| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an attitude control device capable of controlling the attitude at the landing of a flight vehicle. <P>SOLUTION: The attitude control device 90 includes at least two or more protrusions 4 extending from a bottom 31 of a body 3 of the flight vehicle 2 toward a lower side. The protrusions 4 receive an input of load inclined to a vertical direction of the body 3. Namely, when the flight vehicle 2 lands while being inclined, one protrusion 4 of the protrusions 4 first collides therewith to correct the attitude of the flight vehicle 2 while being compressed and deformed into high rigidity, thus controlling the attitude of the flight vehicle 2. <P>COPYRIGHT: (C)2012,JPO&INPIT |
