCA), and space systems with automated spacecraft. The appearance and characteristics of AAC should be formed to meet the requirements of the PCA and the manned craft the specifics of their training and launch.
3.2.1.2 CBC shall provide:
launches of spacecraft scientific, social, economic, military and dual-purpose on the orbits of different altitudes and inclinations, including the GTO, and GEO and escape trajectories; modules of space stations and platforms for low inclination orbit with a basic 51,7 ο ;
Note:
In the conceptual design should consider the possibility of elimination of automatic spacecraft and manned spacecraft into orbit with the PCA inclinations 51,6 ο, 64,8 ο, 72ο and 83ο.
elimination of manned transport spacecraft on a trajectory PCA flights to the Moon and the near-Earth orbital stations;
fulfillment of the requirements for search and rescue complex, developed under the ROC "PCA";
competitiveness in the market of launch services;
storage, reduction and maintenance of pH within the established readiness, maintenance and assembly of the space rocket, preparing for the launch and launches space rocket;
functional and test control, and diagnosis of technical condition of machines and systems for the AAC, including the PH and RB on the stages of preparation and launch;
ease of maintenance and replacement of failed components and assemblies in preparation for launch;
exclusion of manual operations in preparation for the start-up (missed start) ILV from the start of fueling of the launch vehicle, minimizing manufacturing operations, providing for the presence of staff during landing and evacuation of the crew;
minimum necessary to attract staff and its security services during all types of work;
safety of the launch facility, leaving unstressed ILV with the launcher and minimize the impacts of it on the SC and its equipment;
drop in octane RKN and their fragments within the boundaries of the selected RP;
the possibility of group and associated removal of automatic spacecraft;
provision of fire and explosion safety in all phases of operation;
condition monitoring systems and components SK and ILV;
Landing crew PTC 2.5 to 2 hours and emergency evacuation of the crew and service personnel in emergency situations.
3.2.1.3 For the CRC set the following technical readiness:
technical readiness to number 4 - components of the RN, component parts, spare parts made by the operating organization, are in store for media storage. Warehouse and storage facilities provide maintenance parts and spare parts RN able to store;
technical readiness to number three - missile units tested, reloaded on installation and low truck and are on UGC PH. SHM is collected and in the workplace TC SHM. Equipment and systems are ready to UTK to conduct work in accordance with the schedule of training RN, CS alerted to the application;
technical readiness to number two - rocket launcher units are docked, inspected the systems on board RN in full, ILV assembled, tested and is in storage in the UGC space rocket ready for IC removal. Technological equipment, technical systems and structures SK ready to receive and work with RKN;
technical readiness to number one - ILV is installed and tested to CP, terrestrial communications docked. SC is in readiness for work on the fueling and launch space rocket.
UGC is ready to work with ILV in the case of the failed launch.
Note:
In the conceptual design should be given the status and location determined by the time of PH in readiness, transfer times from one to another and the willingness of each of the rocket launch readiness, the number of transfers from one another in readiness.
3.2.1.4 Performance AAC must be at least 10 launches per year from one IP, and the duration of the preparation for the launch rocket out of supply should not exceed 20 calendar days.
Note: CBC building performance to a given value can be carried out in stages.
3.2.1.5 RKN at the SC, facilities and UGC SC, SC, and aggregates of UGC and the SC should be protected from lightning (lightning protection are provided.)
3.2.1.6 At the stage of EP must be addressed the following main tasks:
set design and schematics of the constituent parts of the complex allowing for the use of it as part of the PCA, as much as possible to prevent occurrence of accidents with possible errors personnel at all stages of development and operation;
defined methods and / or methods to ensure and confirm the level of safety requirements CBC;
compiled a list of possible accidents and emergency situations, indicating measures for their prevention, containment and elimination of consequences;
refined by collaboration of head developer components AAC;
defined procedures and work with the technology of separating parts of RKN in marine and terrestrial RP;
refined design schematics and technical complex (developed in the framework of the ROC "TC-East") subject to the general plan of the LC circuit, designed to AAC "Rus-M";
updated technical configuration of the starting complex of the AAC (developed in the framework of the ROC, "East-SC-A") taking into account the previously planned for SC AAC
"Rus-M" space with maximum use of engineering survey results obtained in the framework of the ROC "Rus-M", design and documentation.
