FIELD: defense equipment; guides projectiles and missiles.
SUBSTANCE: actuator with open control surfaces is placed on mounting table and voltage Usup is fed to feedback potentiometer, control surfaces are turned through maximum angle to one side (+ max) and to other side (- max) by applying torque of respective sign equal to torque developed by actuator; angles of turn of control surfaces + max and - max are measured by means of protractor on side of loaded control surface; simultaneously, voltages U+
EFFECT: increased informative capacity; improved quality of estimation of gain factor; enhanced reliability and accuracy; reduced labor consumption; low cost.
3 cl, 11 dwg, 1 tbl
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METHOD FOR DETERMINATION OF AERODYNAMIC CHARACTERISTICS OF GUIDED MISSILE IN FLIGHT, METHOD FOR DETERMINATION OF ANGLE OF ATTACK OF MISSILE IN FLIGHT, METHOD FOR DETERMINATION OF MISSILE ATTITUDE AND DEVICES FOR THEIR REALIZATION | 2002 |
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RU2218550C2 |
INTERRUPTED PNEUMATIC ACTUATOR OF CONTROL SYSTEM OF SPIN-STABILIZED MISSILES AND METHOD FOR MONITORING OF ITS DYNAMICS | 2000 |
|
RU2184340C2 |
ELECTROPNEUMATIC MISSILE CONTROL ACTUATOR | 2001 |
|
RU2218549C2 |
SELF-OSCILLATING CONTROL ACTUATOR OF SPIN-STABILIZED GUIDED MISSILE | 2000 |
|
RU2184926C2 |
METHOD FOR CONTROL OF MISSILE CONTROL ACTUATOR ELECTRO-PNEUMATIC DRIVE AND DEVICE FOR ITS REALIZATION | 2001 |
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RU2206861C2 |
TWO-CHANNEL AIR-DYNAMIC UNIT OF GUIDED MISSILE CONTROL ACTUATOR | 2002 |
|
RU2224214C2 |
Authors
Dates
2004-09-20—Published
2002-07-15—Filed