FRINK Linked Data Fragments server

Matches in SemOpenAlex for { <https://semopenalex.org/work/W2118190057> ?p ?o ?g. }

• W2118190057 endingPage "2270" @default.
• W2118190057 startingPage "2265" @default.
• W2118190057 abstract "This paper is concerned with the problem of determining the time history of position, velocity and thrust acceleration of a space vehicle given only angular observations at discrete times and without prior knowledge of a nominal trajectory. It is shown that the motion, which involves unmeasurable state variables and partially unknown system dynamics, can be mathematically modeled by a system of ordinary differential equations subject to distributed boundary conditions. The resulting system is then solved by iteration with a modified quasilinearization technique. Results obtained from application of the method to a logarithmic spiral orbit will be examined. It will be shown that the method exhibits high precision and fast convergence even with poor estimates of the initial values for the state vector that is used to start the iterative process. ONTINUOUSLY thrusted interplanetary vehicles of the future will require new techniques for their guidance and navigation. At the present time much research has been done on trajectory analysis and optimal control for these missions, yet little work has been done on the critical problem of orbit determination. Jordan1 has shown that it is possible to solve the problem of determining small perturbations in the vehicle's position, velocity, and acceleration by applying filtering techniques to the data if one has prior knowledge of the vehicle's nominal trajectory. Apparently no one, however, has solved the more difficult problem of determining the completely unknown position, velocity, and thrust program of a powered vehicle from the types of observations which are now available; namely telescopic (angular observations) and radar (range and range-rate), without knowledge of a good approximate nominal. In this paper it will be shown that the motion of a thrusted vehicle, which involves unmeasurable state variables and partially unknown system dynamics can be mathematicall y modeled by a system of ordinary differential equations subject to multipoint boundary conditions. Prior knowledge of the vehicle's nominal trajectory is not necessary for a solution. Furthermore, the method of solution is not necessarily restricted to the class of problems where the thrust acceleration magnitude is small compared to the gravitational acceleration. The analytic method of differential approximation and the numerical technique of quasilineariz ation are the basic mathematical tools which will be used to solve the problem. First, the unknown portion of the system dynamics, that which describes the thrust program, is represented by the method of differential approximation which was originally introduced by Bellman 2 for the purpose of state estimation, and extended to the present application by Carpenter.3 Upon application of differential approximation the complete system dynamics can be described by a set of ordi" @default.
• W2118190057 created "2016-06-24" @default.
• W2118190057 creator A5048359102 @default.
• W2118190057 creator A5084659478 @default.
• W2118190057 date "1970-12-01" @default.
• W2118190057 modified "2023-09-23" @default.
• W2118190057 title "Orbit determination for a thrusted space vehicle" @default.
• W2118190057 cites W1974299710 @default.
• W2118190057 cites W2030499163 @default.
• W2118190057 cites W2031363245 @default.
• W2118190057 doi "https://doi.org/10.2514/3.6098" @default.
• W2118190057 hasPublicationYear "1970" @default.
• W2118190057 type Work @default.
• W2118190057 sameAs 2118190057 @default.
• W2118190057 citedByCount "1" @default.
• W2118190057 crossrefType "journal-article" @default.
• W2118190057 hasAuthorship W2118190057A5048359102 @default.
• W2118190057 hasAuthorship W2118190057A5084659478 @default.
• W2118190057 hasConcept C111919701 @default.
• W2118190057 hasConcept C121332964 @default.
• W2118190057 hasConcept C127413603 @default.
• W2118190057 hasConcept C146978453 @default.
• W2118190057 hasConcept C196644772 @default.
• W2118190057 hasConcept C2776888684 @default.
• W2118190057 hasConcept C2778572836 @default.
• W2118190057 hasConcept C39432304 @default.
• W2118190057 hasConcept C41008148 @default.
• W2118190057 hasConcept C57879066 @default.
• W2118190057 hasConcept C87355193 @default.
• W2118190057 hasConceptScore W2118190057C111919701 @default.
• W2118190057 hasConceptScore W2118190057C121332964 @default.
• W2118190057 hasConceptScore W2118190057C127413603 @default.
• W2118190057 hasConceptScore W2118190057C146978453 @default.
• W2118190057 hasConceptScore W2118190057C196644772 @default.
• W2118190057 hasConceptScore W2118190057C2776888684 @default.
• W2118190057 hasConceptScore W2118190057C2778572836 @default.
• W2118190057 hasConceptScore W2118190057C39432304 @default.
• W2118190057 hasConceptScore W2118190057C41008148 @default.
• W2118190057 hasConceptScore W2118190057C57879066 @default.
• W2118190057 hasConceptScore W2118190057C87355193 @default.
• W2118190057 hasIssue "12" @default.
• W2118190057 hasLocation W21181900571 @default.
• W2118190057 hasOpenAccess W2118190057 @default.
• W2118190057 hasPrimaryLocation W21181900571 @default.
• W2118190057 hasRelatedWork W1976630818 @default.
• W2118190057 hasRelatedWork W1985270746 @default.
• W2118190057 hasRelatedWork W1996602965 @default.
• W2118190057 hasRelatedWork W1997589276 @default.
• W2118190057 hasRelatedWork W2039714632 @default.
• W2118190057 hasRelatedWork W2065532950 @default.
• W2118190057 hasRelatedWork W2081233191 @default.
• W2118190057 hasRelatedWork W2094425050 @default.
• W2118190057 hasRelatedWork W2976202745 @default.
• W2118190057 hasRelatedWork W237283816 @default.
• W2118190057 hasVolume "8" @default.
• W2118190057 isParatext "false" @default.
• W2118190057 isRetracted "false" @default.
• W2118190057 magId "2118190057" @default.
• W2118190057 workType "article" @default.