3.2.2 Requirements for components of the AAC
3.2.2.1 Requirements for the launch vehicle
3.2.2.1.1 In the EP should be submitted materials with the following options ILV SHM:
with automated spacecraft, including the DM and KVTK;
with manned transport ships;
with large modules, including transportation and power module.
3.2.2.1.2 Energy should provide the possibility of PH elimination of payloads:
PTC weighing not less than 20 tons into low orbit (Hcr = 200 km, i = 51,7 deg.)
using RB KVTK automated spacecraft with masses less than:
8.0 tonnes in GTO (ΔV go into orbit in 1500 m / s);
5.0 tonnes into geostationary orbit (Hcr = 35 786 km, i = 0 deg.)
with the use of automated spacecraft DM with masses less than:
6.5 tonnes in GTO;
3.7 tons into geostationary orbit.
Notes:
A. Specified energy potential for the removal of spacecraft launch vehicle should be provided, taking into account the location of impact areas separating parts.
Two. Energy should provide opportunities ILV excretion PTC manned complex PCA weighing not less than 20 tonnes in the reference orbit with the parameters agreed with the developers of the PCA.
Three. Energy potential of ILV RB clarifies the results of the development of EP.
4. The mass of PTK during a flight to the moon confirmed the results of the development of technical design of the first stage of PCA.
3.2.2.1.3 Withdrawal of manned transport spacecraft should be in the nose cones of space in the complex PTC, developed under the ROC "PCA» (I phase).
Space warheads should include:
manned transport vehicle;
rocket unit emergency rescue;
assembly and the security unit;
upper stage (if necessary).
3.2.2.1.4 When fading out manned spacecraft launch vehicle must provide:
value of the quasi-static acceleration during ascent (with scatter parameters of engines and options RKN) should not exceed 4 g;
the maximum dynamic pressure for a standard fixed atmosphere should not exceed 4000 kg/cm2;
excretion of HGC with PTC on the "flat" trajectories. Parameters of the nominal trajectory should ensure the elimination of ILV-exceeding the specified values of acceleration on the atmospheric part of the descent vehicle is returned after the withdrawal of the emergency booster (not more than 12 g);
the maximum total level of acoustic pressure on the outer surface of the interface with the LV SHM with PTC should not exceed 151 dB;
launch the product at the site of the spatial angle of attack (including jet and wind without a gust of wind) on the dynamic pressure must not exceed P • q ≤ 12 000 kgf * grad/m2
Note:
In the course of EP Executive should take into account the requirements of the head developer of the PCA.
3.2.2.1.5 Selection RP MOs ILV should be tailored to meet the safety requirements in the ER (including marine areas) with an estimate of their possible variation with a reserve of energy. Number of RP on each track start should be minimal.
Size of RP should be determined taking into account the possible destruction of the MOs on the passive portion of the trajectory and to provide ingress or MOs of its fragments to the ER with a probability of 0.989.
Notes:
A. Selection and use of ILV ER Joints shall be agreed in due course with the competent authorities of the Russian Federation;
Two. Creation of the technical facilities and operating bases ER RN octane called for in the framework of the ROC, "RP-octane East."
3.2.2.1.6 In the EP should be submitted to:
restrictions on the launch velocity of wind, the flight profile and the gradient in the free atmosphere in the vicinity of the cosmodrome "East" in height, including corresponding zones of maximum dynamic pressure and maximum longitudinal overload;
ranges of distances fall of octane with the allowed loss of energy;
opportunities in the area of space to maneuver in order to launch the implementation of the orbital inclination, the inclination is different from the base;
scheme of diversion of the upper stage to orbit (trajectory) in a controlled manner, the composition of systems and units of upper-stage launch vehicle, excluding the possibility of orbital debris (Guiding Principles of the UN Committee on the debris, the General Assembly , A/62/20, GOST 52925 - 2008);
implementation of the scheme to propel spacecraft into orbit by supporting propulsion upper stage or spacecraft in order to secure the upper stage of flooding in the first half-coil of PH in a given area of the ocean;
necessary amount of experimental testing ground AAC;
required volume for a set of positive LEE statistics starts confirming a safe and secure running PTK;
of the experimental base, providing a full range of ground-based experimental testing of the AAC;
measures to reduce the cost of production of LV, including by reducing the cost of production engines.
