SOYUZ-IKAR-FREGAT 1. IDENTIFICATION. 1.1 Name. 1.2 Classification Family : SOYUZ Series : SOYUZ Version : SOYUZ-IKAR SOYUZ-FREGAT

Transcription

1 1. IDENTIFICATION 1.1 Name 1.2 Classification Family : SOYUZ Series : SOYUZ Version : SOYUZ-IKAR SOYUZ-FREGAT Category : SPACE LAUNCH VEHICLE Class : Medium Launch Vehicle (MLV) Type : Expendable Launch Vehicle (ELV) 1.3 Manufacturer : Ts SKB 18, Pskovskaya Str. SAMARA Russian Federation Telephone: (78462) Fax: (78462) Development manager : Ts SKB 1.5 Vehicle operator : Ts SKB 1.6 Launch service agency : FRANCE STARSEM (joint venture between RKA (25%) Ts SKB-Progress (25%), EADS (35%), ARIANESPACE (15%) Tour Maine-Montparnasse 33, avenue du Maine - BP PARIS Cedex 15 Telephone: Fax: Launch cost : About 40 M$ (Starsem commercial price) 2. STATUS 2.1 Vehicle status : Operationnal 2.2 Development period : (SOYUZ-IKAR version) For basic version, see SOYUZ data sheet 2.3 First launch : SOYUZ-IKAR: SOYUZ-FREGAT: December 2001 Page 1

2 3. PAYLOAD CAPABILITY AND CONSTRAINTS 3.1 Payload capability Low Earth Orbits SOYUZ-IKAR ORBIT TYPE MEO - CIRCULAR (1) ELLIPTICAL (2) SUN SYNCH. Altitude (km) / / Inclination ( ) Site Baïkonur Plesetsk Baïkonur Baïkonur Plesetsk Plesetsk mass (kg) (1) See Figure 1 (2) See Figure 2 FIGURE 1 - PERFORMANCE CAPABILITIES IN CIRCULAR ORBITS () FIGURE 2 - PERFORMANCE CAPABILITIES IN ELLIPTICAL ORBITS December 2001 Page 2

3 CIS Ø SOYUZ-FREGAT ORBIT TYPE Altitude (km) Inclination ( ) MEO - CIRCULAR SUN SYNCH / Site mass ELLIPTICAL (kg) FIGURE 3 - PERFORMANCE CAPABILITIES IN LOW CIRCULAR ORBITS FIGURE 4 - PERFORMANCE CAPABILITIES IN MEDIUM CIRCULAR ORBITS December 2001 Page 3

4 3.1.2 Geosynchronous and Interplanetary Orbits SOYUZ-IKAR No capability SOYUZ-FREGAT ORBIT TYPE GTO Altitude (km) 200 x km Inclination ( ) Site mass (kg) FIGURE 5 - PERFORMANCE CAPABILITIES IN GTO (km) Injection accuracy IKAR upper stage; 3-SIGMA For circular orbit (altitude km; inclination 51.8 ): radius : + 25 km, inclination : + 0.1, period : + 2 s. December 2001 Page 4

5 FREGAT upper stage; 3-SIGMA ORBITAL PARAMETERS CIRCULAR ORBIT ALTITUDE (km) GTO ALTITUDE (km) x Semi-major axis (km) ± 10 ± 60 ± 70 Altitude of apogee (km) - - ± 120 Altitude of perigee (km) - - ± 20 Eccentricity ± ± Inclination ( ) ± 6 ± 7 ± 5 Period (s) ± 12 ± 120 ± 170 Argument of perigee ( ) - - ± 11 RAAN(*) ( ) ± 9 ± 15 ± 15 (*) Right Ascension of the Ascending Node 3.2 Spacecraft orientation and separation Thermal control manœuvres : - Nominal payload separation velocity Rotation rate Deployment mechanism type : 0.5 m/s : 0 rpm : pyrotechnic initiators and springs (multiple satellite dispenser) 3.3 Payload interfaces Payload compartments and adaptors Payload fairing description Among the four fairings available as standard, the "type A" is used with the IKAR upper stage. It consists of a two half-shell carbon fiber structure with a longitudinal type separation system. Aluminium foil is applied to the internal and external surfaces of the nose fairing to protect against static electricity and to provide for optimal thermal conditions; thermal insulation is applied to the forward cone external surface. December 2001 Page 5

