A new strategy for lunar soft landing
Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. T...
Ausführliche Beschreibung
Gespeichert in:
| Autor*in: |
Shijie, Xu [verfasserIn] |
|---|
| Format: |
E-Artikel |
|---|---|
| Sprache: |
Englisch |
| Erschienen: |
2007 |
|---|
| Schlagwörter: |
|---|
| Anmerkung: |
© American Astronautical Society, Inc. 2007 |
|---|
| Übergeordnetes Werk: |
Enthalten in: The Journal of the Astronautical Sciences - Springer-Verlag, 2006, 55(2007), 3 vom: Sept., Seite 373-387 |
|---|---|
| Übergeordnetes Werk: |
volume:55 ; year:2007 ; number:3 ; month:09 ; pages:373-387 |
| Links: |
|---|
| DOI / URN: |
10.1007/BF03256530 |
|---|
| Katalog-ID: |
SPR036432717 |
|---|
| LEADER | 01000caa a22002652 4500 | ||
|---|---|---|---|
| 001 | SPR036432717 | ||
| 003 | DE-627 | ||
| 005 | 20230328165746.0 | ||
| 007 | cr uuu---uuuuu | ||
| 008 | 201007s2007 xx |||||o 00| ||eng c | ||
| 024 | 7 | |a 10.1007/BF03256530 |2 doi | |
| 035 | |a (DE-627)SPR036432717 | ||
| 035 | |a (SPR)BF03256530-e | ||
| 040 | |a DE-627 |b ger |c DE-627 |e rakwb | ||
| 041 | |a eng | ||
| 100 | 1 | |a Shijie, Xu |e verfasserin |4 aut | |
| 245 | 1 | 2 | |a A new strategy for lunar soft landing |
| 264 | 1 | |c 2007 | |
| 336 | |a Text |b txt |2 rdacontent | ||
| 337 | |a Computermedien |b c |2 rdamedia | ||
| 338 | |a Online-Ressource |b cr |2 rdacarrier | ||
| 500 | |a © American Astronautical Society, Inc. 2007 | ||
| 520 | |a Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. | ||
| 650 | 4 | |a Vertical Velocity |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Tensile Force |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Lunar Surface |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Soft Landing |7 (dpeaa)DE-He213 | |
| 650 | 4 | |a Assist Module |7 (dpeaa)DE-He213 | |
| 700 | 1 | |a Jianfeng, Zhu |4 aut | |
| 773 | 0 | 8 | |i Enthalten in |t The Journal of the Astronautical Sciences |d Springer-Verlag, 2006 |g 55(2007), 3 vom: Sept., Seite 373-387 |w (DE-627)SPR036426385 |7 nnns |
| 773 | 1 | 8 | |g volume:55 |g year:2007 |g number:3 |g month:09 |g pages:373-387 |
| 856 | 4 | 0 | |u https://dx.doi.org/10.1007/BF03256530 |z lizenzpflichtig |3 Volltext |
| 912 | |a GBV_USEFLAG_A | ||
| 912 | |a SYSFLAG_A | ||
| 912 | |a GBV_SPRINGER | ||
| 951 | |a AR | ||
| 952 | |d 55 |j 2007 |e 3 |c 09 |h 373-387 | ||
| author_variant |
x s xs z j zj |
|---|---|
| matchkey_str |
shijiexujianfengzhu:2007----:nwtaeyolnr |
| hierarchy_sort_str |
2007 |
| publishDate |
2007 |
| allfields |
10.1007/BF03256530 doi (DE-627)SPR036432717 (SPR)BF03256530-e DE-627 ger DE-627 rakwb eng Shijie, Xu verfasserin aut A new strategy for lunar soft landing 2007 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society, Inc. 2007 Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. Vertical Velocity (dpeaa)DE-He213 Tensile Force (dpeaa)DE-He213 Lunar Surface (dpeaa)DE-He213 Soft Landing (dpeaa)DE-He213 Assist Module (dpeaa)DE-He213 Jianfeng, Zhu aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 55(2007), 3 vom: Sept., Seite 373-387 (DE-627)SPR036426385 nnns volume:55 year:2007 number:3 month:09 pages:373-387 https://dx.doi.org/10.1007/BF03256530 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 55 2007 3 09 373-387 |
| spelling |
10.1007/BF03256530 doi (DE-627)SPR036432717 (SPR)BF03256530-e DE-627 ger DE-627 rakwb eng Shijie, Xu verfasserin aut A new strategy for lunar soft landing 2007 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society, Inc. 2007 Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. Vertical Velocity (dpeaa)DE-He213 Tensile Force (dpeaa)DE-He213 Lunar Surface (dpeaa)DE-He213 Soft Landing (dpeaa)DE-He213 Assist Module (dpeaa)DE-He213 Jianfeng, Zhu aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 55(2007), 3 vom: Sept., Seite 373-387 (DE-627)SPR036426385 nnns volume:55 year:2007 number:3 month:09 pages:373-387 https://dx.doi.org/10.1007/BF03256530 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 55 2007 3 09 373-387 |
