Carbon-carbon composite materials (CCCM) are characterized by high heat resistance and thermostability for which they, in most of their physical and mechanical characteristics, can be attributed to the most promising materials. Approximately 81% of all carbon-carbon composite materials are used for the manufacture of brake rotors for aircraft, 18% – in space rocket technology, and only 1% – for all other areas of application. This study discusses calculations of the strength, rigidity, and stability of a frame made of carbon-carbon composite materials. It is known that the strength of CCCM based on high-strength carbon fibers is higher than the strength of a composite material based on high-modulus carbon fibers obtained at various processing temperatures. The stress-strain behaviour (SSB) of the material is carried out. Among the special properties of CCCM are low porosity, low coefficient of thermal expansion, maintaining a stable structure and properties, as well as product dimensions.
Carbon-carbon composite materials (CCCM) are a new class of structural materials designed to create light, durable, and space-based rigid structures for aerospace, hypersonic, gas turbine engines, parts of nozzle blocks, rocket combustion chambers, and transition trusses. They have the unique ability to maintain high strength and stiffness with 2500°C. For the manufacture of thermally stressed parts of nozzles, carbon fiber fabrics are used. Antioxidant coatings based on tantalum and silicon are applied to nozzles with adhesive (made based on tantalum carbide, which provides high mechanical strength of adhesion of erosion-resistant antioxidant coating with CCCM), antioxidant and erosion-resistant layers. To deposit a layer of tantalum carbide on CCCM, we used the technology of vacuum ion-plasma deposition of tantalum film followed by carbonization with carbon. As a result, an adhesive coating of tantalum carbide is formed on the surface of the packing. Obtaining an erosion-resistant antioxidant coating on the adhesion layer of tantalum carbide is obtained by applying a slip of silicon carbide powders and soot. The study of the performance of antioxidant and erosionresistant protective coating in high-temperature airflow was carried out on plasmatron (it is a plasma generator in which an electric current is used to form a plasma; for cooling it, channels washed by water are used). This article shows that the studied packings have a unique ability to maintain high strength and rigidity with 2500°C. There is the expediency of manufacturing such nozzles. The physical and mechanical characteristics of the material were determined.
Carbon-carbon composite materials are characterized by high heat resistance and thermostability for which they, in most of their physical and mechanical characteristics, can be attributed to the most promising materials. Approximately 81% of all carbon-carbon composite materials are used for the manufacture of brake rotors for aircraft, 18% – in space rocket technology, and only 1% – for all other areas of application. While the need for composites for rocket and space technology is constantly decreasing – the volume of production of brake disc rotors for aircraft is steadily growing, and therefore research on the properties of carbon-carbon composite materials (CCCM) under conditions of high-intensity thermal loading is extremely urgent at the moment. In this paper, we consider a method for introducing silicates and oxides hardening them with the addition of refractory, chemical elements into CCCM. Tests of tips from CCCM were carried out under conditions of high-intensity thermo-force loading. The objectives of the experiment were to obtain scalded forms of the tip model and to record the temperature on the surface during the action of a jet flowing out of the nozzle of the propulsion system (PS). The tip of the CCCM is blown by means of a propulsion system with a supersonic flow of a highly enthalpy oxygencontaining gas. The results of experimental studies were determined using video recording on the basis of which sequences of frames were obtained on the basis of which the burning forms were built. Using thermal imaging measurements, the temperature field on the model surface was determined during the entire time the supersonic gas flow was exposed to it.
One of the significant innovative technologies is the creation of large-sized structures that work for a long time in space and meet stringent restrictions on overall mass characteristics. Among these structures, in the first place, is the section of bearing truss (BT). This article presents the results of experimental studies of sectors of load-bearing trusses of mesh design for compression. Recently, composite mesh cylindrical shells are used as spacecraft housings. The mesh shell is a supporting structure to which the instruments and mechanisms of the spacecraft are attached. The truss section is made of cross-linked polymer composite material with carbon fibers. The objective of the tests is to confirm the possibility of creating a lightweight mesh construction using a carbon fiber reinforced polymer composite material. To achieve this goal, the authors were assigned the following tasks: selection of carbon filler of polymer composite materials (PCM); selection of PCM binder; determination of the degree of carbon fiber reinforcement; choice of the number and orientation paths of spiral ribs, number of ring ribs and the sizes of individual ribs. As a result of the research, the calculated indicators for ensuring the bearing capacity and stiffness under the application of axial compressive load were obtained. At the same time, with the determination of bearing capacity, the deformation characteristics of the structure were twice determined in order to confirm their repeatability, as well as linear nature of the dependence of axial and radial deformations as a result of the applied load.
This study covers the issues of the security system in civil aviation. The relevance of the topic is conditioned by a qualitatively new approach to the design of civil aviation, since the modern equipment has the means intended for rescue directly in the area of contact of an emergency aircraft with the ground. When hitting the ground, as a rule, the lower part of the airframe is crushed, the fuselages break in the centre wing section, and the interior equipment breaking off is very traumatic to passengers, the engines are extremely fire and explosion dangerous, which leads to an emergency situation developing into a catastrophic one. The purpose of the study is to investigate the existing security system of a civil aircraft and develop the modification of aviation equipment with the help of collective rescue systems. Two main areas of application of collective rescue systems in aviation technology are analysed. As a solution to the problem at hand, a modification in the form of a parachute system of collective rescue is proposed. A detailed description of the system operation with the use of the necessary calculations for weight, aerodynamic and similar costs is given. The system under study relates to aviation technology and can be used in the development of transport (passenger, cargo, business class, etc.) aircraft. The proposed modification would significantly increase the level of flight safety due to a preventive measure that would exclude the contact area of the emergency aircraft with the ground.
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