The study of the dynamics of the spacecraft landing on a celestial body with microgravity under different fixing conditions

The features of angular motion of the spacecraft when landing on the surface of a small celestial body are studied. Different variants of the spacecraft landing using clamping engines and cable are proposed and the definition of the parameters of the landing system works using a fixing system under different conditions. Optimal conditions are recommended for securing the space lander on the surface of a small celestial body

Use of Modern Digital Software to Model the Motion Dynamics of Spacecraft during Landing

Landing systems for future space missions in Earth and Mars require trustable technologies capable of achieving their aim in the most accurate way possible. For this purpose, systems should go through rigorous dynamic simulations run by precise and efficient software. This study aims to approximately determine the dynamic motion of a landing vehicle using the modern digital software of Universal Mechanism and MATLAB. Universal Mechanism applies the classic mechanics theory on a model based on the geometry of the spacecraft, taking into account the environmental conditions that affect its motion and the properties of the ground to resist its impact [1]. The forces implied in the vehicle phase of descent are also included in MATLAB code to calculate the landing area of the vehicle according to its re-entry velocity [2-4]. Studies were conducted for different initial conditions and approaches to the surface. As a result, the values of the arising overloads and forces acting on the descent vehicle were obtained [1]. The data provided by the simulations conclude the safest landing options that should be taken into account for the success of future missions

Numerical Simulation of the Motion of an Unmanned Aerial Vehicle

Unmanned aerial vehicles are used for research in many areas: photography and video shooting and so on. The development of unmanned aerial vehicles is directly related to the development of airspace. Today, a mathematical model is required that would describe the movement of such an aircraft with the purpose of predicting, correcting and optimizing it. The paper presents the results of a study of the controlled motion of an unmanned multi-rotor aircraft using the example of a quadrocopter. The study included the development of a law governing the apparatus and its modeling in the form of a software package. The structure of the autopilot, its main contours and parameters of these circuits are considered. After determining the necessary characteristics of the autopilot, modeling of the controlled motion of the quadrocopter in the execution environment was carried out

Research of Influence of Small Asymmetries Construction on the Dynamics Motion of Space Landing Vehicle with Considering Resonance

This article provides an analytical methodology rapid assessment of the impact of small asymmetries on motion dynamics of space landing vehicle in a resonant motion. The methodology allows to analyze the value of the design parameters and the aerodynamic coefficients on the degree of their influence through the asymmetry of a deviation from the longitudinal axis of the vehicle velocity vector. The methodology is based on the assumption that the rapid development of resonant modes of motion. An example of the calculations for the proposed method, which showed the adequacy of the results according to the calculations for modeling the spatial movement

Analysis of the reasonableness of the current level of required accuracy of satellite navigation of consumer systems civil mobile means

Analysed the paper presents the analysis of the essential accuracy level expected from the modern fundamental coordinate and time data of both existing and prospective satellite navigation and telecommunication systems, while solving the real-world problems of ballistic and navigational support. The paper shows that the respective analysis of the effect of the navigational coordinate and time data uncertainty should be performed based on the estimates of the required ballistic and navigational support of the satellite systems, taking into account the differences between the theoretically attainable level and the practically feasible level of the accuracy for the fundamental coordinate and time data

Analysis of the reasonableness of the current level of required accuracy of satellite navigation of consumer systems civil mobile means

Analysed the paper presents the analysis of the essential accuracy level expected from the modern fundamental coordinate and time data of both existing and prospective satellite navigation and telecommunication systems, while solving the real-world problems of ballistic and navigational support. The paper shows that the respective analysis of the effect of the navigational coordinate and time data uncertainty should be performed based on the estimates of the required ballistic and navigational support of the satellite systems, taking into account the differences between the theoretically attainable level and the practically feasible level of the accuracy for the fundamental coordinate and time data

Analysis of the reasonableness of the current level of required accuracy of satellite navigation of consumer systems civil mobile means

Analysed the paper presents the analysis of the essential accuracy level expected from the modern fundamental coordinate and time data of both existing and prospective satellite navigation and telecommunication systems, while solving the real-world problems of ballistic and navigational support. The paper shows that the respective analysis of the effect of the navigational coordinate and time data uncertainty should be performed based on the estimates of the required ballistic and navigational support of the satellite systems, taking into account the differences between the theoretically attainable level and the practically feasible level of the accuracy for the fundamental coordinate and time data