| allfields_unstemmed |
10.1007/BF03256530 doi (DE-627)SPR036432717 (SPR)BF03256530-e DE-627 ger DE-627 rakwb eng Shijie, Xu verfasserin aut A new strategy for lunar soft landing 2007 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society, Inc. 2007 Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. Vertical Velocity (dpeaa)DE-He213 Tensile Force (dpeaa)DE-He213 Lunar Surface (dpeaa)DE-He213 Soft Landing (dpeaa)DE-He213 Assist Module (dpeaa)DE-He213 Jianfeng, Zhu aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 55(2007), 3 vom: Sept., Seite 373-387 (DE-627)SPR036426385 nnns volume:55 year:2007 number:3 month:09 pages:373-387 https://dx.doi.org/10.1007/BF03256530 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 55 2007 3 09 373-387 |
| allfieldsGer |
10.1007/BF03256530 doi (DE-627)SPR036432717 (SPR)BF03256530-e DE-627 ger DE-627 rakwb eng Shijie, Xu verfasserin aut A new strategy for lunar soft landing 2007 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society, Inc. 2007 Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. Vertical Velocity (dpeaa)DE-He213 Tensile Force (dpeaa)DE-He213 Lunar Surface (dpeaa)DE-He213 Soft Landing (dpeaa)DE-He213 Assist Module (dpeaa)DE-He213 Jianfeng, Zhu aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 55(2007), 3 vom: Sept., Seite 373-387 (DE-627)SPR036426385 nnns volume:55 year:2007 number:3 month:09 pages:373-387 https://dx.doi.org/10.1007/BF03256530 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 55 2007 3 09 373-387 |
| allfieldsSound |
10.1007/BF03256530 doi (DE-627)SPR036432717 (SPR)BF03256530-e DE-627 ger DE-627 rakwb eng Shijie, Xu verfasserin aut A new strategy for lunar soft landing 2007 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © American Astronautical Society, Inc. 2007 Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. Vertical Velocity (dpeaa)DE-He213 Tensile Force (dpeaa)DE-He213 Lunar Surface (dpeaa)DE-He213 Soft Landing (dpeaa)DE-He213 Assist Module (dpeaa)DE-He213 Jianfeng, Zhu aut Enthalten in The Journal of the Astronautical Sciences Springer-Verlag, 2006 55(2007), 3 vom: Sept., Seite 373-387 (DE-627)SPR036426385 nnns volume:55 year:2007 number:3 month:09 pages:373-387 https://dx.doi.org/10.1007/BF03256530 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER AR 55 2007 3 09 373-387 |
| language |
English |
| source |
Enthalten in The Journal of the Astronautical Sciences 55(2007), 3 vom: Sept., Seite 373-387 volume:55 year:2007 number:3 month:09 pages:373-387 |
| sourceStr |
Enthalten in The Journal of the Astronautical Sciences 55(2007), 3 vom: Sept., Seite 373-387 volume:55 year:2007 number:3 month:09 pages:373-387 |
| format_phy_str_mv |
Article |
| institution |
findex.gbv.de |
| topic_facet |
Vertical Velocity Tensile Force Lunar Surface Soft Landing Assist Module |
| isfreeaccess_bool |
false |
| container_title |
The Journal of the Astronautical Sciences |
| authorswithroles_txt_mv |
Shijie, Xu @@aut@@ Jianfeng, Zhu @@aut@@ |
| publishDateDaySort_date |
2007-09-01T00:00:00Z |
| hierarchy_top_id |
SPR036426385 |
| id |
SPR036432717 |
| language_de |
englisch |
| fullrecord |
<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">SPR036432717</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230328165746.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">201007s2007 xx |||||o 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/BF03256530</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)SPR036432717</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(SPR)BF03256530-e</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Shijie, Xu</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="2"><subfield code="a">A new strategy for lunar soft landing</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2007</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© American Astronautical Society, Inc. 