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“Good Practices” for long term orbit propagation and associated criteria verification in the frame of the French Space A

“Good Practices” for long term orbit propagation and associated criteria verification in the frame of the French Space Act. Hubert.Fraysse@cnes.fr. Presentation to ISO – Berlin - May 24 th 2011. Summary. 1. French Space Act : disposal orbits relatively to region A and B

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“Good Practices” for long term orbit propagation and associated criteria verification in the frame of the French Space A

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  1. “Good Practices” for long term orbit propagation and associated criteria verification in the frame of the French Space Act Hubert.Fraysse@cnes.fr Presentation to ISO – Berlin - May 24th 2011

  2. Summary 1. French Space Act : disposal orbits relatively to region A and B 2. Good Practices : overview 3. Focus on Solar Activity 4. STELA software Reference paper: Fraysse et al, « Long term orbit propagation techniques developed in the frame of the French Space Act », 22nd ISSFD, 2011 2

  3. French Space Act : disposal orbits • Technical methods are defined by CNES in the frame of the French Space Act whose objective is to ensure that the technical risks associated with space activities are properly mitigated • In line with IADC recommendations relative to regions A (LEO) & B (GEO) • Disposal orbits in the vicinity of these regions must not cross them within 100 years • Disposal orbits that cross the LEO region must re-enter the atmosphere in less than 25 years

  4. Good Practices: summary • “Good Practices” definition (with ISO documents 27852 and 26872 as Guidelines) for LEO and GEO orbit types (on-going activity for GTO type): • To propagate disposal orbits up to 100 years • To check the applicable criteria (25 years and 100 years rules) • “Minimum” Dynamical Models for each type of orbits * the effect on orbit eccentricity and ascending node of zonal terms up to J15 has to be considered when the inclination is close to the critical inclination (63.4 deg). J22 considered in the semi-analytical theory. ** the luni-solar perturbation is significant for sun synchronous orbits or orbits with apogee altitude in the upper range of the LEO region *** the effect of SRP has to be considered for orbits that go through a SRP / ”J2 secular effect” resonance (orbit inclination about 40, 80, 110 and 125°, see back-up chart)

  5. Good Practices: summary • Definition of computation parameters for the Solar Pressure and Drag Forces • Area “A”: if attitude is unpredictable -> mean area (random tumbling mode) • Reflectivity coefficient  1.5 (ISO recommendation) • Atmospheric model: NRMLMSISE-00 • Drag coefficient: reference law Cd = f(altitude) • Key difficulty: solar activity

  6. Focus on Solar activity : introduction • The result of a reentry duration computation strongly depends on the solar activity hypothesis : • Level (high, medium, low) of the next 3 or 4 solar cycles ~ 10 years • End of mission date / solar cycle ~ 5 years • Problems: • The level and the length of the next solar cycles are very uncertain • The end of mission date may shift • Difficulty in a Space Act process: An end of life orbit and strategy compliant at time “t” may not be compliant anymore if the solar activity prediction changes, or the end of mission date shifts. • New approach : “constant equivalent solar activity” 6

  7. F10.7 Focus on Solar activity : principles • Following this approach the solar activity is designed such that : • It is constant vs time : • The reentry duration computation no longer depends on the end of mission date and predictions • Equivalent to future possible solar activities : • The equivalence is from a 25 years reentry point of view, with a Z% probability level 1 Space Object 1 End of life orbit Equivalent constant solar activity Possible Future solar activities t 2 4 6 6 3 t t t 25 years lifetime in Z % of the cases 25 years lifetime 100% Z% 0% lifetime 25 years

  8. Focus on Solar activity : algorithm Algorithm to tune the constant equivalent solar activity (1/4) The tuning of the constant equivalent solar activity has been made using solar activity data (F10.7 and Ap) from the last decades and through a statistical approach Random Solar activity : • Data : 5 measured solar cycles (historical F10.7 and Ap data as in ISO approach #1) • 54 = 625 possibilities of four-cycles sequences (2 1 1 5 or 3 5 1 4 or 2 4 5 3 or 4 4 4 4 …) • Random realization of the initial date within the first cycle, twice for each sequence.  n = 1250 random predictions of solar activity These solar activities are considered as representative samples of the possible future solar activity.

