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On Spacecraft «Foton–M» №3

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On Spacecraft «Foton–M» №3 STATE RESEARCH AND PRODUCTION SPACE ROCKET CENTER «TsSKB-PROGRESS» LOW-COST LAUNCH SERVICES FOR MICRO SATELLITES BY MEANS OF UTILIZATION OF SOYUZ ORBITAL STAGE Dr. Ravil N. Akhmetov, Valentin I. Novikov, Prof., Dr. Igor V. Belokonov Собственность ГНПРКЦ «ЦСКБ-Прогресс» Allocation of Samara city Allocation of Samara city Allocation of Samara city Launch statistics of rockets, manufactured by "TsSKB-Progress" (as of 01.01.2008) Baikonur Plesetsk The confirmed Launch Total Failure Total Failure Total Failure serviceability index vehicle launches launches launches launches launches launches "Soyuz-2” 4 - 2 - 2 - 0,981 "Soyuz-U” 746 20 311 9 436 11 0,984 "Soyuz- 22 - 22 - - - 0,984 FG” "Soyuz- 70 - 70 - - - 0,984 U2” "Molniya- 278 2 53 1 225 1 0,980 M” "Vostok- 94 2 14 - 80 2 0,96 2M” "Soyuz- 8 - - - 8 - 0,95 M” "Soyuz-L” 3 - 3 - - - 0,9 "Soyuz” 32 2 32 2 - - 0,96 11A59 2 - 2 - - - 0,875 "Voskhod 299 14 138 3 161 11 0,95 ” "Vostok- 2 - 2 - - - 0,875 2A” "Vostok- 45 5 39 5 6 - 0,98 2” "Molniya” 40 11 40 11 - - 0,83 "Vostok” 26 8 26 8 - - 0,81 "R-7A” 28 2 25 2 3 - 0,94 Satellite 2 1 2 1 - - 0,83 Satellite 2 - 2 - - - 0,78 "R-7” 26 9 26 9 - - 0,78 Total 1729 launches 6 Resurs DK-1 Earth remote sensing spacecraft Manufactured 30 “Resurs-F” Earth remote sensing spacecraft Science spacecraft • Manufactured 15 “Foton”/"Foton‐M“ spacecraft for research in the field of space technology • Manufactured 11 “Bion” spacecraft for medical and biological research Place for additional payload , mass up to 50 kg Place for additional payload, mass up to 200 kg Bion‐M launch time ‐ 2011‐2012, inclination 64,9 deg., altitude 575 km New carrier rockets of Samara Rocket Space Center Soyuz‐1 Soyuz‐2‐3 • Power capacity of rocket Soyuz‐1 • (launch from Plesetsk cosmodrom) Orbit Inclination, Altitude, Payload Deg. km mass, kg Circle 62,8 200 2400 Circle 67,1 200 2600 Elliptical 82,5 200 x 1950 (300‐500) Polar 90 200 x 250 2300 Sun‐synhr. 97 250 x 600 2100 Workability of “Soyuz” carrier rocket third stage for carrying out of research experiments and microsatellites launching transfer compartment Life time of the third orbital stage 350 340 330 320 м 310 300 290 Orbit k height, 280 270 260 250 02468101214161820 Life time, days min middle max Now the market of microsatellite launching services is extended. For last 6 years have been launched more 50 microsatellites by a mass up to 11 kg. The cost per launch of one microsatellite of CubeSat type is evaluated in 15-25 thousand dollars. One of variants of decreasing of the microsatellite launching cost is utilization of orbital rocket stages for piggy back launching. Possible place for accommodation of additional payloads in rocket “Soyuz” is transfer compartment. Orbital parameters for this microsatellites will be corresponds to working orbits of the launcher. In most cases they are near-circle orbits an altitude about 300 km and inclinations from 51,8º up to 98º. The life time of these microsatellites will about 10 day if they can not do maneuvers. For installations of microsatellites can use of several types of transition compartments according for the launchers as "Soyuz" and "Soyuz - 2" : - The transition compartment of type A is recognized schedule to use for launching spacecraft such as Earth remote sensing "Resource-P“and research spacecraft "Foton-M", "Bion-M" since 2010. - The transition compartment of type B is used at start of cargo space vehicle such as “Progress-М/М1” on the ISS within the framework of the manned space program (not less than 4 launches in one year). Possible places for accommodation of additional payloads in î ê 5 ó÷ à ñ ò V I I I I 2 2 ó ó ÷ ÷ à à ñ ñ ò ò type A transfer compartment î î ê ê 1 1 1 1 À 5 5 ó ÷ 8 à À 2 ñ ò 3 î ÿ è í å ùî å ì ç à ð à í î ç 0 ê ' 4 ÿ à ì è ò ñ ó ï î Ä ) Ä Ò î ï ( À Ê Ì À ó ÷ à ñ 5 ò 2 î ê 2 37 I I I À À Ê î ã î â î ç à á à í î Ç 0 5 7 À - À à ê û ò ñ ü ò ñ î ê ñ î ë Ï " 2 - ç þ î Ñ " Í Ð ñ Î õ Ï