An yi wannan darasi da wani Local Solar System ma'aikacin ƙungiyar Foundation kuma za'a iya inganta shi da mai duba da ya dace. Shin kana da kwarewa a cikin wannan batutuwa? Suggest an edit
Wannan ita ce ƙa’ida mafi ban sha’awa ta jirgin sama na orbital: don ka samu ka daina, kuma don ka kai mafita ka yi sauri, sa’an nan kuma ka ƙare da yin sauri. Walter Hohmann, wani injiniyan birni na Jamus, ya yi aiki a cikin 1925 kan hanyar da ta fi sauki don motsa tsakanin orbits biyu masu juyawa. A kusan kowace salula a geostationary orbit samu zuwa nan da amfani da tunaninsa.
Ka yi sauri ka hau, kuma za ka isa cikin sauri fiye da yadda ka bar.
Look
- Burn 1, forwards. Saurin da aka kara bai sa tauraron dan adam ya yi sauri ba a cikin ɗaurewarsa: yana shimfiɗa ɗaurewar zuwa ellipse. Maɓallin ƙananan yana zaune inda ƙonawa ya faru; gefen da ke kusa yana tashi zuwa tsayin maɓallin.
- Coast. Half an orbit without any engine. Sataiti na tashi kuma, kamar yadda aka yi wa kwallo, ya daina yayin da yake tafiya.
- Burn 2, forwards again. A sama yanzu yana da sauri sosai don ya zauna a can kuma zai iya faɗi baya. A na biyu ya sanya orbit da ke cikin wani tsawo.
Daga 300 km zuwa geostationary orbit biyu burns kara har zuwa kusan 3.9 km/s, da tafiyar take kusan 5 hours 17 minutes.
Understand
A cikin wannan littafin, an yi amfani da kalmar “a” a matsayin ma’anar “a” (a cikin Littafin 1:2). Wani ellipse na canja wurin Hohmann yana shafar daruruwan biyu, don haka maɓallinsa mai girma shine a_t = (r₁ + r₂)/2.
| Radius (km) | _Saurin (km/s) | |
|---|---|---|
| Cire a 300 km | 6,678 | 7.73 |
| Transfer, low point | 6,678 | 10.15 |
| Transfer, high point | 42,164 | 1.61 |
| Geostationary | 42,164 | 3.07 |
Burn 1 = 10.15 − 7.73 ≈ 2.43 km/s. Burn 2 = 3.07 − 1.61 ≈ 1.47 km/s. An yi amfani da wannan tsari ne a cikin tsarin lissafi na zamani (5.3).
(A gaskiya geostationary launches kuma dole ne su canza da orbit’s tilt daga launch site na latitude zuwa equator, wanda farashin fiye da; launching kusa da equator tsare mai.)
Master
Δv₁ = √(μ/r₁)·(√(2r₂/(r₁+r₂)) − 1), Δv₂ = √(μ/r₂)·(1 − √(2r₁/(r₁+r₂)))
Canja wurin Hohmann shine mafi ƙarancin canja wurin motsi biyu tsakanin coplanar circular orbits, har sai r₂/r₁ < 11.94. A baya ga wannan adadin bi-elliptic canja wurin (uku burns, tafiya a kan gaba da manufa) farashin kaɗan Δv, a kan farashin lokaci mai yawa.
Burning a kan kasa point ne kuma mafi kyau wuri don ƙara makamashi: Oberth tasiri ya ce da aka ba Δv canja orbital makamashi mafi yawan inda jirgin sama yana tafiya da sauri, saboda Δε ≈ v · Δv.
Try it
Yi amfani da vis-viva don duba gudun a sama na canja wurin: μ = 398,600 km³/s², r = 42,164 km, a = 24,421 km. Sa'an nan ka kwatanta shi da gudun kewayawa a 42,164 km. bambanci shine na biyu.
Great. kalubale ne inda koyon sticks.
Quick quiz
3 tambayoyi masu sauri. Zaɓi amsa don ka ga ko kai mai gaskiya ne.
-
Domin isa wani tsayi da ya fi girma na orbit, farkon burn shine:
- A Straight up
- B Forwards, speeding up
- C Backwards, slowing down
- D Sideways, out of the orbit plane
Nuna amsa
B. Forwards, speeding up
-
A cikin tsaunuka a tsakanin biyu wuta, da salula:
- A Speeds up as it climbs
- B Yana da sauri yayin da yake tashi
- C Keeps the same speed
- D Stops at the top
Nuna amsa
B. Yana da sauri yayin da yake tashi A cikin wannan yanayin, za a iya amfani da makamashi na kinetic don samar da makamashi na potential.
-
Why is the geostationary orbit useful?
- A Kuma shi ne mafi kusa ga ƙasa.
- B A satellite a can take daya rana ga kowace orbit, don haka shi ke zama a kan wani wuri mai kama da
- C Babu wani nauyin jiki a can
- D Shĩ ne mafi kusa ga jũna ga sarari (na tafiyar wata).
Nuna amsa
B. A satellite a can take daya rana ga kowace orbit, don haka shi ke zama a kan wani wuri mai kama da
Finish line
- Read the lesson
- Did the challenge
- Took the quiz
Mark the lesson complete to save it to your progress on this device.
An kammala darasi. Mai kyau!
Up next Fara tagogi: hanyar zuwa MarsWords in this lesson
Sources
- W. Hohmann, Die Erreichbarkeit der Himmelskörper (1925), NASA technical translation F-44
- NASA JPL, Basics of Space Flight, Chapter 4: Trajectories
- JPL SSD, Astrodynamic parameters
- R. Bate, D. Mueller, J. White, Fundamentals of Astrodynamics (Dover, 1971), ch. 3
Wannan darasi yana da lasisin CC BY-SA 4.0.