Add Astra example: ascent+descent validation, hazard zone & abort#72
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A km-scale real-flight example built on RocketPy's "Astra" (Faraday Rocketry UPV, EuRoC 2022; Cesaroni 4263L1350-P, apogee ~3.25 km). Unlike the existing validation examples it validates trochia on BOTH legs of the flight: the recovery did not deploy cleanly, so the measured descent is near ballistic and can be checked against real data, not just the apogee. What it shows: - validation vs the measured trajectory (measured.dat): apogee 3260 m vs measured 3249 m (+0.3 %, t 25.0 s vs ~24 s); the as-flown partial-recovery descent reproduced to ~70 m over the 3.2 km fall (effective recovery CdA). - Cd sensitivity: a still-air Cd sweep shows the measured apogee selects a flight-averaged constant Cd ~ 0.55 (the transonic drag rise folded into one number; the rocket reaches ~Mach 0.88 at burnout). - hazard zone (落下分散) + abort (途中破談): a wind-direction sweep over four contingency scenarios (nominal dual-deploy / recovery-failure ballistic / motor-cutoff / cato) -> one landing footprint each, on an OSM basemap of the EuRoC site (Ponte de Sor) with the measured GPS track overlaid. Uses the 12 m rail / 84 deg / 133 deg launch geometry now expressible via the config [launcher] length & azimuth. Files: config.toml (hazard+abort), config-validation.toml (still-air reconstruction), measured.dat / measured-track.dat (RocketPy flight data, GPS dropout fixes removed), fetch-engine.sh, run.sh, the gnuplot scripts + footprints-map.py, and the four committed result plots. Also cites the example from the repo and examples READMEs. Co-Authored-By: Claude Opus 4.8 (1M context) <noreply@anthropic.com> Claude-Session: https://claude.ai/code/session_01LiKBVgTqjZV84zcMVY3w46
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概要
RocketPy の検証用ロケット "Astra"（Faraday Rocketry UPV / EuRoC 2022,
市販 Cesaroni 4263L1350-P, apogee ~3.25 km）を題材にした km スケールの
実飛行 example。既存の検証 example と違い、上昇と降下の両方を実測と
照合できるのが要点です（Astra は回収がうまく展開せず降下がほぼ弾道だったため、
apogee だけでなく降下も実データで検証できる）。
内容
1. 妥当性検証（実測トラジェクトリと比較）
config-validation.toml（無風で実飛行を再構成）降下は「回収部分展開」を有効 CdA としてキャリブレートし、実測記録が終わる
~145 m AGL まで ~70 m（約 2 %）で一致。
2. Cd 感度
無風で定数 Cd をスイープ → 実測 apogee が apogee を合わせる有効定数 Cd ≈ 0.55
を選ぶことを示す（遷音速の抗力上昇を 1 つの定数に畳み込み。燃焼終了で約 Mach 0.88）。
3. 警戒区域（落下分散）＋ 途中破談
config.toml：風向スイープ × 4 シナリオ（nominal=dual deploy / recovery-failure=弾道 / motor-cutoff / cato）→ シナリオごとの着地 footprint。打上げは 84° / 方位 133°
に傾けてあり、各 footprint は 133° 方向にバイアス。
EuRoC サイト（Ponte de Sor）の OSM 地図に実測 GPS トラックを重ねて表示：
モデル上の注意（README に明記）
recovery-failureシナリオは parachute なし（実飛行の部分回収より厳しい弾道）。massは装填エンジンを除いた機体質量（9.10 kg）。エンジンは.engから（装填 3.57 kg / 推進剤 2.02 kg）→ 離昇 12.67 kg は RocketPy モデルと一致。
catoは単体飛翔（推力停止＋回収無効）で、破片分散モデルではない。実行
run.shは通しで動作し、4 つの図がすべてバイト単位で同一に再生成される（差分ゼロ）。🤖 Generated with Claude Code