Close-proximity Coulomb formation flying offers attractive prospects in multiple astronautical missions. An analytical method of constructing the series solution up to an arbitrary order for the relative motion near the equilibrium of Coulomb formation systems is proposed to facilitate the design of Coulomb formations based on a Lindstedt-Poincaré method. The details of the series expansion and coefficient solution for Lissajous orbits and arbitrary m : n-period orbits are discussed. To verify the effectiveness of the Lindstedt-Poincaré method in constructing series solutions, the practical convergence domain of series solutions for various bounded orbits is computed by comparison with the corresponding exact numerical solutions. Given the accuracy requirements of practical formation missions, the configuration design for the Coulomb formation can be carried out conveniently and quickly by employing the proposed series solutions.

Close-proximity Coulomb formation flying offers attractive prospects in multiple astronautical missions. An analytical method of constructing the series solution up to an arbitrary order for the relative motion near the equi-librium of Coulomb formation systems is proposed to facilitate the design of Coulomb formations based on a Lindstedt-Poincaré method. The details of the series expansion and coefficient solution for Lissajous orbits and arbitrary m : n-period orbits are discussed. To verify the effectiveness of the Lindstedt-Poincaré method in constructing series solutions, the practical convergence domain of series solutions for various bounded orbits is computed by com-parison with the corresponding exact numerical solutions. Given the accuracy requirements of practical formation missions, the configuration design for the Coulomb formation can be carried out conveniently and quickly by employing the proposed series solutions.

In this paper, experimental and finite element methods are integrated to carry out the research about residual strength of composite laminate structure with central and edge notch. First, the specimens with central and edge notch and the fixtures used in compression tests were designed and manufactured, and the tensile and compression residual strengths with different notch size were measured. Then, finite element analysis model of specimens with central and edge notch were established to predict the residual strength based on the average stress criterion and Hoffman criterion, the effect of the notch size on the residual strength is evaluated, the results were compared and found that the average stress model has higher prediction accuracy and notch size has a significant influence on the residual strength of composite laminate structure with central and edge notch.