Search Results for “velocity” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Tue, 02 Apr 2024 12:52:26 +0000 en-GB hourly 1 https://wordpress.org/?v=6.2.2 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “velocity” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel https://journal.yuzhnoye.com/content_2019_2-en/annot_9_2_2019-en/ Tue, 03 Oct 2023 11:48:27 +0000 https://journal.yuzhnoye.com/?page_id=27211
Therefore, the study of the distribution of Mach numbers profiles in the working section of the modernized shock wind tunnel at low and high supersonic velocity was chosen as the main line of research. Key words: incident flow modeling , velocity fields in the wind tunnel working section , aerodynamic experiment Bibliography: 1. incident flow modeling , velocity fields in the wind tunnel working section , aerodynamic experiment .
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9. Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

Authors:

Sirenko V. M., Zhivotov O. Yu.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (2); 63-70

DOI: https://doi.org/10.33136/stma2019.02.063

Language: Russian

Annotation: A promising experimental bench – a shock wind tunnel was put into operation at Yuzhnoye SDO. The shock wind tunnel is designed to simulate the incident flow during rocket flight at high supersonic and hypersonic velocities. To solve actual design problems facing Yuzhnoye SDO, it was necessary to expand the range of velocities under investigation in a shock wind tunnel by low supersonic Mach numbers (Mа=1.5; 2; 3). As a result of this work, a modernized configuration of the shock wind tunnel was developed, which allows simulating flow parameters at low supersonic velocities. The results of aerodynamic experiment performed in the modernized shock wind tunnel, which are close to full scale ones, can be obtained using as much data on peculiarities of supersonic flow formation in it as possible. Therefore, the study of the distribution of Mach numbers profiles in the working section of the modernized shock wind tunnel at low and high supersonic velocity was chosen as the main line of research. The results of the research presented in the article are based on the use of numerical simulation methods, as well as data obtained experimentally. As a result of gasdynamic simulation of a supersonic flow conducted for the nozzle Mа=4 and the nozzle Mа=2, the calculated and experimental data on the distribution pattern and field values of Mach numbers in the working section of the tunnel were obtained. A comparative analysis was carried out. The boundaries of the region of equal velocities, within which the condition of quasistatic supersonic flow is satisfied, and the lifetime of the operating mode for the selected nozzle type were determined. At the flow from the nozzle Mа=2, a peculiarity was revealed in the distribution pattern of Mach numbers fields associated with the appearance of “blocking” effect of the supersonic flow. The methods for eliminating the effect of flow “blocking” at low supersonic velocities are proposed.

Key words: incident flow modeling, velocity fields in the wind tunnel working section, aerodynamic experiment

Bibliography:
1. Zvegintsev V. I. Gasodynamicheskie ustanovki kratkovremennogo deistviya. V dvuh chastyakh. Ch. 1. Ustanovki dlya nauchnykh issledovaniy. Novosibirsk, 2014. 551 s.
2. Computerno-vymiryuvalni tekhnologii kontrolu ta upravlinnya raketno-kosmichnoi techniki / monogr. pid zagal. red. prof. V. P. Malaichuka. Dnipro, 2018. 344 s.
3. «Sirius-18». Systema izmereniya i upravleniya impulsnoi aerodynamicheskoi truboi. Rukovodstvo po ekspluatatsii. ELVA4.044.901 RE. 2018. 45 s.
4. Abramovich G.N. Prikladnaya gazovaya dynamika. M., 1978. 888 s.
5. Raschet vnutrennego davlenia v otsekakh RN. YSF YZH UMN 041 01. Rukovodstvo operatora. 2016. 138 s.
6. Issledovania characteristic hyperzvukovoi aerodynamicheskoi truby AT-303. Ch. 1. Polya skorostey / A. M. Kharitonov at al. Teplophysika i aeromekhanika. 2006. T. 13, № 1. S. 1–17.

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9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel
9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel
9.2.2019 Gas-dynamic simulation of the supersonic stream in the pulsed wind tunnel

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]]> 7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation https://journal.yuzhnoye.com/content_2020_1-en/annot_7_1_2020-en/ Wed, 13 Sep 2023 06:27:07 +0000 https://journal.yuzhnoye.com/?page_id=31031
It is shown that as the launch moment becomes closer, the cataloged space situation is ascertained, which leads to the constant change of the quantity of hazardous space debris objects observed in the vicinity of launch vehicle trajectory and to the change of the parameters of their approach to the launch vehicle: minimal relative distance, relative velocity, rendezvous angle and launch moment for which hazardous approach is revealed. In this case, the histograms of distribution of relative distance, relative velocity, and rendezvous angle from catalog to catalog vary insignificantly.
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7. Mechanics of a satellite cluster. Methods for estimating the probability of their maximal approach in flight

Authors:

