Patent ID: 6227494
Filing Date: 2001-05-08
Classification: B64G

Abstract:
A spacecraft, comprising:a space travel vessel; andlanding gear interconnected with said space travel vessel and comprising a first landing leg assembly, wherein said first landing leg assembly comprises:a first leg assembly which comprises first and second ends, wherein said first leg assembly is pivotally interconnected with said space travel vessel at a first location, wherein said first leg assembly further comprises first and second legs which are telescopingly interconnected with each other for an axial extension of said first leg assembly simultaneously with a pivoting of said first leg assembly relative to said space travel vessel about said first location during a deployment of said first landing leg assembly;a second leg assembly which is disposed on a first side of said first leg assembly and which comprises first and second ends, wherein said second leg assembly is pivotally interconnected with said space travel vessel at a second location which is spaced from said first location, wherein said second end of said second leg assembly is pivotally interconnected with said first leg assembly, and wherein said second leg assembly comprises third and fourth legs which are telescopingly interconnected with each other for an axial extension of said second leg assembly simultaneously with a pivoting of said second leg assembly about said second location during said deployment of said first landing leg assembly; anda third leg assembly which is disposed on a second side of said first leg assembly which is opposite said first side and which comprises first and second ends, wherein said first end of said third leg assembly is pivotally interconnected with said space travel vessel at a third location which is spaced from said first location, wherein said second end of said third leg assembly is pivotally interconnected with said first leg assembly, wherein said third leg assembly comprises fifth and sixth legs which are telescopingly interconnected with each other for an axial extension of said third leg assembly simultaneously with a pivoting of said third leg assembly about said third location during said deployment of said first landing leg assembly, wherein said second and third leg assemblies stabilize said first leg assembly, and wherein said landing gear further comprises:means for limiting a relative movement of said first leg assembly relative to said space travel vessel during a first portion of said deployment of said first landing leg assembly to said axial extension of said first leg assembly; andmeans for providing both said axial extension of said first leg assembly relative to said space travel vessel and said pivoting of said first leg assembly relative to said space travel vessel in a second portion of said deployment of said first leg assembly which is after said first portion of said deployment of said first leg assembly.