  9. Focus on Solar activity : algorithm Algorithm to tune the constant equivalent solar activity (2/4) • For an initial orbit and a ballistic coefficient value • Run of the n reentry duration computations using the n random solar activity samples  Lifetime cumulative distribution function • Iteration on the initial orbit until the orbit lifetime is 25 years with a targeted Z% probability level

  10. Focus on Solar activity : algorithm Algorithm to tune the constant equivalent solar activity (3/4) • Iterations : change of the perigee of the orbit, fixed apogee Convergence when: 25 years  Z% (Z% = 50% in this case) • Computation of the reentry duration of the last orbit by using a constant solar activity and iteration on its value so that the reentry duration is 25 years • N.B. : tuning of F10.7 • Ap = 15 (arbitrary choice)

  11. Focus on Solar activity : algorithm Cd = 2.2 Algorithm to tune the constant equivalent solar activity (4/4) • The F10.7 constant (vs time) value may depend on initial conditions (orbit and ballistic coef) 1. Scan initial orbits (within LEO region) and ballistic coefficients and run the whole algorithm for each initial state (orbit and ballistic coefficient) 2. Analyze the sensitivity to these parameters 3. Fit a reference law on these simulation results • The algorithm works for any probability level of reentry within 25 years: 50% has been chosen in the frame of the French Space law

  12. Focus on Solar activity : result Finally the “constant equivalent solar activity” defined for LEO type orbits : • does not depend on inclination or local time of the RAAN of the initial orbit • depends on the apogee altitude of the initial orbit (log-function, R² > 99%) • depends on the ballistic coefficient of the space object (log-function, R² > 99%) A.Cd/m : ballistic coefficient (m2/kg) Za : apogee altitude (km) Z%=50% law

  13. Focus on Solar activity : Synthesis The use of the “constant equivalent solar activity” approach : • removes the sensitivity of the disposal maneuver cost to solar activity prediction uncertainties and to an end of mission date shift (during the spacecraft development process or later) • gives the information of a “mean 25 years reentry duration” (Z%=50%) considering all space objects using this approach Example (Parasol microsat): - DAS Solar activity file • Past and translated Solar Activity • Constant Equivalent Solar Activity

  14. Good Practices implemented in STELA software : Semi-Analytic Tool for End of Life Analysis • Used in the frame of the French Space Act to check the compliance with the rules but usable more generally • Rapid Semi analytical propagation (ISO “method 2” type) • Propagation of mean orbital parameters • Short periods added to compute osculating parameters when necessary • Includes: • rapid semi-analytic propagators (for LEO and GEO type orbits in the current version) • iterative modes helpful to choose disposal orbits parameters • a tool that computes the mean area of a spacecraft • JAVA based, usable as a software (GUI or batch mode) or a library • STELA is freeware  http://logiciels.cnes.fr/STELA • Curent version is 1.2.1. New 1.3 version expected beginning of June ( SRP for LEO, batch mode, other input frames, GUI improvements…). Version 2 including GTO propagation expected end of 2011

  15. Validation by comparison with CNES reference numerical propagators (high precision numerical integration, full dynamical model) on the following domain: • LEO type orbits: inside or at the vicinity of the LEO region (alt < 2200 km) • GEO type orbits:inside or at the vicinity of the GEO region (GEO alt  1000 km), initial inclination < 30 deg LEO typical results GEO typical results

  16. GEO propagation Mean area computation Computation configuration .xml GTO propagation Cd = f(alt) LEO propagation Solar activity = f(t) Plots Simulation configuration .xml Log File .txt Simulation Synthesis .txt Ephemeris (CCSDS) .txt 16

  17. Back-up 18

  18. Algorithm for an equivalent solar activity ( Generate Solar Activity files) OLT z % = 25 years ha, hp, i, S/m no yes Guess an new hp value that would lead to a OLTz% close to 25 years Guess an equivalent constant solar activity that lead to an OLT z % of 25 years Compute the 1250 OLT values with this hp value (monte carlo) OLT(F10.7) = 25 years no Compute the distribution function and the OLT z % yes Z% Constant equivalent solar activity 19

  19. J2/SRP resonant orbits • Resonance condition: • (a,i) leading to a J2/SRP resonance (“0” curves on figures) for LEO quasi-circular orbits N.B. : slight sensitivity to eccentricity value • J2/SRP resonance (if any) impact mainly the orbit eccentricity evolution 20

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