6 The "type S" fairing is used with the FREGAT upper stage. IKAR "A" type FREGAT "S" type Length 8.34 m 7.7 m External diameter 3.3 m 3.7 m Volume 27 m 3 52 m 3 FIGURE 6 - SOYUZ-IKAR TYPE A FAIRING December 2001 Page 6

7 Payload access provisions FIGURE 7 - SOYUZ-FREGAT TYPE S FAIRING Users can access the spacecraft for physical operations up to 10 h before lift-off by removing specially designed access doors. The allowable and locations of these doors (as well as those of the radiotransparent windows) vary with the fairing selected. Doors can be installed in all parts of the fairing except in areas close to the separation plane and in the vicinity of its interface with the intermediate bay. December 2001 Page 7

8 FIGURE 8 - ACCESS DOORS AND RF WINDOWS ACCEPTABLE AREAS FOR SOYUZ-IKAR Payload adaptor interface and dispenser STARSEM may provide a standard mm separation interface. In addition, user provided adaptor can be bolted to the reference interface or designed to meet existing western interfaces such as ARIANE 937 or Multiple launch configuration may imply the use of a dispenser such as in Globalstar missions to carry 4 satellites: - overall height: 2.7 m, - empty mass: 390 kg, - four attach points used for each satellite deployed by pyrotechnic initiators and springs. 3.4 Environments Mechanical environment DESIGNATION LEVEL (g) AT THE BASE OF THE SPACECRAFT NOTE Steady state Longitudinal 4.3 acceleration (see Figure 9) Lateral 0.4 Occurs at 1 st stage cut-off Low frequency vibration Random vibrations Longitudinal to 40 Hz Lateral Longitudinal and lateral See Figure 10 1 to 10 Hz 10 to 40 Hz December 2001 Page 8

9 FIGURE 9 - TYPICAL LONGITUDINAL STEADY STATE ACCELERATION (STAGE 1 TO 3) FIGURE 10 - SOYUZ-IKAR AND UPPER STAGE FLIGHT RANDOM VIBRATION (LATERAL) December 2001 Page 9

10 3.4.2 Acoustic vibrations Acoustic pressure values are presented with allowances made for possible variations of flight values at maximal dynamic pressure. They correspond to launch vehicle lift-off and flight phases at maximal dynamic pressure and applies to the payload volume Shock FIGURE 11 - TYPICAL ACOUSTIC FLIGHT LEVEL FOR STANDARD SOYUZ-IKAR FAIRING Stages separation and fairing jettisoning shock spectrum are presented in Figure 12. FIGURE 12 - SOYUZ-IKAR INTERSTAGE AND FAIRING SEPARATION SHOCKS December 2001 Page 10

11 3.4.4 Thermal environment Prelaunch temperature within the fairing The system is compatible with cleanliness class and has the following characteristics: - inlet temperature of injected air ajustable between 15 and 25 C with accuracy of + 2 C, - relative humidity 60%, - filtration 0,2 µm, - flow rate: m 3 /h. In-flight temperature under fairing The thermal flux density radiated by the fairing does not exceed 800 W/m 2 at any point. Aerothermal flux after fairing jettisoning Typically it varies from W/m 2 to zero within 50 s after fairing jettisoning. FIGURE 13 - TYPICAL VARIATION OF AIR TEMPERATURE UNDER SOYUZ-IKAR FAIRING December 2001 Page 11