ó÷ à ñ ò î ê 3 Î õ Ï ä î ï 1 1 3 ÿ Ä À - À à í ü ë å ò è í ë î ï î à "ê 2û - ò ç ñ þü î ò Ññ î" Í ê Ð ñ ñ î Î ë õ Ï Ï 0 5 9 ) Î õ Ï ( * À Ê Ì ÿ è í å ù å ì ç à ð à í î ç ó÷ à ñ ò î ê 3 ÿ à )ì Äè òÒ î ñ ï ó ( ï À î ÊÄ Ì " ç þ î Ñ " à ï è ò Í Ð 4 ê î ÿ è í å ù å ì ç à ð à í î ç ò à ñ ó÷ payloads in type B transfer compartment I I À Possible places for accommodation of additional Î õ Ï ä î ï è í å ï ó ò ñ I I I à ê î ë á " Ã " à ê à á à í î Ç I I I À Ê î ã î â î ç à á à í î Ç À 2 2 ê ê î î ò ò ñ ñ à à ÷ ÷ ó ó I 2 î ê ò ñ ÷ à V I ó ó÷ à ñ ò î ê 1 Accomodation of five CubeSat satellites in type B transfer compartment Adapter Transfer compartment Container for microsatellite Fuel tank of the third stage ÿ à í ò ó ï î Ï à ê ç ó ð ã à í ' 7 ) Î 0 õ 5 Ï 9 ( 4 à ê û 4 ò ñ ü ò R 1 4 9ñ 0 î ê ñ î ë Ï 0Î 6õ Ï ñ " ç þ î Ñ " à ï è ò Í Ð 0 0 1 R R R R R R 0 9 2 1 1 1 2 2 9 9 0 0 1 8 0 1 1 1 0 0 8 8 1 1 0 5 8 2 2 2 8 8 5 5 0 0 ÿ à ì è ò ñ ó ï î Ä Accomodation of microsatellites in type B transfer compartment ÿ è í å ù å ì ç à ð à í î ç I I Î õ Ï ä î ï I I I 37 À Ê î ã î â î ç à á à í î Ç 3 1 1 16 2 3 0 I V I Microsatellites can be located inside of transition compartments in defined admissible zones. These zones are defined from a condition of safety of base space vehicle. The capability of arranging of microsatellites outside of the specified zones (in particular, for type В transfer compartment) can be surveyed in addition. In this case additional study and mutual coordination of the zone corresponded with microsatellite construction, with a zone of the base space vehicle and a zone of the third stage of the launcher arranged under a transition compartment is required. Can be accommodation of some microsatellites as CubeSat which have dimensions 10×10×10 sm and a mass about 1 kg. Microsatellite can be established as immediately on transfer compartment body, and on previously timbered the special adapter with own separation system on transfer compartment. In transfer compartment the special manholes for a service of an additional payload are not provided, therefore microsatellite installation (with the adapter) on transfer compartment can be realized only on a maintenance area up to the moment of a docking of a base space vehicle with a transition compartment. The admissible total mass of microsatellite with adapter should not exceed 20 kg. Microsatellites are need located for disposing in admissible zones uniformly (on a mass) on a head loop of transfer compartment, in view of limitations on a static moment of inertia of a construction of a transition compartment. Temperature conditions around microsatellites: - On start: from +50 up to a minus 40°С (without thermostatic control); - In flight: from +130 up to a minus 40°С (up to separation from base space vehicle). Power supplies, security of a thermal condition, control and monitoring of microsatellite instrumentation should be carried out at the expense of own independent power sources and the gears included in a small space vehicle. The capability of the installation on transition compartment of additional instrumentation (gears, transmitters of control and monitoring, antennas, etc.) can be surveyed. The possible field of application of the small space vehicles launched by an introduced way, can become the problems on improvement and demonstrations of new technologies with a short term of orbital existence. Additional piggy back launching opportunities for small satellites • In the frames of Federal Space program our enterprise develops new “Bion‐M” No 1 spacecraft intended for medical biological research. • The launch of spacecraft is scheduled to the year 2010 (IV quarter) from Baikonur space range using “Soyuz” launcher. • The flight program foresees the injection of spacecraft to near‐circular orbit with the parameters • i=64,9°, H=450‐580 km • the specific value of altitude from the range will be specified in a year before the launch), 30 days orbital flight and return of descending vehicle with scientific hardware to the Earth.
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