Holubek O. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2020, (1); 76-84

DOI: https://doi.org/10.33136/stma2020.01.076

Language: Russian

Annotation: The mathematic modeling was performed of the flight of light-class three-stage launch vehicle injecting a payload into sun-synchronous orbit of 700 km altitude and a cluster of observed space debris objects in the conditions of dynamically changing cataloged space situation. It is shown that as the launch moment becomes closer, the cataloged space situation is ascertained, which leads to the constant change of the quantity of hazardous space debris objects observed in the vicinity of launch vehicle trajectory and to the change of the parameters of their approach to the launch vehicle: minimal relative distance, relative velocity, rendezvous angle and launch moment for which hazardous approach is revealed. The hazardous approaches for the launch vehicle trajectory under consideration are more often observed with the relative velocities of more than 8 km/s and rendezvous angles less than 90 deg and their variations within the launch window do not exceed 1.2 m/s and 0.035 deg respectively. In this case, the histograms of distribution of relative distance, relative velocity, and rendezvous angle from catalog to catalog vary insignificantly. The distribution of hazardous approaches in launch time within launch window is not uniform, the regions are observed with low quantity of hazardous approaches and with high quantity. The hazard of launch vehicle collision with observed space debris objects in a launch is confirmed. In all, in the launch day time window under consideration, more than ten hazardous approaches are revealed, for two of them the approach to minimal distance of less than 1 km is predicted. This testifies to the necessity of taking measures to increase safety of launch vehicle flight through observed space debris cluster. In order to increase Ukrainian launch vehicles miss ion safety in the conditions of near space pollution, it is proposed to create the system of pre -flight space analysis, whose tasks are periodic analysis of space situation not less than once in a day, revealing of hazardous approaches, determination of their parameters, and preparation of data to make decision on launch time.

Key words: method of launch time planning, safety of flight through space debris cluster

Bibliography:
1. ESA Operations. For the first time ever, ESA has performed a ‘collision avoidance manoeuvre’ to protect one of its satellites from colliding with a ‘mega constellation’. Electronic resource. – Access mode: https://twitter.com/esaoperations/status/ 1168533241873260544 (Access date 12.09.2019).
2. Klinkrad H. Space Debris – Models and Risk Analysis. Chichester, UK: Praxis Publishing Ltd, 2006. 430 p.
3. Johnson N. L. Orbital Debris: The Growing Threat to Space Operations / Advances in the Astronautical Sciences. 2010. Vol. 137. P. 3-11.
4. Orbital Debris. A Technical Assessment. Washington, D.C.: National Academy Press, 1995. 210 p.
5. Bandyopadhyay P., Sharma R.K., Adimurthy V. Space debris proximity analysis in powered and orbital phases during satellite launch / Advances in Space Research. 2004. Vol. 34. P. 1125-1129. https://doi.org/10.1016/j.asr.2003.10.043
6. Adimurthy V., Ganeshan A. S. Space debris mitigation measures in India / Acta Astronautica. 2005. Vol. 58. P. 168-174. https://doi.org/10.1016/j.actaastro.2005.09.002
7. Schultz E. D., Schultz E. D., Wilde P. D. Mitigation of Collision Hazard for the International Space Station from Globally Launched Objects / 6th IAASS Conference Safety is Not an Option. 21-23 May 2013. Montreal, Canada. Electronic resource. Access mode: https://iaassconference2013.-space-safety.org/ wp-content/uploads/sites/-19/2013/06/ 1420_Shultz.pdf (Access date 12.09.2019).
8. Brevdik G. D., Strub J. E. Determination of acceptable launch windows for satellite collision avoidance / AAS/AIAA Astrodyna-mics Conference. 19-21 August 1991 Pt1. Durango USA. Astrodynamics. P. 345-356.
9. Hejduk M. D., Plakalovic D., New-man L. K., Ollivierre J. C., Hametz M. E., Beaver B. A., Thompson R. C. Trajectory Error and Covariance Realism for Launch Cola Operations / Advances in the Astronautical Sciences. 2013. Vol. 148. P. 2371-2390.
10. Hejduk M. D., Plakalovic D., New-man L. K., Ollivierre J. C., Hametz M. E., Beaver B. A., Thompson R. C. Recommended Risk Assessment Techniques and Thresholds for Launch Cola Operations / Advances in the Astronautical Sciences. 2014. Vol. 150. P. 3061-3080.
11. Handschuh D. A., Wang C., Vidal B. Operational Feedback on Four Years of Collision Risk Avoidance at Launch in Europe / 7th IAASS Conference Space Safety is No Accident, 20-22 October 2014. Fredrichschafen, Germany. P. 355-363. https://doi.org/10.1007/978-3-319-15982-9_42
12. Ihdalov I. М., Kuchma L. D., Poliakov N. V., Sheptun Yu. D. Dinamicheskoe proektirovanie raket. Zadachi dinamiki raket i ikh kosmicheskikh stupenei: mohografiia / pod red. akad. S. N. Koniukhova. Dnepropetrovsk, 2010. 264 s.
13. NIMA TR 8350.2. Department of Defense world geodetic system 1984: Its definition and relationships with local geodetic systems. 3-d ed. National Geospatial-Intelligence Agency, 2000. 174 p.
14. NGA EGM2008 – WGS 84 version. Electronic resource. Access mode to page: http://earth-info.nga.mil/GandG/ wgs84/gravitymod/egm2008/ gm08_wgs84.html. (Access date 12.09.2019).
15. Holubek А. V. Sblizheniie rakety-nositelia s katalogizirovannymi kosmicheskimi ob’ektami v processe vyvedeniia na orbity s nizkim nakloneniem / Izvestiia vysshikh uchebnykh zavadenii. Mashinostroenie. 2018. №2 (695). S. 86-98.

