Research on the landing surface ground properties influence on a stability of the space vehicle landing process with a mechanical landing device

Spacecraft and Rockets


Аuthors

Bakulin V. N.1*, Kokushkin V. V.2**, Borzykh S. V., Voronin V. V.***, Shchiblev Y. N.

1. Institute of Applied Mechanics of Russian Academy of Science, IAM RAS, 32a, Leninskii av., Moscow, В-334, GSP-1, 119991, Russia
2. Bauman Moscow State Technical University, MSTU, 5, bldg. 1, 2-nd Baumanskaya str., Moscow, 105005, Russia

*e-mail: vbak@yandex.ru
**e-mail: elenanik7@mail.ru
***e-mail: vitaliyvoronin@gmail.com

Abstract

Stability of one difficult space systems functioning key stages is investigated. This is a process of spacecraft landing on a ground. Essential residual spacecraft kinetic energy dissipates at a direct contact to a landing surface. The vehicle is supplied by a multi-supported landing gear of lever type, because for reusable spacecrafts the requirement of an exception of its body impact with a ground is obligatory. The approach to modeling is based on that the vehicle body and its landing gear elements are considered as a structurally-difficult mechanical system with the intercommunications which character reflects the design features of landing gear support. For each body the displacement equations of the centre mass and the rotation equation about centre mass are recorded. Besides, the special system of the equations for joints reactions definition between bodies consisting system is made. Stability in activity is understood as an overturning absence from the landing gear support of first contact moment to a surface to vehicle full stop. Character of motion is appreciably determined by landing surface properties which should be considered for reusable spacecrafts in a broad band, i.e. from the soft dry sand structures to the heavy frozen ground. The elastic-viscous interaction model of support landing gear scuff plate with a ground based on Voigt hypothesis is developed. The support element is a spherical segment for which ground reaction on a normal to the surface is determined as a function of geometrical segment parameters, depths and speeds of its introduction into a ground and landing surface deformation characteristics. Lateral reaction (at a tangent to the surface) is determined by means of the generalized drag coefficient to horizontal displacement considering the friction forces of steams «scuff plate -ground» and ground displacement along the surface. The parameters rendering influence on a landing stability are revealed. There is a spacecraft angular velocity at the first contact moment to the surface, speed of its centre mass, spacecraft orientation to landing surface, landing surface slope and ground characteristic. The analysis has shown that for stability maintenance the landing case of a soft sand ground is critical. Stability zones for parameters of center mass horizontal speed component and landing surface slope angle for the set of other initial parameters that characterize the normal («regular») landing conditions are constructed. It is shown that initial parameters which can be provided by a spacecraft control system lies in stability areas. Some solutions which can provide landing stability even at determined deviations from regular landing conditions are offered.

Keywords:

space vehicle, dynamics of landing, landing surface, landing device, overloads, stability of motion

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