Siberian Aerospace Journal

The implementation of the internet of things technologies in the rocket-space industry requires increased security measures for information and communication processes. Existing intrusion detection systems are unable to take into account the heterogeneity of the network structure and the scale of information circulating between devices. To solve this problem, intrusion detection systems use an anomaly method, which requires a large number of representative data sets. The authors have reviewed public datasets that can be used to build an anomaly detection system. They contain information from artificial simulation medium or isolated environments with simulated devices, include examples that are not directly related to the internet of things, and do not take into account the dynamic nature of traffic changes.

In this paper, we present a new infrastructure that will avoid these drawbacks. It collects data on the functioning of a real Internet of Things network and allows testing its stability to typical attacks. We use the MQTT (message queuing telemetry transport) application protocol and software platforms that support information interaction based on the publisher-subscriber pattern. The infrastructure contains devices that monitor technological rooms with telecommunications equipment, brokers with various security policy settings, applications for data control and analysis, software agents for collecting network traffic and threat simulators that perform attacks on network nodes from single sources or in a distributed environment. Researchers will be able to use the data collected in the infrastructure for cybersecurity analysis to create reliable IoT-based solutions needed to implement this technology in knowledge-intensive space systems production.

The results of the development of a scheduler for the joint execution of simulation models of multicomponent systems are presented. The software is implemented in Python, which allows integration with numerous libraries for control and data analysis. Data exchange is carried out via UDP packets that support different programming languages. This simplifies the implementation of hardware-in-the-loop technology, improving the development of control systems. An example of using the scheduler is demonstrated on the model of the attitude determination and condtrol system of a CubeSat spacecraft with a magnetic orientation system. The B-Dot algorithm and the results of simulating the transient process are provided. The source code is available under the BSD license on GitFlic, and the documentation is available on ReadTheDocs.

In this work, a novel method for self-tuning genetic programming (GP) algorithms is presented, based on the ideas of the Success History based Parameter Adaptation (SHA) method, originally developed for the Differential Evolution (DE) algorithm. The main idea of the method is to perform a dynamic analysis of the history of successful solutions to adapt the algorithm's parameters during the search process. To implement this concept, the operation scheme of classical GP was modified to mimic the DE scheme, allowing the integration of the success history mechanism into GP. The resulting algorithm, denoted as SHAGP (Success-History based Adaptive Genetic Programming), demonstrates new capabilities for parameter adaptation, such as the adjustment of crossover and mutation probabilities. The work also includes a detailed review of existing self-tuning methods for GP algorithms, which allowed for the identification of their key advantages and limitations and the application of this knowledge in the development of SHAGP. Additionally, new crossover operators are proposed that enable dynamic adjustment of the crossover probability, account for the selective pressure at the current stage, and implement a multi-parent approach. This modification allows for more flexible control over the process of genotype recombination, thereby enhancing the algorithm's adaptability to the problem at hand. To adjust the probabilities of applying various operators (selection, crossover, mutation), self-configuring evolutionary algorithm methods are employed, in particular, the Self-Configuring Evolutionary Algorithm and the Population-Level Dynamic Probabilities Evolutionary Algorithm. Within the framework of this work, two variants of the algorithm were implemented – SelfCSHAGP and PDPSHAGP. The efficiency of the proposed algorithms was tested on problem sets from the Feynman Symbolic Regression Database. Each algorithm was run multiple times on each problem to obtain a reliable statistical sample, and the results were compared using the Mann–Whitney statistical test. The experimental data showed that the proposed algorithms achieve a higher reliability metric compared to existing GP self-tuning methods, with the PDPSHAGP method demonstrating the best efficiency in more than 90 % of the cases. Such a universal self-tuning mechanism can find applications in a wide range of fields, such as automated machine learning, big data processing, engineering design, and medicine, as well as in space applications – for example, in the design of navigation systems for spacecraft and the development of control systems for aerial vehicles. In these areas, the high reliability of algorithms and their ability to find optimal solutions in complex multidimensional spaces are critically important.

