Add comprehensive guide for using Lambert's problem solution with
the Satellite class to generate state vectors without SGP4.

New files:
- docs/lambert-satellite-integration-guide.md: Complete guide covering
  Lambert solver basics, integration workflows, and advanced usage
- examples/lambert-state-vector.ts: Seven practical examples demonstrating
  Lambert IOD usage, numerical propagation, TLE conversion, transfer
  orbit planning, and validation

Updated:
- examples/README: Add instructions for running Lambert examples
- package-lock.json: Update dependencies after npm install

The guide covers:
- Basic Lambert solution from two position observations
- Using Lambert with RungeKutta89 propagator for high-precision propagation
- Converting Lambert solutions to Satellite objects via TLE
- Transfer orbit planning and delta-V calculations
- Multi-revolution transfers
- Short path vs long path comparison
- Solution validation and error handling

Examples demonstrate practical applications including orbit determination,
rendezvous planning, and transfer trajectory design.

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