SSC Swedish Space Corporation

Transcription

1 SSC Swedish Space Corporation Platforms for in-flight tests Gunnar Florin, SSC

2 Presentation outline SSC and Esrange Space Center Mission case: Sounding rocket platform, dedicated to drop tests Satellite launches from Esrange

3 Our history SSC Swedish Space Corporation Founded in 1972 Private company, 100% owned by Ministry of Finances Main office in Solna, Stockholm Launch range ESRANGE in Lapland, northern Sweden SSC Group with activities in 10 countries, 4 continents

4 Over 50 years in space 1961 The first sounding locket launch from Sweden 1966 First rocket from Esrange 1974 First balloon from Esrange to the Ural mountains 1978 Satellite data reception at Esrange Landsat Station 1990 Sounding rocket over 700 km

5 After 48 years at Esrange: balloon missions rocket launches and still counting

6 2015

7 Why Esrange?

8 The least populated area in Europe Esrange N E Norway Finland 6000 km 2 restricted airspace Kiruna Esrange

9 Esrange N E Norway Finland 6000 km 2 restricted airspace Kiruna Esrange

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12 Rocket missions at Esrange Payload Altitude Microgravity MAXUS kg 700 km 13 min MASER /TEXUS kg 260 km 6 min National programs kg km Student program kg 85 km -

13 Stratospheric Balloons Atmospheric physics Astronomy/astrophysics High altitude crane

14 マスタ D-SEND タイトルの書式設定 #1, Herkules マスタテキストの書式設定 第 2 レベル 第 3 レベル 第 4 レベル» 第 5 レベル 8th European Symposium on 2015/3/ March /3/9 Aerothermodynamics for Space Vehicles, Lisbon 15

15 Drop tests missions from Esrange Mikroba - micro gravity experiment in free flight DLR Hugyens drop test of moon probe 1995 CNES HSFD - high speed flight demonstrator (HOPE-X Reusable Launch Vehicle) D-SEND Drop tests for non-symm. sonic boom 2003 JAXA /CNES JAXA SHADT - Sub-scale high altitude parachute 2014 ESA Balloon launches up to 42 km SHARK - re-entering capsule UHT Ceramic 720 km 2010 Super-MAX super sonic parachute test 720 km 2016 ESA/CIRA ESA

16 Other in-flight opportunities Maser 13 Payload data transmitter demonstrating ability of enhanced data down-link bandwidth by SOQPSK modulation. 3 kg equipment with antenna system. Inertial Measurement Unit Breadboard, testing performance in representative launch, ascent and planetary descent/re-entry environment under ESA contracts, flying on ESA missions.

17 SSC provider of systems and sub-systems In addition to launch systems, SSC provides sub-systems for balloons and sounding rockets; Structures, gondolas service systems telemetry, power systems, gps, tracking systems, video system, parachute systems rocket motors, fin sets, radar systems, separation system, and also complete experiment systems for sounding rockets

18 Mission case: Sounding rocket platform dedicated to drop tests

19 Current situation High interest in making use of existing missions for going piggyback Difficulties: - Interfaces, engineering budgets are tight - Reluctance due to logistics to bring aboard passenger at late stage - Don t disturb the main mission! - Reluctance to involve other organisations in a National project - Dependency on main mission schedule

20 Drop tests High interest in Europe for using in-flight platforms for test/validation/verification of re-entry body technologies, inflatable structures, supersonic parachutes and thermal protection materials 6000 km2 impact area SSC can offer a recurrent sounding rocket platform with dedicated launches for releasing re-entry bodies from high altitudes, launched and recovered at Esrange Space Center. 120x70 km Drop tests from high-altitude (<42 km) balloons is already practice at Esrange, and can be used as complementary test platform.

21 Sounding Rocket mission case A low cost mission, configuration derived from Swedish Leewaves mission Apogee: Experiment payload: 100 km 50 kg Payload diameter: 14 inches ( 345 mm inside width)

22 Launch configuration Experiment module Rocket Motor: Motor adapter: Experiment module: Service module: Nose cone: Single-staged Improved Orion Housing motor igniter and payload separation system Accommodating the system to be tested (re-entry body) Housing GPS, TM transmitter and antennas (for safety tracking) Empty

23 Launch configuration Experiment module length (mm) mass (kg) Rocket Motor: inch Motor adapter: inch diameter Experiment payload: inch (356 mm) Service module: inch Nose cone: < 75 kg payload mass

24 Imp.Orion (Leewaves) total speed up to 40 seconds

25 Imp.Orion altitude and range profile

26 Improved Orion (Leewaves) acceleration profile

27 Experiment payload Housed in 14 diameter structure 1500 mm length 345 mm inside width 310 mm minimum diameter at radax joints Example of 14 inch structures with radax joints, narrowing the inner diameter from 345 to 310 mm at ends

28 Flight time line Once motor separation has occurred, the experiment can be initiated. Several possibilities/solutions for carrying missions; Ejecting a re-entry body from the inside of the experiment structure Splitting the experiment module open late in the descent phase, to release the experiment once the speed is high (as practiced in drop tests from balloons) Using nose-cone and service module as ballast mass for super-sonic parachute tests

29 Recurrent mission scenario With access to several motors of Improved Orion type, a recurrent mission scenario can be depicted. With ten missions over a number of years, non-recurrent system design and development costs would not be significant, and there could be several launches each year. Esrange is open for balloon and rocket launches through-out the year, apart for the month of September.

30 Cost picture Cost of the described low-cost scenario, with repeated flights: Around 600 k recurrent cost for flight ticket Around 200 k non-recurrent costs Flight ticket: motor with separation system, nose cone, service module, experiment outer structure, System AIV, launch campaign support, recovery campaign fee.

31 More possibilities for access to space Higher apogees than 100 km and larger diameters than 14 opens up for further range of tests. Missions with larger payload diameter (e.g. 16, 17, 20,.. inches) and higher apogees calls for different motor combinations than the one of the presented mission case, combinations which SSC can offer to provide and launch. Maser 12 launch from ESC, Maxus 8 launch from ESC, 275 kg scientific payload, 250 km apogee 510 kg of scientific payload, 700 km apogee

32 SATELLITE LAUNCHES FROM ESRANGE PROJECT RAINBOW

33 BACKGROUND With increasing demand for independent access to space and the Cubesat and small sat market expansion, SSC has initiated the idea of building a European launch capability of small satellites from Esrange Europe has a capability for launching large satellites but lacks the ability for small satellites A complement to Ariane and Vega Financed by EU and European organisations, not ESA s Launcher Program

34 THE CONCEPT: kg satellites. CubeSats are target payloads (commercial, governmental, scientific) Standardized orbit: h=500 km, i=97,4 (Sun-synchronous orbit) Node at 2200, 0600, or 1400 Local solar time Fixed launch periods: 2-3 times per year Deploy a constellation in three launches Green launch site, no hydrazine

35 Satellite launch area (4 km from main building) Sounding rocket launch area Balloon launch area Main building Satellite station Entrance

36 PROJECT STATUS Phase A study completed. Result: it is feasible to implement a satellite launch service at Esrange Phase B1 study initiated. Will concentrate on ensuring program engagement and momentum Goal: to launch small satellites from Esrange in 2020

37 WE HELP EARTH BENEFIT FROM SPACE!