The aim of the work is the calculation and experimental substantiation of the expediency of using (both on Earth and on the surface of other planets) active-reactive type penetrator projectiles (SPART) for solving a number of scientific problems related to the formation of wells in the ground and the delivery of payloads to a certain depth. Research methods: various launch schemes (options for organizing the functioning process) of SPART are considered. The depth of penetration of an active-reactive type penetrator projectile into loam is calculated for the case when SPART is fired from a ballistic launcher located in such a way that the projectile exit velocity is equal to the velocity of its entry into the ground, and the thrust of the propulsion system is twice as great as the static resistance of the soil. From a variety of options, three SPART design schemes are selected depending on the combustion rate of the fuel used to ensure normal operation of the engine. As a result of the conducted calculation and experimental studies to determine the depth of penetration into loam of 152.4 mm penetrator projectiles 4.6 m long, launched from an artillery mount using the same powder charge weighing 18 kg, it was found that from the moment the engine is turned off until it comes to a complete stop, ${\mathrm{L}}_{\mathrm{full}}^{\mathrm{ps}}=205,48\mathrm{m}$, which is more than twice the penetration depth of the same penetrator projectile if it moved in the soil only by inertia. Conclusion: the results presented in the article can be useful for researchers, graduate students and engineers involved in the creation and operation of aviation and rocket and space technology, and can also be useful for students of technical universities studying in the relevant specialties.

Power elements of structures in the form of structural anisogrid shells of rotation are often used in the production of rocket and space technology. This is due, first of all, to high specific mechanical properties of composites, which allow to manufacture structures with a high degree of weight perfection. In addition, they are quite technological, as the method of continuous winding of composite fibers used in their production is widespread and well developed. In recent years, close attention has been paid to the design of composite mesh structures.

An actual example of anisogrid cylindrical and conical shells is a spacecraft adapter for GLONASS satellites orbit launching, different variants of which are still produced in the workshops of Reshetnev JSC. The shells are of the same type, but differ in dimensions (diameters and lengths of cylindrical and conical parts) and bearing capacity. For composite elements of rocket-space technology it is characterized by the presence of a large list of variable parameters, the determination of the optimal combination of which every time results in a complex problem of scientific search.

An algorithm and a program for building a finite element model of anisogrid conical shells made by continuous winding of composite fiber have been developed. The small base is fixed and the large base is reinforced by a spandrel and loaded by concentrated forces and moments. Numerical investigation of stability, stiffness and stress-strain state of the structure under varying parameters of its mesh structure formation is carried out with the help of FE model.

In this article, a comparative analysis of two methods of increasing the pressure in the zone of subsidence of the energy characteristics of a low-speed axial pump is carried out: the installation of an inlet guide vanes (IGV) and an upper-rotor device with axial grooves (J-Grooves). Axial pumps are widely used in power systems for liquid rocket engines, as well as in aircraft hydraulic power systems. Modern aircraft engines are capable of deep throttling, which puts forward important requirements for high-speed pumps. One of these requirements is multi-mode – the ability to work in a wide range of costs and operating speeds. The relevance of the work is due to the fact that the pressure characteristics of axial pumps in the vast majority of cases have non-monotonic curves, which complicates the process of their design and regulation. Increasing the head in the area of falling productivity and striving for a monotonically falling pressure characteristic of the axial pump is one of the most important goals in the design of the unit.

In this work, the energy characteristics of an axial pump with an inlet vane device installed in the form of guide vanes (IGV), which create a preliminary twist of the flow at the peripheral sections in the inlet line and an optimal upper-rotor device (J-Grooves) in the form of axial ducts, were obtained by numerical computer modeling. Their influence on the energy characteristics of the object of study and the magnitude of reverse currents is shown, and a comparison is made with the research results of foreign and domestic authors.

The article contains the results of research on the effect of abrasive flow machining on the roughness and microhardness of the surface of small channels (holes) in samples of workpieces made of 12X18N10T steel. Empirical dependences of the change in roughness and microhardness of the surface of a small channel on the degree of filling of the working medium with a plasticizer and the shear pressure of the hydraulic system with the extrema of these functions in the studied area are obtained. Based on these dependencies, the composition of the working environment was selected: the degree of filling of the working media base (with a constant content of white electro corundum – 30 %) with a plasticizer in the form of diamond paste (ASN 60/40 VOM G) Ka 40 % and SKT rubber 30 %, respectively. As a result of abrasive flow machining, it was possible to reduce the roughness of the surface layer from Ra = 0.49…0.62 µm to Ra = 0.047…0.06 µm, and also to increase the microhardness of the surface from h = 188…192 HB to h = 213…220 HB. The thickness of the hardened layer is ≈ 7.24 µm. Analysis of surface profilograms shows that as a result of abrasive flow machining, both the height roughness parameters (average – Ra, Rz, Rp; maximum – Rmax) and the depth roughness parameters (Rk) were significantly reduced. Using electron microscopy (SEM MAG), a qualitative assessment of the structure of the surface layer of the small channel was carried out. The obtained results show good machinability by abrasive flow of austenitic steel blanks, in particular 12X18N10T steel.