2012
DOI: 10.1007/s11431-012-4969-4
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Point return orbit design and characteristics analysis for manned lunar mission

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Cited by 15 publications
(21 citation statements)
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“…Provided a tentative solution is given, the equations of motion and adjoint differential equations are integrated to determine the errors on the boundary conditions. The initial values of the unknown constants that rule the state equations (Δ t 1 , Δ t 2 , Δ v r 1 , Δ v θ 1 ) are easily estimated from their physical meaning; one only needs to ensure that they are within reasonable ranges (Section 6), which can be determined according to the existing literature . Therefore, in this paper, attention is focused on estimating only the initial adjoints, as finding appropriate values is a quite difficult task.…”
Section: Indirect Optimization Methodsmentioning
confidence: 99%
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“…Provided a tentative solution is given, the equations of motion and adjoint differential equations are integrated to determine the errors on the boundary conditions. The initial values of the unknown constants that rule the state equations (Δ t 1 , Δ t 2 , Δ v r 1 , Δ v θ 1 ) are easily estimated from their physical meaning; one only needs to ensure that they are within reasonable ranges (Section 6), which can be determined according to the existing literature . Therefore, in this paper, attention is focused on estimating only the initial adjoints, as finding appropriate values is a quite difficult task.…”
Section: Indirect Optimization Methodsmentioning
confidence: 99%
“…The optimal trajectory with minimal Δ v is depicted in Figure . By referring to the results of and , the ranges for the unknown constants to estimate the initial adjoints are assumed as 0.25hΔitalict10.75h,2.5dayΔitalict24.5day,Δitalicvr1=0,0.8km/sΔitalicvθ11km/sand the procedures usually provide a suitable initial guess for any set of values within these ranges. In the following example, Δ t 1 = 0.5 h, Δ t 2 = 4 day, Δ v r 1 = 0, and Δ v θ 1 = 0.85 km/s are used.…”
Section: Validationmentioning
confidence: 99%
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“…The spacecraft velocity is either free or related to the maximum permitted value of velocity v reentry at the atmosphere boundary r reentry , which is usually set at 122 km above the Earth's surface. () Using the patched‐conic approximation, the hyperbolic excess velocity on entering the Earth's sphere of influence becomes ‖‖bold-italicvf=‖‖vfv()tf=vreentry22normalμrreentry, where μ ⊕ is the gravitational parameter of the Earth. The maximum incoming hyperbolic excess velocity is assumed to be 6 km/s, resulting in entry velocity v reentry around 12.6 km/s, which is slightly smaller than the corresponding limited value used for NASA's Stardust mission…”
Section: Statement Of the Problemmentioning
confidence: 99%
“…The spacecraft velocity is either free or related to the maximum permitted value of velocity v reentry at the atmosphere boundary r reentry , which is usually set at 122 km above the Earth's surface. 23,24 Using the patched-conic approximation, the hyperbolic excess velocity on entering the Earth's sphere of influence becomes…”
Section: Statement Of the Problemmentioning
confidence: 99%