3.2.2.1.7 Two-stage launch vehicle consisting of ILV to ensure the accuracy of GHG removal at a given point of a circular orbit with parameters H = 200 km, i = 51,6 ° with tolerances specified in the specifications
№ 8457/12.
3.2.2.1.8 Requirements for the sustainer engine
3.2.2.1.8.1 boosters in the ILV must ensure removal of the payload for a given level of reliability and safety.
3.2.2.1.8.2 The probability of failure-free operation of a single engine rocket with a confidence level of 0.9 should be 0.999 to the beginning of manned space launches.
3.2.2.1.8.3 In the EP has to be worked out the possibility of diagnosing performance in preparation for launch, including for the first stage sustainer rocket engine at a preliminary mode to the manual for about 1.5 s (to be confirmed by the results of EP).
3.2.2.1.9 Requirements Management System
3.2.2.1.9.1 SU RN should provide the possibility of organizing different types of command and information exchange with the RN SU SU PCA manned spacecraft, including the relay and multiplex (GOST R 52070-2003 - MIL STD 1553B) communication channels.
3.2.2.1.9.2 A list of commands, and the number of interfaces, command and organization of information exchange with HGC RN agreed with the developers of the PCA.
3.2.2.1.9.3 For the exchange of commands and signals between the ground equipment training at PTC IC and ground equipment SU RN in the preparation and start-up must be provided for coupling ground-based GC PH:
- With a set of automated control of the preparation of PTK on SK (KAU PTK on SK - part of the complex preparation of PTK on SK);
- Automated testing system for DCS SC (AIS PTK on SK - part of the complex preparation of PTK on SK).
3.2.2.1.9.4 The material must study the EP questions the sustainability movement, and manageability of all configurations of PH, especially with large fairings, as well as meet the requirements for the SU to limit the aerodynamic loading of the body pH in wind conditions spaceport "East" with the conduct of settlement and modeling the movement of ROP.
3.2.2.1.9.5 When deriving a two-stage rocket SU should provide:
a) In normal flight:
issuing commands to reset the elements RBAS, fairing separation and spacecraft from the launch vehicle. In this discharge TTDU RBAS allowed the final phase of the first stage launch vehicle (or the beginning of the second stage) with the dynamic pressure q <50 kg/m2, and axial load nx <1,7. Resetting the BEO is permitted on the final leg of the flight of the second stage nx <1,4 when the parameters required for removal of PTK single-turn trajectory. In this case, the requirements:
the time between separation and completion launch BEO should be minimal;
after separation from the launch vehicle head unit, if necessary should be provided in the input VA VA atmosphere and descend in the atmosphere;
issuing commands to reset the GO with the dynamic pressure q <15 kg/m2;
diagnosis NSHS;
b) if abnormal flight:
PH in the accident - the transfer to the PTK signal "Crash" and execution Avdou;
when receiving a signal from the PTC, "Crash" Avdou execution.
Notes:
A. SU RN must provide drop components PH landing outside VA.
Two. SU RN should ensure the sustainability of not less than one failure.
Three. Interfaces with SC RN Subki PTC PTC determined by the developer.
3.2.2.1.10 Requirements for on-board telemetry system
3.2.2.1.10.1 BSTI should provide the necessary amount of product measurements (parameters of any type, including video) and their transfer to the desired characteristics directly and through a relay satellite system space "Ray" in the means of land acquisition and processing for all stages of preparation and routine operation.
3.2.2.1.10.2 Information and telemetry software must include as basic structural elements:
BSTI;
ground receiving and recording station;
land information and managing a complex system of measurement;
expert system for automated analysis of telemetry data;
a means of gathering, transmission TMI (including satellite repeater) and communicate with developers enterprises ILV components and other interested organizations.
3.2.2.1.10.3 consumer navigation equipment should be part of the RTS-NP and ensure that the definition of navigation parameters of ILV signals Space Systems "GLONASS" and GPS.
3.2.2.1.10.4 shall be developed on-board satellite navigation and search tools to identify the signals of the GLONASS (GPS) coordinates of the sites fall octane first stage launch vehicle and trajectory of the fall of stage II launch vehicle in a given area of ocean and transmit the coordinates to the consumer via satellite link.