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7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation
7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation
7.1.2020 Studying the motion of a launch vehicle and observed space debris objects during launch preparation

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]]> 21.2.2018 Ensuring Aiming Accuracy of Ship’s Telemetry Reception Antenna Installation for Small Vessels https://journal.yuzhnoye.com/content_2018_2-en/annot_21_2_2018-en/ Thu, 07 Sep 2023 12:30:29 +0000 https://journal.yuzhnoye.com/?page_id=30807
In the article, the connection between kinematic parameters of the antenna rotary support drives and parameters of the space launch vehicle motion were identified, rotation angles of the antenna drives along the three axes were determined, and the law of angular velocity variation along the azimuthal axis, including the maximum feasible angular velocity provided by the azimuthal axis drive, was chosen.
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21. Ensuring Aiming Accuracy of Ship’s Telemetry Reception Antenna Installation for Small Vessels

Authors:

Lyalyuk S. M., Tikhonov V. L.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 178-183

DOI: https://doi.org/10.33136/stma2018.02.178

Language: Russian

Annotation: For monitoring rocket flight and determining accuracy of spacecraft injection into the planned orbit, it is necessary to ensure the reception of telemetry data from the launch vehicle. Telemetry data receiving stations may be located either on land or on shipboard. When the antenna system of such station is placed on shipboard, ship roll and ship drift have the most considerable impact on the antenna guidance accuracy. To ensure the guidance accuracy of the telemetry receiving antenna set, placed on shipboard, the control algorithm was designed. It was offered to use triaxial rotary support with axis of reflector inclination angle to meet the requirements specified. In the article, the connection between kinematic parameters of the antenna rotary support drives and parameters of the space launch vehicle motion were identified, rotation angles of the antenna drives along the three axes were determined, and the law of angular velocity variation along the azimuthal axis, including the maximum feasible angular velocity provided by the azimuthal axis drive, was chosen. Numerical simulation of antenna guidance algorithms that provide stable signal receiving under conditions of ship roll was carried out in the visual development environment of Embarcadero RAD Studio XE6. Several variants for operation of the rotary support drives of the antenna set were chosen for mathematical simulation; disturbing conditions of ship roll and ship drift were analyzed and chosen for ships with small displacement. The simulation validated the designed antenna control algorithm and showed that the requirements for the cinematic parameters of the antenna drives were reduced under conditions of ship roll when the axis of reflector inclination angle was introduced; and accelerometer unit or GPS receiver installed in the antenna structure additionally increased the accuracy of target designation of the antenna and improved its guidance accuracy

Key words: antenna, guidance algorithm, ship roll, ship drift, simulation

Bibliography:
1. Blagoveshchensky S. N., Kholodilin A. N. Guide on Ship’s Statics and Dynamics. Vol. 2. Ship’s Dynamics. L., 1976. 544 p.
2. Sakelari N. Navigation. М., 1936. P. 137.
3. Bezrukov Y. F. Wave Level Variation in the World Ocean. Simferopol, 2001. 50 p.

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21.2.2018 Ensuring Aiming Accuracy of Ship’s Telemetry Reception Antenna Installation for Small Vessels
21.2.2018 Ensuring Aiming Accuracy of Ship’s Telemetry Reception Antenna Installation for Small Vessels
21.2.2018 Ensuring Aiming Accuracy of Ship’s Telemetry Reception Antenna Installation for Small Vessels

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]]> 7.2.2018 Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall https://journal.yuzhnoye.com/content_2018_2-en/annot_7_2_2018-en/ Thu, 07 Sep 2023 11:12:23 +0000 https://journal.yuzhnoye.com/?page_id=30754
It is supposed that in the near-wall layer of the channel, toroidal vortexes (vortex rings) are formed, which move into turbulent core of the flow where their size decreases and the velocity of rotation around the ring axis of torus increases.
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7. Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall

Authors:

Konokh V. I.1, Shevchenko S. A.1, Grigor’ev O. L.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; National Technical University “Kharkiv Polytechnic Institute”, Kharkiv, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2018 (2); 57-67

