Satellite Orbit Determination L1-467
Unclaimed Principle — open for contribution
This Principle is declared in the catalog but has no reference solver, no pinned dataset, and is not registered on-chain. There is no reward pool. Submitting a cert against this Principle today will record the cert for reproducibility but pay zero PWM.
To claim it as a Bounty #7 contribution: open a PR adding (1) a reference solver, (2) ≥1 dataset pinned to IPFS, (3) updates to the L3 manifest with dataset CIDs. After verifier-agent triple-review, the founders' 3-of-5 multisig signs PWMRegistry.register() and the Principle becomes mineable.
Forward model E
Satellite Orbit Determination: Satellite orbit determination: estimate initial state vector from tracking data (range, range-rate, angles) using batch or sequential processing. The forward operator produces the measurement through a 3-node primitive DAG (M.ode.equations_of_motion…); recovery is posed as a parameter_estimation problem. Difficulty tier delta=3 with effective condition number kappa_eff~200; atmospheric_drag_uncertainty, SRP_modeling_error set the accuracy floor at the Omega boundary. See the forward_model field for the closed-form equation.
L-DAG
Well-posedness W
- Existence:
- true
- Uniqueness:
- true
- Stability:
- conditional
- κ:
- 5000
Existence of the recovered 6D_orbital_state_vector is guaranteed within the declared Omega bounds. Uniqueness holds on the measurement-supported subspace; out-of-support modes are controlled by declared priors. Stability is conditionally stable (kappa_eff ~= 200); atmospheric_drag_uncertainty dominates the stability cliff; the remaining mismatch parameters contribute higher-order bias terms. Gaussian sets the irreducible data-fidelity floor.
Solvability C
- Solver class:
- sequential-filter [batch_least_squares or extended_Kalman_filter (SGP4 for TLE)]
- Convergence rate q:
- 2
- Complexity:
- O(N_obs * N_state ** 2) for batch normal equations per iteration