{"title":"轨道机动","authors":"","doi":"10.1002/9781119455301.ch6","DOIUrl":null,"url":null,"abstract":"A classical manoeuvre problem would be to have an orbit with a known semi major axis a1, then change the velocity of the spacecraft to change this to a new value a2. The short motor burn which causes the change in velocity takes place with a value of r which is constant to both orbits. We thus know a1, a2 and r, so we can calculate the velocity required for both orbits, and hence the change in velocity to move between the two orbits.","PeriodicalId":101486,"journal":{"name":"Foundations of Space Dynamics","volume":"39 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2021-01-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Orbital Manoeuvres\",\"authors\":\"\",\"doi\":\"10.1002/9781119455301.ch6\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"A classical manoeuvre problem would be to have an orbit with a known semi major axis a1, then change the velocity of the spacecraft to change this to a new value a2. The short motor burn which causes the change in velocity takes place with a value of r which is constant to both orbits. We thus know a1, a2 and r, so we can calculate the velocity required for both orbits, and hence the change in velocity to move between the two orbits.\",\"PeriodicalId\":101486,\"journal\":{\"name\":\"Foundations of Space Dynamics\",\"volume\":\"39 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2021-01-26\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Foundations of Space Dynamics\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.1002/9781119455301.ch6\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Foundations of Space Dynamics","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1002/9781119455301.ch6","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
A classical manoeuvre problem would be to have an orbit with a known semi major axis a1, then change the velocity of the spacecraft to change this to a new value a2. The short motor burn which causes the change in velocity takes place with a value of r which is constant to both orbits. We thus know a1, a2 and r, so we can calculate the velocity required for both orbits, and hence the change in velocity to move between the two orbits.
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