DOI: https://doi.org/10.33136/stma2018.02.057

Language: Russian

Annotation: During experimental investigation of the dynamic characteristics of a pneumatic test bench for testing liquid rocket engine high-flowrate automatic units, the effect was detected of 20-35% sound speed increase in the gas flow moving along the channel with corrugated wall (metal hose) which is a part of test bench drain system. The article presents the results of experiments and the task of theoretical justification of the effect is solved. It is indicated that its causes may be two mutually complementary factors – a decrease of gas compressibility at eddy motion and oscillations of metal hose wall. The physical model is considered that describes variation of gas elasticity and density in the conditions of high flow vorticity. It is supposed that in the near-wall layer of the channel, toroidal vortexes (vortex rings) are formed, which move into turbulent core of the flow where their size decreases and the velocity of rotation around the ring axis of torus increases. The spiral shape of the corrugation ensures also axial rotation, which increases vortexes stability. The intensive rotation around the ring axis creates considerable centrifugal forces; as a result, the dependence of pressure on gas density and the sound speed increase. The mathematical model has been developed that describes coupled longitudinal-lateral oscillations of gas and channel’s corrugated shell. It is indicated that in the investigated system, two mutually influencing wave types are present – longitudinal, which mainly transfer gas pressure pulses along the channel and lateral ones, which transfer the shell radial deformation pulses. As a result of modeling, it has been ascertained that because of the lateral oscillations of the wall, the propagation rate of gas pressure longitudinal waves (having the same wave length as in the experiments at test bench) turns out to be higher than adiabatic sound speed.

Key words: rocket engine automatic units, pneumatic test bench, metal hose, corrugated shell, toroidal vortex, longitudinal-lateral oscillations

Bibliography:
1. Shevchenko S. A. Experimental Investigation of Dynamic Characteristics of Gas Pressure Regulator in Multiple Ignition LRE Starting System. Problems of Designing and Manufacturing Flying Vehicle Structures: Collection of scientific works. 2015. Issue 4 (84). P. 49-68.
2. Shevchenko S. A., Valivakhin S. A. Results of Mathematical Modeling of Transient Processes in Gas Pressure Regulator. NTU “KhPI” News. 2014. No. 39 (1082). P. 198-206.
3. Shevchenko S. A., Valivakhin S. A. Mathematical Model of Gas Pressure Regulator. NTU “KhPI” News. 2014. No. 38 (1061). P. 195-209.
4. Shevchenko S. A., Konokh V. I., Makoter A. P. Gas Dynamic Resistance and Sound Speed in Channel with Corrugated Wall. NTU “KhPI” News. 2016. No. 20 (1192). P. 94-101.
5. Flexible Metal Hoses. Catalogue. Ufimsky Aggregate Company “Hydraulics”, 2001.
6. Loytsyansky L.G. Liquid and Gas Mechanics. М., 1978. 736 p.
7. Prisnyakov V. F. et al. Determination of Gas Parameters at Vessel Emptying Taking into Account Compressibility and Manifold Resistance. Problems of High-Temperature Engineering: Collection of scientific works. 1981. P. 86-94.
8. Kirillin V. A., Sychyov V. V., Sheydlin A. E. Technical Thermodynamics. М., 2008. 486 p.
9. Grekhov L. V., Ivashchenko N. A., Markov V. A. Propellant Equipment and Control Systems of Diesels. М., 2004. 344 p.
10. Sychyov V. V., Vasserman A. A., Kozlov A. D. et al. Thermodynamic Properties of Air. М., 1978. 276 p.
11. Shariff K., Leonard A. Vortex rings. Annu. Rev. Fluid Mech. 1992. Vol. 24. P. 235-279. https://doi.org/10.1146/annurev.fl.24.010192.001315
12. Saffman F. Vortex Dynamics. М., 2000. 376 p.
13. Akhmetov D. G. Formation and Basic Parameters of Vortex Rings. Applied Mechanics and Theoretical Physics. 2001. Vol. 42, No 5. P. 70–83.
14. Shevchenko S. A., Grigor’yev A. L., Stepanov M. S. Refinement of Invariant Method for Calculation of Gas Dynamic Parameters in Rocket Engine Starting Pneumatic System Pipelines. NTU “KhPI” News. 2015. No. 6 (1115). P. 156-181.

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7.2.2018 Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall
7.2.2018 Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall
7.2.2018 Theoretical Models of Sound Speed Increase Effects in Gas Duct with Corrugated Wall

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]]> 6.1.2018 On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction https://journal.yuzhnoye.com/content_2018_1-en/annot_6_1_2018-en/ Tue, 05 Sep 2023 06:19:12 +0000 https://journal.yuzhnoye.com/?page_id=30454
On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction Authors: Degtyareva O. 2018 (1); 31-38 DOI: https://doi.org/10.33136/stma2018.01.031 Language: Russian Annotation: The paper deals with the options of solving the task of constructing an inertial navigation system in the conditions of considerable g-load and angular velocity in identified direction by method of setting the sensitive elements at some angle to the identified direction, which allows making measurements in it without loss of measurement quality in the other directions. (2018) "On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction" Космическая техника. "On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction" Космическая техника.
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6. On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction

Authors:

Degtyareva O. А., Lapko O. M., Meleshko A. O., Chucha Y. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (1); 31-38

DOI: https://doi.org/10.33136/stma2018.01.031

Language: Russian

Annotation: The paper deals with the options of solving the task of constructing an inertial navigation system in the conditions of considerable g-load and angular velocity in identified direction by method of setting the sensitive elements at some angle to the identified direction, which allows making measurements in it without loss of measurement quality in the other directions. The paper describes the technique of calculating the angle of sensitive elements setting to the identified direction. The scheme of constructing an inertial navigation system with incomplete set of sensitive elements is considered for the cases when in entire operation leg, rotation around the identified direction is executed. The analysis is given of measurement vector error due to incompleteness of the sensitive elements set.

