40 research outputs found
Sterowanie i korekcja platformy giroskopowej umieszczonej na pok艂adzie obiektu lataj膮cego
The work is concerned with the optimal control and correction of a three-axis gyroscopic platform fixed on board of a flying object. The deviations from the predetermined motion are minimized by means of a method of programmed control, an algorithm of the optimal correction control, and selection of optimal parameters for the gyroscopic platform.W pracy przedstawione jest sterowanie optymalne i korekcja trzyosiowej platformy giroskopowej, umieszczonej na pok艂adzie obiektu lataj膮cego. Odchylenia od ruchu zadanego s膮 minimalizowane za pomoc膮 sterowania programowego, algorytmu optymalnego sterowania korekcyjnego oraz wyboru optymalnych parametr贸w platformy giroskopowej
A process of gyroscope motion control in an autonomus system of target detection and tracking
A control algoritm of a three-degree-of-freedom gyroscope axis motion emerging from a solution to the inverse problem of dynamic is presented in the paper. A complete system of non-linear differential equations represents the motion of axis of a gimballed gyroscope (i.e. mounted in the Cardan joint), including both the inertial parameters of all elements and resisting forces acting in joint bearings. The effects of the following factors : initial conditions choice, disturbances, as well as non-linearity, on precision of gyro-axis required motion realisation is presented. Optimal parameters of the control algoritm correcting the gyro-axis motion are determined, as well.W pracy przedstawiono wyniki sterowania ruchem osi giroskopu o trzech stopniach swobody, kt贸rego program sterowania jest wyznaczany za pomoc膮 tzw. metod odwrotnych dynamiki. Ruch osi giroskopu, zawieszonego na przegubie Cardana, zosta艂 opisany pe艂nym uk艂adem nieliniowych r贸wna艅 r贸偶niczkowych z uwzgl臋dnieniem bezw艂adno艣ci wszystkich element贸w giroskopu oraz si艂 oporu w 艂o偶yskach przegubu. Pokazano wp艂yw warunk贸w pocz膮tkowych, zak艂贸ce艅 oraz nieliniowo艣ci na dok艂adno艣膰 realizacji ruchu programowego osi giroskopu. Wyznaczono parametry optymalne sterowa艅 stabilizuj膮cych ruch osi giroskopu
The Algorithm of Optimal Control of the Anti-Aircraft Launcher on Board a Ship
W artykule przedstawiony jest algorytm optymalnego sterowania wyrzutni膮 przeciwlotniczych pocisk贸w rakietowych umieszczon膮 na poruszaj膮cym si臋 okr臋cie. Model matematyczny ruchu wyrzutni jest linearyzowany, a nast臋pnie, wykorzystuj膮c macierze stanu i sterowania, wyznaczane jest sterowanie optymalne ze wzgl臋du na minimum funkcjona艂u 艣redniokwadratowego. Wyznaczone w ten spos贸b sterowanie dzia艂aj膮c na wyrzutni臋, zapewnia minimalizacj臋 uchybu mi臋dzy ruchem zadanym a rzeczywistym oraz podczas procesu poszukiwania i 艣ledzenia celu powietrznego w warunkach oddzia艂ywania zak艂贸ce艅 zewn臋trznych ze strony okr臋tu.The paper presents the algorithm of optimal control of the anti-aircraft launcher mounted on board a moving ship. The mathematical model of the launcher motion is linearised, and then, using the matrix of state and control, the optimal control is determined on account of the minimum functional mean-square. This way of determining control which affects the launcher, ensures minimization of the deviation between the applied and actual motion while searching and tracing the aerial target under the condition of external disturbances generated by the ship
Non-Linear Model of Anti-Aircraft Missile Launcher Mounted on Board of a Ship
W pracy przedstawione s膮 elementy sformu艂owanego modelu wyrzutni przeciwlotniczych pocisk贸w rakietowych umieszczonej na pok艂adzie okr臋tu. Ruch zestawu rozpatrywany jest w tr贸jwymiarowej przestrzeni Euklidesa i w jednorodnym polu grawitacyjnym. Rozwa偶ane s膮 drgania o du偶ych warto艣ciach przemieszcze艅 uog贸lnionych poszczeg贸lnych obiekt贸w. Opracowany model okr臋towej wyrzutni rakietowej w og贸lnym przypadku ma trzyna艣cie stopni swobody.The paper presents elements of a model of the anti-aircraft missile launcher mounted on board of a ship. The assembly motion is examined in the three-dimensional Euclidean space and in the homogenous gravitational field. Vibrations with high values of generalized dislocations of particular objects are discussed. The elaborated model of the ship's missile launcher has thirteen degrees of freedom in the general case
The impact of launcher turret vibrations control on the rocket launch
