Protection against overturning of a lunar-planetary lander using a controlled landing gear
This paper describes an attitude control method to prevent the overturning of lunar and planetary landers. The proposed control method that is based on a variable-damping shock absorber for the landing gear is experimentally validated. Conventionally, the landing gear of lunar and planetary landers...
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| Veröffentlicht in: | Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering Journal of aerospace engineering, 2019-02, Vol.233 (2), p.438-456 |
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| container_title | Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering |
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| creator | Maeda, Takao Otsuki, Masatsugu Hashimoto, Tatsuaki |
| description | This paper describes an attitude control method to prevent the overturning of lunar and planetary landers. The proposed control method that is based on a variable-damping shock absorber for the landing gear is experimentally validated. Conventionally, the landing gear of lunar and planetary landers has a fixed shock attenuation parameter that is not used proactively for attitude control of the lander during the touchdown sequence. The proposed method suppresses any disturbance to the attitude of the lander by adjusting the damping coefficient of each landing leg independently, based on the angular velocity and displacement velocity of each landing leg. First, the control method for the variable damper is presented. Second, the result of a landing experiment conducted in a two-dimensional plane is shown. These results indicate that the proposed semi-active landing gear system is effective for preventing the overturning of the lander on inclined terrain. |
| doi_str_mv | 10.1177/0954410017742931 |
| format | Article |
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The proposed control method that is based on a variable-damping shock absorber for the landing gear is experimentally validated. Conventionally, the landing gear of lunar and planetary landers has a fixed shock attenuation parameter that is not used proactively for attitude control of the lander during the touchdown sequence. The proposed method suppresses any disturbance to the attitude of the lander by adjusting the damping coefficient of each landing leg independently, based on the angular velocity and displacement velocity of each landing leg. First, the control method for the variable damper is presented. Second, the result of a landing experiment conducted in a two-dimensional plane is shown. 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These results indicate that the proposed semi-active landing gear system is effective for preventing the overturning of the lander on inclined terrain.</description><subject>Aircraft accidents & safety</subject><subject>Angular velocity</subject><subject>Attenuation</subject><subject>Attitude control</subject><subject>Damping</subject><subject>Landing gear</subject><subject>Lunar landing</subject><subject>Shock absorbers</subject><subject>Touchdown</subject><issn>0954-4100</issn><issn>2041-3025</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2019</creationdate><recordtype>article</recordtype><recordid>eNp1UE1LxDAQDaLg-nH3GPAczWSSrT3K4hcs6EEvXkpIp6VLTdYkFfz3pq4gCL7LDPPevPlg7AzkBUBVXcraaA1SllyrGmGPLZTUIFAqs88WMy1m_pAdpbSRBWaJC_b6FEMml4fgue3t4FPm4YNinqIffM9Dxy0fJ2-j2I7WU7bxk5ekpcinNCssd8HnGMaR2m9mLvZk4wk76OyY6PQnHrOX25vn1b1YP949rK7XwqHBLFCTcbU0VhJQLVUFXdsB1tgZjbQ0tVKKCpR2YKW9wtoggtJL1erKIeAxO9_5bmN4nyjlZhPK9mVko6AqhsZoVVRyp3IxpBSpa7ZxeCvXNCCb-YPN3w-WFrFrSbanX9N_9V-b0294</recordid><startdate>201902</startdate><enddate>201902</enddate><creator>Maeda, Takao</creator><creator>Otsuki, Masatsugu</creator><creator>Hashimoto, Tatsuaki</creator><general>SAGE Publications</general><general>SAGE PUBLICATIONS, INC</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7TB</scope><scope>8FD</scope><scope>F28</scope><scope>FR3</scope><scope>H8D</scope><scope>L7M</scope></search><sort><creationdate>201902</creationdate><title>Protection against overturning of a lunar-planetary lander using a controlled landing gear</title><author>Maeda, Takao ; Otsuki, Masatsugu ; Hashimoto, Tatsuaki</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c353t-34e5c905a0e1e90271fdf1393f543e659222eeee24c1a0a83953312462d47c313</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2019</creationdate><topic>Aircraft accidents & safety</topic><topic>Angular velocity</topic><topic>Attenuation</topic><topic>Attitude control</topic><topic>Damping</topic><topic>Landing gear</topic><topic>Lunar landing</topic><topic>Shock absorbers</topic><topic>Touchdown</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Maeda, Takao</creatorcontrib><creatorcontrib>Otsuki, Masatsugu</creatorcontrib><creatorcontrib>Hashimoto, Tatsuaki</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>ANTE: Abstracts in New Technology & Engineering</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Proceedings of the Institution of Mechanical Engineers. 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Conventionally, the landing gear of lunar and planetary landers has a fixed shock attenuation parameter that is not used proactively for attitude control of the lander during the touchdown sequence. The proposed method suppresses any disturbance to the attitude of the lander by adjusting the damping coefficient of each landing leg independently, based on the angular velocity and displacement velocity of each landing leg. First, the control method for the variable damper is presented. Second, the result of a landing experiment conducted in a two-dimensional plane is shown. These results indicate that the proposed semi-active landing gear system is effective for preventing the overturning of the lander on inclined terrain.</abstract><cop>London, England</cop><pub>SAGE Publications</pub><doi>10.1177/0954410017742931</doi><tpages>19</tpages></addata></record> |
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| ispartof | Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering, 2019-02, Vol.233 (2), p.438-456 |
| issn | 0954-4100 2041-3025 |
| language | eng |
| recordid | cdi_proquest_journals_2170275542 |
| source | SAGE Complete A-Z List |
| subjects | Aircraft accidents & safety Angular velocity Attenuation Attitude control Damping Landing gear Lunar landing Shock absorbers Touchdown |
| title | Protection against overturning of a lunar-planetary lander using a controlled landing gear |
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