Key words:

Bibliography:
1. Shunkov V. N. Encyclopedia of Rocket Artillery / Under the general editorship of A. E. Taras. Minsk, 2004. 544 p.
2. Shirokorad A. B. Encyclopedia of National Artillery / Under the general editorship of A. E. Taras. Minsk: Harvest, 2000. 1156 p.
3. Pugachyov V. S. et al. Rocket Control System and Flight Dynamics / V. S. Pugachyov, I. E. Kazakov, D. I. Gladkov, L. G. Yevlanov, A. F. Mishakov, V. D. Sedov. М., 1965. 610 p.
4. Branets V. N., Shmyglevsky I. P. Use of Quaternions in Solid Body Orientation Problems. М., 1973. 320 p.
5. Borisova A. Y., Smal’ A. V. Analysis of Developments of Gimballess Inertial Navigation Systems. Engineering News. N. E. Bauman MGTU. No. 05. 2017.

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6.1.2018 On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction
6.1.2018 On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction
6.1.2018 On Building of Inertial Navigation System in the Condition of Presence of Considerable g-Load and Angular Velocity in Preferential Direction
]]> 21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft https://journal.yuzhnoye.com/content_2017_2/annot_21_2_2017-en/ Wed, 09 Aug 2023 12:32:56 +0000 https://journal.yuzhnoye.com/?page_id=29940
Improving Metallic Thermal-Protection-System Hypervelocity Impact Resistance Through Numerical Simulation.
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21. Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft

Authors:

Husarova I. O.1, Potapov O. М.1, Shevtsov E. I.1, Onofriienko V. I.1, Husev V. V.1, Manko Т. А.2

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine1; Oles Honchar Dnipro National University, Dnipro, Ukraine2

Page: Kosm. teh. Raket. vooruž. 2017 (2); 121-126

Language: Russian

Annotation: The paper considers the TZS-U design developed by Yuzhnoye SDO specialists for windward part of reusable spacecraft with external metal three-layer panel, U-like joint and tiled thermal protection, in which the problem is solved of compensation of thermal expansions and sealing of gaps; for optimization of structural mass. The specially created dispersion-hardened powder alloy based on nichrome and aluminum with yttrium dioxide with decreased specific mass of 7500 kg/m3 and lighter felt of MKRF brand are used , and honeycomb filler of three-layer panel is replaced by the filler with square cell.

Key words:

Bibliography:
1. Aerothermal performance and structural integrity of a René-41 thermal protection system at Mach 6.6 / W. D. Deveikis, R. Miserentino, I. Weinstein, J. L. Schideler. NASA-TN-D-7943, NASA, Washington DC. 1975. 105 р.
2. Poteet C. C., Blosser M. L. Improving Metallic Thermal-Protection-System Hypervelocity Impact Resistance Through Numerical Simulation. Journal of Spacecraft and Rockets. 2004. Vol. 41, No. 2. Р. 221-232.
3. Advanced metallic thermal protection system development / M. L. Blosser, R. R. Chen, I. H. Schmidt et al. AIAA-2002-0504; AIAA, Washington DC. 2002. 56 р.
4. David E. European Directions for Hypersonic Thermal Protection Systems and Hot Structures. 31st Annual Conference on Composite Materials and Structures (Daytona Beach, FL, January 22, 2007). 44 р.
5. Gusarova I. A. Selection of Scheme of Heat Protection Tile Attachment to Reusable Spacecraft Body. Problems of Designing and Manufacturing Flying Vehicle Structures. 2016. No. 4 (88). P. 105-113.
6. Gusarova I. A. Evaluation of Thermal Resistance of Three-Layer Honeycomb Panel Produced from YuIPM-1200 Alloy by Method of Diffusion Welding in Vacuum / I. A. Gusarova, М. Parko, А. М. Potapov, Y. V. Fal’chenko, L. V. Petrushinets, Т. V. Melnichenko, V. E. Fedorchuk. Automatic Welding. 2016. No. 12 (759). P. 31-35.
7. Patent 108096 Ukraine. Method of Producing Heat-Resistant Alloy Based on Nichrome / V. V. Skorokhod, V. P. Solntsev, G. O. Frolov, Т. O. Solntseva, О. М. Potapov, V. G. Tikhiy, I. A. Gusarova, Y. M. Litvinenko / Application No. а2012 11691; Claimed 04.10.2012; Published 25.03.2015, Bulletin No. 6. 4 p.

