Delta-v peta
Jumlah parobahan kecepatan anu diperlukeun pikeun ngaleupaskeun antara Bumi, orbit, Bulan, Mars jeung asteroid.
ESO/S. Guisard (www.eso.org/~sguisard) (CC BY 4.0)
Delta-v peta
Delta-v total
Langkah
Nilai nyaéta maneuver impulsif hiji arah, ideal kajaba ditandakeun biasa. Misi nyata nambahan kaleungitan jeung parubahan pesawat.
Jadwal data (alternatif teks)
| Saka | Ka_nggo | → | ← | Carane digawé |
|---|---|---|---|---|
| Lapisan Bumi | Orbit Bumi Rendah (200 km) | 9,4 km/s | 0 km/s (bisa nggunakake aerobraking) | biasa (diterbitake): Delta-v budget (Wikipedia, with its cited references), typical values including lossesLaunch to orbit: about 7.8 km/s of orbital speed plus losses to gravity and air drag. |
| Orbit Bumi Rendah (200 km) | Orbit transfer geostasioner | 2,45 km/s | 2,45 km/s (bisa nggunakake aerobraking) | diitung (ideal): Hohmann perigee burn, 200 km to 35,786 km altitude, equatorial |
| Orbit transfer geostasioner | Orbit | 1,48 km/s | 1,48 km/s | diitung (ideal): Hohmann apogee burn, no plane changeFrom a launch site away from the equator, also changing the orbit's tilt adds a few hundred metres per second. |
| Orbit Bumi Rendah (200 km) | Bumi escape | 3,22 km/s | 3,22 km/s (bisa nggunakake aerobraking) | diitung (ideal): Escape speed minus circular speed at 200 km |
| Orbit Bumi Rendah (200 km) | Transfer menyang Bulan | 3,13 km/s | 3,13 km/s (bisa nggunakake aerobraking) | diitung (ideal): Raise apogee to the Moon's mean distance |
| Transfer menyang Bulan | Orbit Bulan Rendah (100 km) | 0,82 km/s | 0,82 km/s | diitung (ideal): Patched conic capture into a 100 km lunar orbit |
| Orbit Bulan Rendah (100 km) | Lapisan Bulan | 1,63 km/s | 1,63 km/s | diitung (ideal): Circular speed at 100 km (ideal, no gravity losses; real landings need more) |
| Orbit Bumi Rendah (200 km) | Transfer menyang Mars | 3,61 km/s | 3,61 km/s (bisa nggunakake aerobraking) | diitung (ideal): Earth-Mars Hohmann departure from 200 km, Oberth effect included |
| Transfer menyang Mars | Orbit Mars ngisor (300 km) | 2,09 km/s (bisa nggunakake aerobraking) | 2,09 km/s | diitung (ideal): Capture into a 300 km circular Mars orbit |
| Orbit Mars ngisor (300 km) | Mars | 0 km/s (bisa nggunakake aerobraking) | 4,1 km/s | biasa (diterbitake): Delta-v budget (Wikipedia, with its cited references), typical values including lossesSatelit ieu diwangun ku dua bagian: awak (saperti satelit) jeung sistem peluncuran (saperti pesawat ruang angkasa). |
| Orbit Bumi Rendah (200 km) | Asteroid (Bennu) | 4,11 km/s | 4,11 km/s (bisa nggunakake aerobraking) | diitung (ideal): Heliocentric Hohmann 1 au to Bennu's semi-major axis, coplanar (ignores its 6 degree inclination and its eccentricity); departure from 200 km LEO |
| Orbit Bumi Rendah (200 km) | Orbit Ceres | 9,48 km/s | 9,48 km/s (bisa nggunakake aerobraking) | diitung (ideal): Heliocentric Hohmann 1 au to Ceres, coplanar (ignores its 10.6 degree inclination); departure from 200 km LEO, capture into a 200 km Ceres orbit |
Alat jeung pelajaran ngagunakeun model anu diserepkeun ngan ukur pikeun diajar. Éta henteu kedah dianggo pikeun navigasi, perencanaan misi atanapi kaputusan operasi naon waé. Sertifikat bébas sareng henteu diakreditasi. Waca isi pendidikan