METHOD FOR TEST RIG DEVELOPMENT OF LASER BEAM-CONTROLLED ROCKETS, MICRORANGE AND TEST RIG FOR ITS REALIZATION

FIELD: tests. ^ SUBSTANCE: the rocket is installed on a test rig, the countdown graph is started, the power of the control signal is changed in proportion with the distance of the rocket to the target, and the external actions on the rocket in a real flight are simulated. The operation of the rocket...

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Bibliographische Detailangaben
Hauptverfasser:	KUZNETSOV VLADIMIR MARKOVICH, LIKHTEROV VLADIMIR MOISEEVICH, IVANOV SERGEJ NIKOLAEVICH, KOLOTILIN VLADIMIR IVANOVICH, ZAVAL'NJUK ANATOLIJ GAVRILOVICH
Format:	Patent
Sprache:	eng ; rus
Schlagworte:	ADVERTISING AIMING APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND,DEAF OR MUTE BLASTING BULLET CATCHERS CRYPTOGRAPHY DIAGRAMS DISPLAY EDUCATION EDUCATIONAL OR DEMONSTRATION APPLIANCES GLOBES HEATING LIGHTING MECHANICAL ENGINEERING PHYSICS PLANETARIA SEALS TARGET RANGES TARGETS WEAPON SIGHTS WEAPONS
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Beschreibung
Zusammenfassung:	FIELD: tests. ^ SUBSTANCE: the rocket is installed on a test rig, the countdown graph is started, the power of the control signal is changed in proportion with the distance of the rocket to the target, and the external actions on the rocket in a real flight are simulated. The operation of the rocket control system and the parameters of the external actions are monitored, the serviceability of the system is determined according to the response of the rocket control system to the checked external actions. The microrange includes a test route, rocket and a test rig for development of the rocket. A guidance instrument is installed on the test route, a device for varying the control signal power in proportion with the distance to the rocket is installed between the guidance instrument and the rocket, and the rocket is positioned on the rig simulating the external actions on the rocket. The device for varying the control signal power is made in the form of optical filters of various penetrability or reflecting surfaces of various curvature that are installed on the shaft of the rotation drive. The rig has a device for installation of the rocket, base and a system for measurements and recording of the rocket parameters. The device for installation of the rocket is made in the form of a gas turbine, whose rotor is fastened on the rocket, and the stator is coupled to the base through a hinge providing for turning of the rotor in the horizontal plane, and an additional rotation assembly installed at a distance from the turbine. The fixed yoke of the additional rotation assembly is coupled through a hinge to the rod of a pendulum, whose axle is installed on the vertical guide of the base. The system for measurement and recording in addition has transducers of rocket attitude, spinning and rocket bank position electrically coupled to the recording system. ^ EFFECT: provided test rig development of laser beam-controlled rockets in the conditions simulating the real flight, the material for the analysis and repeated use being preserved. ^ 6 cl, 4 dwg