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21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft
21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft
21.2.2017 Mass Parameter Optimization of Thermal Protective Structure for Reusable Spacecraft
]]> 2.1.2019 Flying Vehicle Maneuvering Dynamics in Atmosphere with Weight Asymmetry and Elements of Terminal Control in Turn Leg https://journal.yuzhnoye.com/content_2019_1-en/annot_2_1_2019-en/ Thu, 25 May 2023 12:09:03 +0000 https://journal.yuzhnoye.com/?page_id=27707
In the absence of disturbances, the angular motion of the aircraft shows in part signs of regular precession (almost constant precession velocity and nutation angle) and autorotation (close to zero self-rotation angle). Composition of disturbances includes the spread of the aircraft technical characteristics (position of the center of mass, moments of inertia, aerodynamic coefficients, velocity head, etc.),
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2. Flying Vehicle Maneuvering Dynamics in Atmosphere with Weight Asymmetry and Elements of Terminal Control in Turn Leg

Authors:

Levin O. S., Mashtak I. V., Sheptun A. D.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 4-14

DOI: https://doi.org/10.33136/stma2019.01.004

Language: Russian

Annotation: This paper suggests method for analysis of the dynamics of the aircraft with weight asymmetry (transverse displacement of the center of mass) maneuvering in the atmosphere under the impact of the short-time alternating moment of engine thrust, spread out over a period. The engines are installed on the bottom of the aircraft at the maximum distance from its longitudinal axis. Angular motion with nominal and perturbed performances of the aircraft and flight conditions has been consistently considered. Before maneuvering, the aircraft is set at the trimming angle of attack, determined by the magnitude of transverse displacement of the center of mass and aerodynamic characteristics. The direction of the aircraft maneuvering in the atmosphere depends on the acting moments of forces and time diversity of the engine firings to speed up and shutdown the angular motion. In the absence of disturbances, the angular motion of the aircraft shows in part signs of regular precession (almost constant precession velocity and nutation angle) and autorotation (close to zero self-rotation angle). Under the influence of disturbances, the spread of the aircraft angular motion parameters increases, mainly at the angle of precession, which characterizes changes in the direction of maneuvering. Composition of disturbances includes the spread of the aircraft technical characteristics (position of the center of mass, moments of inertia, aerodynamic coefficients, velocity head, etc.), errors associated with the operation of the engines (thrust spread, time of ignition and shutdown, angular alignment of their longitudinal axes). Terminal control was introduced to realize the given final state and to reduce the disturbances impact on the maneuvering parameters based on the registered deviations of the angular motion from the nominal one after the first shutdown of the attitude maneuver engine. Monte Carlo method (1000 variations of random realizations of the acting perturbations) confirmed the effectiveness of the proposed terminal control of the angular motion of the aircraft to provide the specified maneuvering parameters.

Key words: angular motion, angles of precession, nutation (attack), proper rotation, spread of technical characteristics of the aircraft

Bibliography:

1. Lebedev A. A., Gerasuta N. F. Ballistika raket. M.: Mashinostroenie, 1970. 244 p.
2. Buchgolz N. N. Osnovnoy kurs teoreticheskoi mechaniki. Ch. 2. M.: Nauka, 1972. 332 p.
3. Aslanov V. S. Prostranstvennoe dvizhenie tela pri spuske v atmosfere. M.: Fizmatlit, 2004. 160 p.
4. Gukov V. V., Kirilinko P. P., Mareev Y. A., Samarskiy A. M., Chernov V. V. Osnovy teorii poleta letatelnykh apparatov. M.: MAI, 1978. 70 p.
5.Teoretychni osnovy poletu kosmichnykh apparativ. Ministerstvo oborony Ukrainy, 2000. 180 p.

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2.1.2019 Flying Vehicle Maneuvering Dynamics in Atmosphere with Weight Asymmetry and Elements of Terminal Control in Turn Leg
2.1.2019 Flying Vehicle Maneuvering Dynamics in Atmosphere with Weight Asymmetry and Elements of Terminal Control in Turn Leg
2.1.2019 Flying Vehicle Maneuvering Dynamics in Atmosphere with Weight Asymmetry and Elements of Terminal Control in Turn Leg

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]]> 22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification https://journal.yuzhnoye.com/content_2019_1-en/annot_22_1_2019-en/ Wed, 24 May 2023 16:00:54 +0000 https://journal.yuzhnoye.com/?page_id=27727
The offered methodology for uncertainty calculation is applicable to centrifugal machines, for which numerical values of reproducible linear acceleration are determined by results of calculations of the centrifugal machine’s rotor angular velocity and radial distance from rotor’s longitudinal axis to the given point of the tested unit. Initial data used were results of observation obtained after multiple reproductions of the given values of linear acceleration as well as numerical values of errors and measurement uncertainties of measuring equipment that was used when monitoring the rotary angular velocity and radial distance considering the contribution of each measurable parameter to a certain value of linear acceleration.
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22. Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification

Authors:

Bondar’ М. А., Voloshina M. O., Yeres L. O., Kurako I. М., Morozov O. D.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 149-153

DOI: https://doi.org/10.33136/stma2019.01.149

Language: Russian

Annotation: Applicable documents on metrological assurance regulate the estimation of measurement uncertainty. In Ukraine there is no regulative methodology for uncertainty calculation when certificating test equipment that causes the necessity of its definition. This article offers the methodology for uncertainty calculation when certificating a centrifugal machine that is used to reproduce precisely the given value of linear acceleration that permanently acts on a tested unit spinning together with a rotor. The offered methodology for uncertainty calculation is applicable to centrifugal machines, for which numerical values of reproducible linear acceleration are determined by results of calculations of the centrifugal machine’s rotor angular velocity and radial distance from rotor’s longitudinal axis to the given point of the tested unit. Initial data used were results of observation obtained after multiple reproductions of the given values of linear acceleration as well as numerical values of errors and measurement uncertainties of measuring equipment that was used when monitoring the rotary angular velocity and radial distance considering the contribution of each measurable parameter to a certain value of linear acceleration. The calculation given in the article estimates the limit of linear accelerations that can be attributed with established probability to the given value of linear acceleration reproduced when certificating the centrifugal machine. The design formulae are given to estimate the uncertainty components of the reproducible values of linear accelerations and the recommendations are given to present the uncertainty budget.

