FIELD: control systems of flight vehicles, in particular, guided missiles. SUBSTANCE: the design is based on registration of actuator operation in response to zero, direct and harmonic input and output signals. The output signal is subjected to a harmonic analysis concerning the direct component, amplitude and phase shift of the first harmonic of expansion into a Fourier series. Measured are the free-running frequency and amplitude from the feedback transmitter output in the absence of an input signal to the actuator and compared with the rated ones. Then the signal from the feedback transmitter is passed via a ripple filter, whose time constant is selected from the condition of effective suppression of the free-running frequency at a minimum sluggishness of the filter. The control actuator zero drift and static gain are judged by the value of the filter output voltage; and the value of phase shift - by the value of shift of the filter output signal relative to the input one. EFFECT: objective control and enhanced accuracy, reduced labour input and cost of control. 3 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SELF-OSCILLATING CONTROL ACTUATOR OF SPIN-STABILIZED GUIDED MISSILE | 2000 |
|
RU2184926C2 |
| SELF-SUSTAINED CONTROL ACTUATOR OF GUIDED MISSILE | 1997 |
|
RU2114387C1 |
| SELF-EXCITED ACTUATOR OF GUIDED MISSILE ROTATING IN ROLL | 2003 |
|
RU2236669C1 |
| SELF-OSCILLATING CONTROL ACTUATOR OF ROLL-STABILIZED GUIDED MISSILE | 2005 |
|
RU2288441C1 |
| SELF-OSCILLATORY AUTOMATIC PILOT OF GUIDED MISSILE | 1993 |
|
RU2081446C1 |
| GUIDED MISSILE SELF-SUSTAINED AUTOPILOT | 1996 |
|
RU2115086C1 |
| INTERRUPTED PNEUMATIC ACTUATOR OF CONTROL SYSTEM OF SPIN-STABILIZED MISSILES AND METHOD FOR MONITORING OF ITS DYNAMICS | 2000 |
|
RU2184340C2 |
| SELF-SUSTAINED AUTOPILOT OF GUIDED MISSILE | 1992 |
|
RU2092784C1 |
| SELF-OSCILLATING AUTOMATIC PILOT OF GUIDED MISSILE | 1997 |
|
RU2117324C1 |
| METHOD AND DEVICE FOR CONTROL OF ELECTROPNEUMATIC ACTUATOR | 1997 |
|
RU2138767C1 |
