Zobrazeno 1 - 10
of 38
pro vyhledávání: '"Ron Noomen"'
Autor:
Kapish Aggarwal, Ron Noomen
Publikováno v:
Advances in Space Research.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::4e718db8ea9311fe2a0039054d5b2ac7
https://doi.org/10.1016/j.asr.2022.07.023
https://doi.org/10.1016/j.asr.2022.07.023
Autor:
Maarten Schild, Ron Noomen
Publikováno v:
Advances in Space Research.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::b30b517633307c566e2cf3a1ab44337b
https://doi.org/10.1016/j.asr.2022.07.011
https://doi.org/10.1016/j.asr.2022.07.011
Publikováno v:
Journal of Guidance, Control, and Dynamics: devoted to the technology of dynamics and control, 44(4)
Verified interval orbit propagation provides mathematically guaranteed solutions of satellite position and velocity over time. These verified solutions are useful for conjunction analysis and other space-situational-awareness activities. Unfortunatel
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::1706549b43cb8a04b456f4f4c73a87ee
https://doi.org/10.2514/1.g004947
https://doi.org/10.2514/1.g004947
Autor:
Ron Noomen, Thomas V. Peters
Publikováno v:
Journal of Guidance, Control, and Dynamics: devoted to the technology of dynamics and control, 44(4)
This paper presents the theory for linear cotangential transfers and safe orbits for elliptic orbit rendezvous. Expressions for the transfer angle and the required ΔV’s are derived. Singularities in the algorithm can occur if the two orbits inters
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::fc06a294de807f53e5310cbc8c6bce32
https://doi.org/10.2514/1.g005152
https://doi.org/10.2514/1.g005152
Publikováno v:
Journal of the Astronautical Sciences, 68(1)
We develop a Gravity Assist Mapping to quantify the effects of a flyby in a two-dimensional circular restricted three-body situation based on Gaussian Process Regression (GPR). This work is inspired by the Keplerian Map and Flyby Map. The flyby is al
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::f78e10d9e707070c72a8ff3da1f151d4
https://doi.org/10.1007/s40295-021-00246-3
https://doi.org/10.1007/s40295-021-00246-3
Autor:
Liam Pieters, Ron Noomen
Publikováno v:
Advances in Space Research.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::2b78a75eb2a5f77e8767414cb1e6397b
https://doi.org/10.1016/j.asr.2022.04.049
https://doi.org/10.1016/j.asr.2022.04.049
Publikováno v:
Advances in Space Research, 68(6)
Inspired by the Keplerian Map and the Flyby Map, a Gravity Assist Mapping using Gaussian Process Regression for the fully spatial Circular Restricted Three-Body Problem is developed. A mapping function for quantifying the flyby effects over one orbit
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::b2cfe2dbe2ea5bd012075674695b0276
http://resolver.tudelft.nl/uuid:156e4db9-23f4-40d5-a927-e42bcd1536e9
http://resolver.tudelft.nl/uuid:156e4db9-23f4-40d5-a927-e42bcd1536e9
Publikováno v:
Journal of Guidance, Control, and Dynamics. 41:1276-1289
Satellite reentry predictions are used to determine the time and location of impacts of decaying objects. These predictions are complicated by uncertainties in the initial state and environment mod...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::4d7df28b4e72461052f873fbc8305a83
https://doi.org/10.2514/1.g003258
https://doi.org/10.2514/1.g003258
Publikováno v:
Advances in Space Research. 59:2522-2535
Accurate knowledge of satellite orbit errors is essential for many types of analyses. Unfortunately, for two-line elements (TLEs) this is not available. This paper presents a weighted differencing method using robust least-squares regression for esti
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::731d6a70c8b7255afe02e6374c00dd18
https://doi.org/10.1016/j.asr.2017.02.038
https://doi.org/10.1016/j.asr.2017.02.038
Autor:
Ron Noomen, Aleix Pinardell Pons
Publikováno v:
Advances in Space Research, 63(7)
GTO objects can potentially collide with operative satellites in LEO and GEO protected regions. Internationally accepted debris mitigation guidelines require that these objects exit these protected regions within 25 years, e.g. by re-entering and bur
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::118d67297503189a4911a4f3b5db5def
http://resolver.tudelft.nl/uuid:4e9741b2-ccf1-4a80-a352-66d38e2fdc9e
http://resolver.tudelft.nl/uuid:4e9741b2-ccf1-4a80-a352-66d38e2fdc9e