12 3.4.5 Variation of static pressure under fairing FIGURE 14 - VARIATION OF STATIC PRESSURE UNDER SOYUZ-IKAR FAIRING 3.5 Operation constraints Ground constraints Coordination is exercised by Russian Space Agency (RSA) and the Ts SKB General Designer representing the entire launch authority. The "safety regulations" define the rules applicable to all operations including the use of hazardous systems or products. Launch rate capability: per year (Ts SKB wants to increase production to at least 25) Procurement lead time: about 23 months between contract signature and launch December 2001 Page 12

13 4. LAUNCH INFORMATION 4.1 Launch site Location The Baikonur cosmodrome (45 60'N, 63 40'E) in Kazakhstan (2 100 km to the South-East of Moscow) is used for commercial launches. Payload processing FIGURE 15 - SOYUZ LAUNCH COMPLEX For STARSEM operations at Baikonur, a modern new facility called STARSEM Payload Processing Facility has been built; it consists of: - the Payload Preparation Facility (PPF): the 290 m 2 PPF includes a class clean room and two control rooms, - the Hazardous Processing Facility (HPF): it covers a 290 m 2 surface and incorporates a class clean room, control room and safety shower, - the Upper Composite Integration Facility (UCIF): this 550 m 2 site has a class clean room. December 2001 Page 13

14 The customer payload is transported to the Baikonur Cosmodrome in its protective container, then delivered to the STARSEM Payload Processing Facility. The spacecraft is installed in the Payload Preparation Facility clean room, where final assembly is performed along with functional tests (nonhazardous mechanical and electrical tests). After completion of final assembly and the functional test, the satellite is then moved to the Hazardous Processing Facility for propellant filling. The payload is transferred to the Upper Composite Integration Facility to be integrated with the launch vehicle's upper stage. Integration is performed with the spacecraft and upper stage in the vertical position. Fairing encapsulation of the payload is performed in the Upper Composite Integration Facility and this completed upper composite is moved to the horizontal position using a special tilting unit and crane. The upper composite is transferred to the SOYUZ launch vehicle assembly building (MIK) where it is integrated with the launch vehicle and electrical checks are carried out before the complete launcher is transferred to the launch pad. Launch vehicle processing The following operations are carried out in the launch vehicle preparation MIK: - assembling of launch vehicle stages, - mating the upper stage/payload with the launch vehicle, - checking electrical circuits, - installation of the assembled launcher on the rail guided transportation and erection unit. The SOYUZ-IKAR and the SOYUZ-FREGAT are transported to the launch pad in a horizontal position. 4.2 Sequence of flight events SOYUZ-IKAR A typical flight sequence for mission is given. TIME AFTER LIFT-OFF s s 158 s 283 s 528 s 2 h 29 min 31 s 3 h 33 min 30 s EVENTS Ignition of stage 1 and 2 engines Lift-off Stage 1 separation Payload fairing separation Stage 2 separation Stage 3 separation; IKAR/Payload enter into parking orbit Ignition of IKAR upper stage Payload separation December 2001 Page 14

15 FIGURE 16 - TYPICAL ASCENT PROFILE FOR A SOYUZ-IKAR MISSION December 2001 Page 15

16 4.2.2 SOYUZ-FREGAT The typical suborbital ascent profile for a SOYUZ-FREGAT mission and its associated sequence of events is described in the following figure. FIGURE 17 - TYPICAL SUBORBITAL ASCENT PROFILE FOR A SOYUZ-FREGAT MISSION 4.3 Launch record data LAUNCH DATE SITE NUMBER OF SATELLITES ORBIT RESULT REMARK SOYUZ-IKAR SOYUZ-IKAR SOYUZ-IKAR SOYUZ-IKAR SOYUZ-IKAR SOYUZ-IKAR SOYUZ-FREGAT SOYUZ-FREGAT SOYUZ-FREGAT SOYUZ-FREGAT Success Success Success Success Success Success Success Success Success Success Failures : none Previsional reliability : - Success ratio : SOYUZ-IKAR: 6/6 = 100% SOYUZ-FREGAT: 4/4 = 100% 4.4 Planned launches Not available December 2001 Page 16

