The aim of this paper is to elaborate a discrete event approach to the development of a methodology for the design of an onboard active system of goal-oriented efficiency support (OASGOES) for a rocket. Materials and methods: OASGOES discrete event models. Results and discussion. A typical model problem is formulated concerning active support of rocket goal-oriented efficiency, which provides for the detection and localization of failures (unforeseen malfunctions) of rocket systems and assemblies. The OASGOES must: (1) detect and localize failures with a required accuracy and as early as possible (before the failures pose major problems for the rocket operation), (2) alter the algorithm of the rocket flight control system, i. e., adapt the algorithm to the rocket operation under failure conditions so that the flight control system may continue to accomplish the control objectives and, as far as possible, provide optimal control, and (3) implement supervisory control by generating an optimal sequence of active control actions that restrict the behavior of the rocket and thus continuously keep it within the admissible state region. The paper discusses possibilities of OASGOES design with the use of discrete event simulation (DES) algorithms, which rely on the notions of observability, diagnosability, and supervisory control in discrete event systems. The proposed approach is illustrated by solving, with the use of methods of the algebraic dioid theory, the model problem of organization of a cyclic inspection of two rocket assemblies taking into account the required synchronous operation of the relevant blocks of the structural health monitoring system. Conclusions. It is expedient to use the discrete event approach in the development of a methodology for OASGOES design. The DES basic advantage is freedom from a detail simulation of the system under consideration.
The goal of this paper is to develop elements of a simulation algorithm for determining the controlled dynamic parameters of the sustainer stages of launch vehicles (LVs) equipped with an active control system (ACS). In this study, methods of system analysis and computational rocket dynamics were used. The paper proposes a system approach to the organization of LV ACS information support with account for specified limiting values of the controlled dynamic parameters: the pitch rate, the velocity pressure, and the angle of attack. In flight, the LV ACS uses information on these parameters to suppress bending deformations of the LV structure and form a trajectory close to the energy-optimal one. The controlled dynamic parameters were brought to a simplified form, thus making it possible to take the data needed for their calculation from the inertial sensors of the LV control system. Simulation algorithm elements were developed to determine the dynamic parameters from the actual values of the center of mass motion parameters in the launch coordinate system, which can be obtained from their calculated values and the corresponding isochronous variations of their apparent values in the inertial coordinate system. The elements of the simulation algorithm for the determination of the LV sustainer stage dynamic parameters may be used in the development of ACS methodological support. The main advantage of the proposed system approach with account for specified limiting values of the controlled dynamic parameters is that it does not require any detailed simulation of dynamic loads on the LV sustainer stages and uses nothing but information on the dynamic parameters that characterize LV trajectory motion conditions.
The aim of this work is to develop a methodological approach to simulating the evolution of a droplet cloud (DC) formed as a result of an explosion of a launch vehicle with self-inflammable propellant components in the initial portion of the flight trajectory and thrown into the atmosphere with initial motion parameters that correspond to the launch vehicle position at the time of the explosion. The proposed approach, which is based on a phenomenological analogy with the motion of a fuel spray injected in the combustion chamber of a diesel, takes into account the fragmentation and tracing of droplets and the effect of their collisions and possible coalescence on the structure and parameters of the propellant component DC, which undergoes a transformation as it moves. The proposed model of the DC evolution, which is due to droplet interaction in the DC and its structuring in the process of motion, reflects the most important, in terms of the environmental consequences of the explosion, processes in the DC and allows one to estimate its basic kinematic and geometric characteristics required for solving the ballistic problem of the motion of the suspended DC droplets in the atmosphere and their precipitation onto the ground surface.
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