Key words: extended uncertainty, standard uncertainty, sensitivity coefficient, measurement uncertainty contribution, frequency meter

Bibliography:
1. GOST 24555. Poryadok attestatsii ispytatelnogo oborudovania. Osnovnye polozheniya. Vved. 27.01.81. M.: Gosstandart, 1982. 12 p.
2. https://www.twirpx.com/file/1791976.
3. Guide to the Expression of Uncertainty in Measurement: ISO. Geneva, 1993. 101 p.
4. Zakon Ukrainy «Pro metrologiu ta metrologychnu diyalnist’»// Vidom. Verkhovnoi Rady (VVR). 2014. № 30. P.1008.
5. Duplischeva O. M. i dr. Experimentalnaya otrabotka agregatov avtomatiki I system letatelnykh apparatov/ Pod obsch. red. d. t. n. A. V. Degtyareva. Dnepropetrovsk: GP KB «Yuzhnoye» im. M. K. Yangelya», 2013. 208 p.
6. Bondar’ M. A. i dr. Metodologia otsenivania neopredelennosti izmerenniy pri provedenii attestatsii sredstv izmeritelnoi techniki//Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch. – techn. st. 2017. Vyp. 1. P. 3–7.

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22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification
22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification
22.1.2019 Calculation of Uncertainty of Represented Values of Linear Accelerations during Centrifugal Machines Certification

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]]> 21.1.2019 Optimization of Geometrical Shape of Isolation Valve Blading Position https://journal.yuzhnoye.com/content_2019_1-en/annot_21_1_2019-en/ Wed, 24 May 2023 16:00:50 +0000 https://journal.yuzhnoye.com/?page_id=27726
2019, (1); 144-148 DOI: https://doi.org/10.33136/stma2019.01.144 Language: Russian Annotation: One of the main design parameters of the automatic equipment in the launch vehicle’s pneumohydraulic systems is the flow friction characteristic, which represents the proportionality factor between the automatic equipment pressure differential and velocity head.
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21. Optimization of Geometrical Shape of Isolation Valve Blading Position

Authors:

Veskov E. V., Nazarenko O. P., Rabotilov V. S.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 144-148

DOI: https://doi.org/10.33136/stma2019.01.144

Language: Russian

Annotation: One of the main design parameters of the automatic equipment in the launch vehicle’s pneumohydraulic systems is the flow friction characteristic, which represents the proportionality factor between the automatic equipment pressure differential and velocity head. The flow friction characteristic of the completely open automatic device should have very small value with required dimensions and mass. With decrease of the pressure losses, the required upstream pressure of the propulsion system is ensured with smaller pressurization of the tanks. It results in the decrease of the required pressurization gas volume, which boosts reduction of the performance of the launch vehicle as a whole. This paper describes the method of reduction of the flow friction characteristic of the dividing valve, optimizing the geometric shape of the flow passage. The problem of minimization of the valve’s flow friction characteristic is considered with the specified mass and design dimensions restrictions. The initial design of the valve was developed, taking into account the specified requirements, literature references and parameters of the analogue units. With the goal of optimization various options of valve design were considered, different from the initial design in configuration of the inlet and discharge nozzles, notably various angle sizes, forming the stream profile, and lengths of the direct-flow sections. Four options of the valve design were calculated using numerical methods of ANSYS CFX software. Navier – Stokes equations and k-ω SST turbulence model were used. Based on the calculations results the optimal design was selected. Initial design of the valve was compared with the optimal one. The flow friction characteristic of the optimal valve design decreased by 26 % in comparison with initial design with insignificant change of mass and dimensions. The design of the developed dividing valve can be involved in the design of the new launch vehicles.

Key words: automation devices, valve, launch vehicle, design optimization, ANSYS CFX

Bibliography:
1. Gurevich D. F. Raschet i konstruirovanie truboprovodnoi armatury: Raschet truboprovodnoi armatuty. 5-e izd. M.: Izd-vo LKI, 2008. 480 p.
2. Yanshin B. I. Hydrodynamicheskie characteristiki zatvorov i elementov truboprovodov. M.: Mashinostroenie, 1965. 259 p.
3. Idelchik I. Ye. Spravochnik po hydrovlicheskim soprotivleniyam / Pod red. M. O. Steinberga. 3-e izd., pererab. i dop. M.: Mashinostroenie, 1992. 672 p.
4. Ansys CFX Solver Theory Guide [Electronniy resurs] / ANSYS Inc., 2012. Rezhim dostupa: http://www1.ansys.com/customer/content/ documentation/180/cfx_thry.pdf.