The paper discusses the missile lift-off from a launcher placed on a motor vehicle. The stimulation of the assembly vibration results from the input generated by the road and the missile firing. The unfavourable input generated in the course of assembly operation has an impact on the characteristics of the initial missile flight parameters. The aim of the paper is to apply the hybrid vibroisolation system of the launcher turret in order to improve the conditions of the missile launch from the assembly. The active system reducing the occurring disturbance allows to control the launcher turret vibrations. Owing to that it is possible influence effectively the initial missile flight parameters
Giroskopowy uk艂ad lokalizacji punktowego 藕r贸d艂a promieniowania elektromagnetycznego ma艂ej cz臋stotliwo艣ci
The work discusses a new concept of locating the angular position of an electromagnetic radiation source. It presents a mathematical model and calculations concerning the process of target location. The considerations include the guidance of aerial vehicles onto targets of this type.W opracowaniu przedstawiono koncepcj臋, model matematyczny oraz szacunkowe obliczenia dotycz膮ce lokalizacji po艂o偶enia k膮towego punktowych urz膮dze艅 elektroenergetycznych. Rozpatrywana jest tak偶e mo偶liwo艣膰 naprowadzania obiektu lataj膮cego na tego rodzaju urz膮dzeni
Numerical analysis of dynamics of an automatically tracked anti-tank guided missile using polynomial functions
The paper presents algorithms of automatic control of an intelligent anti-tank guided missile
(ATGM) with possibility of attacking the target from the upper ceiling and with possibility
of the missile flight through indicated points in space. The polynomial functions are used to
designate the program trajectories. Numerical analysis of the operation of chosen algorithms
is performed. The results are presented in a graphical form. As it results from the conducted
tests, the proposed algorithms of automatic control of ATGM with the use of polynomial
functions work properly during attack on the target from the upper ceiling, for both mobile
and immobile targets
Selected algorithms of automatic guidance for armor-piercing rocket attacking a target from a ceiling
W pracy zaprezentowano dwa algorytmy automatycznego naprowadzania pocisku rakietowego (ppk), atakuj膮cego cel z g贸rnego pu艂apu. Pierwszy algorytm kieruje lotem ppk tak, aby wektor pr臋dko艣ci ppk w chwili zderzenia z celem by艂 skierowany prostopadle w d贸艂. Drugi zak艂ada przelot ppk tu偶 nad celem w czasie ataku. Uproszczony model matematyczny ppk oraz r贸wnania toru lotu pos艂u偶y艂y do przeprowadzenia symulacji komputerowej ataku celu z g贸rnego pu艂apu. Wyniki bada艅 symulacji komputerowej przedstawiono w postaci graficznej.The paper presents two algorithms of automatic guidance of an armor-piercing rocket (apr) attacking a target from a ceiling. The first algorithm direct flight amr so that the velocity vector of amr in the moment of impact with the target was directed perpendicularly downwards. The second assumes amr flight just above the target during the attack. A simplified mathematical model amr and trajectory flight equations were used to carry out computer simulation of attack of target from the ceiling. The results of computer simulation are presented in graphical form
Automatic control of an anti-tank guided missile based on polynomial functions
The paper presents algorithms of automatic control of an intelligent anti-tank guided missile
with the possibility of attacking a target from the upper ceiling (top attack). Polynomial
functions have been used to determine program trajectories. The numerical analysis of chosen
algorithms has been performed. The results of work are presented in a graphical form. It
appears from the conducted research that the proposed algorithms of automatic control
of the anti-tank guided missile work correctly during attack from the upper ceiling, both
movable and fixed
Dynamics and Control of Gyroscopic System of Bomb Guidance on a Ground Target
W artykule przedstawiony jest algorytm naprowadzania bomby kierowanej na cel naziemny z wykorzystaniem uk艂adu giroskopowego. Rozpatrzone s膮 r贸偶ne przypadki realizacji toru programowego po艂膮czonego z samonaprowadzaniem w ko艅cowym odcinku lotu. Przytoczone s膮 niekt贸re wyniki symulacji komputerowej.The paper presents an algorithm of guiding the bomb on a ground target using the gyro system. There are considered different cases of the execution of flight path program combined with bomb homing in the final stretch of the flight. There are also quoted some of the results of computer simulation