17 5. DESCRIPTION 5.1 Launch vehicle FIGURE 18 - SOYUZ-IKAR FIGURE 19 - SOYUZ-FREGAT 5.2 Overall vehicle SOYUZ-IKAR SOYUZ-FREGAT Overall length m m Maximum diameter m m Lift-off mass (approx.) 305 t 308 t December 2001 Page 17

18 5.3 General characteristics of the stages STAGE 1 (Boosters) Designation B, V, G, D Blocks Block A Block I IKAR FREGAT Manufacturer Ts SKB Ts SKB Ts SKB Ts SKB LAVOCHKIN Structure Aluminium Skinstringer Length (m) Diameter (m) Dry mass (t) Propellant: Type Liquid Liquid Liquid Liquid Liquid Fuel Kerosene Kerosene Kerosene UDMH UDMH Oxidizer LO 2 LO 2 LO 2 N 2 O 4 N 2 O 4 Propellant mass (kg) Fuel x Oxidizer x TOTAL x up to Tank pressure (bar) Total lift-off mass (t) December 2001 Page 18

19 FREGAT upper stage overview 1 - S5.92 main engine 2 - Fuel tanks 3 - Hydrazine bottle 4 - ACS thrusters 5 - Oxidizer tanks 6 - Telemetry system antenna 7 - Control system 8 - Equipment bay coverradiator 9 - Telemetry and tracking system 10 - Helium bottles 11 - Chemical batteries FIGURE 20 - THE FREGAT UPPER STAGE Launch vehicle growth In the future, STARSEM wants to launch an upgraded version called SOYUZ/ST which could use the ARIANE 4 fairing and is supposed to be able to accommodate both the IKAR and the FREGAT upper stages. December 2001 Page 19

20 5.4 Propulsion STAGE Designation RD-117 RD-118 RD D 61 S5.92 Manufacturer ENERGOMASH ENERGOMASH KHIMAUTOMATIKI KB MELNIKOV KB KHIMMASH Number of engines 4 (4 chambers + 2 verniers each) 1 (4 chambers + 4 verniers) 1 (4 chambers + 4 verniers) 1 (16 verniers) 1 (+ 8 ACS thrusters) Engine mass (kg) Feed syst. type Turbopump Turbopump Turbopump Gaz pressure Turbopump Mixture ratio to 2.10 Chamber pressure (bar) Cooling Liquid (Kerosene) Liquid (Kerosene) Specific impulse (s) Sea level Vacuum Thrust (kn) Sea level 813 x Vacuum 997 x Burning time (s) 120 < Nozzle expansion ratio Restart capability No No No Yes (up to 50) Yes (up to 20) 5.5 Guidance and control Guidance Inertial Two avionics systems are used. One is located on stage 2 and controls this stage and stage 1 (boosters). A second avionics package is located on stage 3 (intertank section) and is similar to the lower package. IKAR upper stage has its own semi-autonomous 3-axis inertial unit. December 2001 Page 20

21 5.5.2 Control STAGE Pitch, yaw, roll Movable aerodynamic fins and 8 gimballed verniers (deviation angles up to 45 ) 4 gimballed verniers (deviation angles up to 45 ) 4 gimballed verniers (deviation angles up to 40 ) IKAR: by gimballing nozzle (pitch, yaw) 16 thrusters (roll) (+ all control during ballistic phase) FREGAT: by translation of S5.92 engine or use of 8 ACS thrusters 6. DATA SOURCE REFERENCES 1 - SOYUZ User's manual - Issue 2 - June Jane's Space Directory p STARSEM documentation Orbireport.com 5 - SOYUZ User s manual - Issue 3 - April 2001 December 2001 Page 21