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21.1.2019 Optimization of Geometrical Shape of Isolation Valve Blading Position
21.1.2019 Optimization of Geometrical Shape of Isolation Valve Blading Position
21.1.2019 Optimization of Geometrical Shape of Isolation Valve Blading Position

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]]> 17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type https://journal.yuzhnoye.com/content_2019_1-en/annot_17_1_2019-en/ Wed, 24 May 2023 16:00:35 +0000 https://journal.yuzhnoye.com/?page_id=27722
Testing SRE with pyroxiline powder grain showed that the optimum design of the engine can be developed only with the application of the specially developed design procedure of the gas-dynamic flow pattern of powder gases in the engine chamber with definition of field of pressure and velocity.
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17. Development of Prospective Small-Size Auxiliary SMR of New Type

Authors:

Toloch’yants G. E., Mikhailov M. S., Magdin E. K., Oglikh V. V.

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2019, (1); 114-121

DOI: https://doi.org/10.33136/stma2019.01.114

Language: Russian

Annotation: This article considers essentially new versions of small-sized solid propellant rocket engines (SRE), designed for rocket and spacecraft flight control with serial artillery pyroxiline powder taken as grain and solidpropellant gas generators discretely operating into the receiver. Preliminary results of design and experimental activities, performed in Yuzhnoye SDO, showed the possibility in principle and practicability to develop two new types of advanced small-sized SRE. Testing SRE with pyroxiline powder grain showed that the optimum design of the engine can be developed only with the application of the specially developed design procedure of the gas-dynamic flow pattern of powder gases in the engine chamber with definition of field of pressure and velocity. Such procedure has been developed based on Ansys software package. The article describes areas of further design and experimental activities, fulfilment of which will provide development of production models of the described engines. Intraballistic characteristics design procedure, mentioned in the article, can be used to design new type of micropulse SRE with less than 0.1 s burn time. This article will also facilitate definition of the application area for discrete solid-propellant propulsion systems, where they get the edge over the cold gas gas-jet systems.

Key words: procedure, microSRE, gas-jet system, heat-transfer factor

Bibliography:

1. Kovalenko N. D., Kukushkin V. I. Triumph I tragediya systemy upravleniya vektorom tyagi dvigatelya ZD65 vduvom kamernogo gaza v soplo// Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2014. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 97-106.
2. Oglykh V. V., Vakhromov V. A., Kirichenko A. S., Kosenko M. G. Razrabotka porokhovykh accumulyatorov davlenia dlya minometnogo starta raket – vazhneishee uslovie ego uspeshnoy realizatsii / Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauch.-techn. st. 2016. Vyp. 1. Dnepropetrovsk: GP KB «Yuzhnoye». P. 88-92.
3. Golubev K. S., Svetlov V. G. Proektirovanie zenitnykh upravlyaemykh raket. M.: Izd-vo MAH, 2001. 730 p.
4. Oglykh V. V., Tolochyants G. E., Mikhailov N. S., PopkovV. N. Eksperimentalnye issledovania vozmozhnosti sozdania impulsnogo RDTT s malym vremenem raboty/ Kosmicheskaya technika. Raketnoe vooruzhenie: Sb. nauchn.-techn. st. 2016. Vyp. 2. Dnepr: GP KB «Yuzhnoye». P. 30-34.
5. Belyaev N. M., Belik N. P., Uvarov Ye. I. Reaktyvnye systemy upravleniya kosmicheskykh letatelnykh apparatov. M.: Mashinostroenie, 1979. 232 p.
6. Gubertov A. M., Mironov V. V., Borisov D. M. Gazodynamicheskie i teplophysicheskie process v raketnykh dvigatelyakh na tverdom toplive. M.: Mashinostroenie, 2004.
7. Kutateladze S. S. Teploperedacha i hydrodynamicheskoe soprotivlenie. Energoatomizdat, 1990. 368 p.
8. Scherbakov M. A. Opredelenie coeffitsientov teplootdachi pri modelirovanii zadach v Ansys CFX // Dvigateli i energoustanovki aerokosmicheskykh letatelnykh apparatov: Sb. nauch. statey. M.: Nauch.- techn. Centr im. A. Lyulki, 2014.
9. Moskvichev A. V. Primenimost’ modeley turbulentnosti, realizovannykh v Ansys CFX dlya issledovaniya gasodynamiki v schelevom kanale TNA ZhRD. Voronezhskiy gosudarstvenniy technicheskiy universitet, 2015.
10. Magdin E. K., Oglykh V. V., Rozlivan A. B. Tverdotoplivnaya dvigatelnaya ustanovka orientatsii I stabilizatsii descretnogo deistviya dlya upravleniya kosmicheskimi obiektami / Vestn. dvigatelestroiteley. 2017. Vyp. 2. P. 108-111.

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17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type
17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type
17.1.2019 Development of Prospective Small-Size Auxiliary SMR of New Type

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