2007</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Vertical Velocity</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Tensile Force</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Lunar Surface</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Soft Landing</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Assist Module</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Jianfeng, Zhu</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">The Journal of the Astronautical Sciences</subfield><subfield code="d">Springer-Verlag, 2006</subfield><subfield code="g">55(2007), 3 vom: Sept., Seite 373-387</subfield><subfield code="w">(DE-627)SPR036426385</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:55</subfield><subfield code="g">year:2007</subfield><subfield code="g">number:3</subfield><subfield code="g">month:09</subfield><subfield code="g">pages:373-387</subfield></datafield><datafield tag="856" ind1="4" ind2="0"><subfield code="u">https://dx.doi.org/10.1007/BF03256530</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_SPRINGER</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">55</subfield><subfield code="j">2007</subfield><subfield code="e">3</subfield><subfield code="c">09</subfield><subfield code="h">373-387</subfield></datafield></record></collection>
|
| author |
Shijie, Xu |
| spellingShingle |
Shijie, Xu misc Vertical Velocity misc Tensile Force misc Lunar Surface misc Soft Landing misc Assist Module A new strategy for lunar soft landing |
| authorStr |
Shijie, Xu |
| ppnlink_with_tag_str_mv |
@@773@@(DE-627)SPR036426385 |
| format |
electronic Article |
| delete_txt_mv |
keep |
| author_role |
aut aut |
| collection |
springer |
| remote_str |
true |
| illustrated |
Not Illustrated |
| topic_title |
A new strategy for lunar soft landing Vertical Velocity (dpeaa)DE-He213 Tensile Force (dpeaa)DE-He213 Lunar Surface (dpeaa)DE-He213 Soft Landing (dpeaa)DE-He213 Assist Module (dpeaa)DE-He213 |
| topic |
misc Vertical Velocity misc Tensile Force misc Lunar Surface misc Soft Landing misc Assist Module |
| topic_unstemmed |
misc Vertical Velocity misc Tensile Force misc Lunar Surface misc Soft Landing misc Assist Module |
| topic_browse |
misc Vertical Velocity misc Tensile Force misc Lunar Surface misc Soft Landing misc Assist Module |
| format_facet |
Elektronische Aufsätze Aufsätze Elektronische Ressource |
| format_main_str_mv |
Text Zeitschrift/Artikel |
| carriertype_str_mv |
cr |
| hierarchy_parent_title |
The Journal of the Astronautical Sciences |
| hierarchy_parent_id |
SPR036426385 |
| hierarchy_top_title |
The Journal of the Astronautical Sciences |
| isfreeaccess_txt |
false |
| familylinks_str_mv |
(DE-627)SPR036426385 |
| title |
A new strategy for lunar soft landing |
| ctrlnum |
(DE-627)SPR036432717 (SPR)BF03256530-e |
| title_full |
A new strategy for lunar soft landing |
| author_sort |
Shijie, Xu |
| journal |
The Journal of the Astronautical Sciences |
| journalStr |
The Journal of the Astronautical Sciences |
| lang_code |
eng |
| isOA_bool |
false |
| recordtype |
marc |
| publishDateSort |
2007 |
| contenttype_str_mv |
txt |
| container_start_page |
373 |
| author_browse |
Shijie, Xu Jianfeng, Zhu |
| container_volume |
55 |
| format_se |
Elektronische Aufsätze |
| author-letter |
Shijie, Xu |
| doi_str_mv |
10.1007/BF03256530 |
| title_sort |
new strategy for lunar soft landing |
| title_auth |
A new strategy for lunar soft landing |
| abstract |
Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. © American Astronautical Society, Inc. 2007 |
| abstractGer |
Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. © American Astronautical Society, Inc. 2007 |
| abstract_unstemmed |
Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy. © American Astronautical Society, Inc. 2007 |
| collection_details |
GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER |
| container_issue |
3 |
| title_short |
A new strategy for lunar soft landing |
| url |
