In practice, a spacecraft’s stabilization system, which is partially invariant to the disturbing moment, is the easiest to implement. The velocity performance limitation of the control actuator has the most influence upon stability of the system among all the nonlinearities considered in the mathematical modelling. Therefore, we shall consider a model of an invariant stabilization system with due regard to nonlinearity. For the system under consideration, it is possible to construct lines of equal values of the auto oscillation amplitude in a two-parameter plane. The study of the stability of the proposed partially invariant stabilization system revealed that it is possible to ensure sufficient stability margins in the system under consideration by choosing parameters for the stabilization controller. At the same time, it allows to provide high quality of the transition process.
-The publication suggests how to significantly improve the spacecraft center of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for high navigation accuracy, when rigid trajectory control method is used.
In this article have been proposed the design objectives for an integrated guidance system of a
commercial launch vehicle with application of GPS technologies and has been set a technical problem of the
conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial
Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system
based on GPS technology involves determination of its structure, models and algorithms, providing the
required accuracy and reliability in injecting payloads with due regard to restrictions on weight and
dimensions of the system.
A method for improving the spacecraft center of mass movement stabilization accuracy in the active phases of trajectory correction is proposed. This method is used during interplanetary and transfer flights, which in some cases provides high navigational accuracy, when rigid trajectory control methods are used. The required stability conditions obtained are consistent with the known criteria in the invariant theory. Computer modeling shows that a partially invariant stabilization system exhibits significant advantages in terms of accuracy when compared to known stabilization systems.
This paper introduces a 1U CubeSat based on 3D printing technology. Compared to the traditional large satellites, CubeSat has advantages such as low cost and short development cycle, so more and more CubeSat has been applied to space exploration missions in recent years. The design process of the CubeSat includes the determination of main parameters, the design of external and internal layout, and the structural main features. To professionalize the engineering work of CubeSat design, the concept of design process is proposed, and the structure and parameter optimization (SPO) about basic parameters and feature compatibility are found. The design problem is solved gradually by the structure and parameter optimization (SPO), and the value range of the selected parameters is determined. In this paper, a CubeSat prototype manufactured using 3D printing technology, having this several advantages including fast implementation, accuracy in manufacturing small parts and low cost, the combination of CubeSat and 3D printing technology will maximize the rapid development of CubeSat. In the space exploration field, the number of 3D printed plastic CubeSat is very small, and this paper is aimed to test the ability of the plastic CubeSat to complete space exploration missions in space. In this paper, the 3D printing technology and traditional manufacturing technology are discussed, and the feasible structure design model is obtained by combining the material and parameter design.
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