https://dx.doi.org/10.1007/BF03256530 |
| remote_bool |
true |
| author2 |
Jianfeng, Zhu |
| author2Str |
Jianfeng, Zhu |
| ppnlink |
SPR036426385 |
| mediatype_str_mv |
c |
| isOA_txt |
false |
| hochschulschrift_bool |
false |
| doi_str |
10.1007/BF03256530 |
| up_date |
2024-07-03T17:34:40.979Z |
| _version_ |
1803580165042733057 |
| fullrecord_marcxml |
<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">SPR036432717</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20230328165746.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">201007s2007 xx |||||o 00| ||eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/BF03256530</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)SPR036432717</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(SPR)BF03256530-e</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Shijie, Xu</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="2"><subfield code="a">A new strategy for lunar soft landing</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2007</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© American Astronautical Society, Inc. 2007</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Abstract A new strategy based on a windlass device is proposed to deal with the terminal descent of a lunar soft landing mission in this paper. The lunar lander considered here consists of a rover and an assist module (AM) which is equipped with three decelerating thrusters and a lateral thruster. The rover and the AM are connected by a tether (mass is negligible) which winds around the windlass. The dynamics of the terminal descent process is modeled. The guidance laws for the terminal descent phase are derived. Both fuel optimality and lander safety are considered. The design of the terminal guidance laws in this paper are separated into three stages: firstly, finding the activation point of the decelerating thrusters to minimize fuel consumption; secondly, determining the tensile force of the tether for deployment; and finally, designing the tether’s tensile force to make the rover track the desired velocity-altitude profile. The proposed soft landing strategy needs only the measurements of altitude and vertical velocity. Therefore, it is easy to implement. It effectively prevents the decelerating thrusters’ plume from damaging the lander due to ground interference. Moreover, it is robust against the uncertainties of initial altitude and vertical velocity. Numerical simulation results illustrate the feasibility of the proposed soft landing strategy.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Vertical Velocity</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Tensile Force</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Lunar Surface</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Soft Landing</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Assist Module</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Jianfeng, Zhu</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">The Journal of the Astronautical Sciences</subfield><subfield code="d">Springer-Verlag, 2006</subfield><subfield code="g">55(2007), 3 vom: Sept., Seite 373-387</subfield><subfield code="w">(DE-627)SPR036426385</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:55</subfield><subfield code="g">year:2007</subfield><subfield code="g">number:3</subfield><subfield code="g">month:09</subfield><subfield code="g">pages:373-387</subfield></datafield><datafield tag="856" ind1="4" ind2="0"><subfield code="u">https://dx.doi.org/10.1007/BF03256530</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_SPRINGER</subfield></datafield><datafield tag="951" ind1=" " ind2=" "><subfield code="a">AR</subfield></datafield><datafield tag="952" ind1=" " ind2=" "><subfield code="d">55</subfield><subfield code="j">2007</subfield><subfield code="e">3</subfield><subfield code="c">09</subfield><subfield code="h">373-387</subfield></datafield></record></collection>
|
| score |
7.399639 |