| 摘要 |
1288290 Measuring pitch, roll and heading SPERRY RAND CORP 9 Dec 1969 [11 Dec 1968] 59929/69 Heading G1N In a system for deriving signals representing roll, pitch and heading of an aircraft, the roll and pitch signals are derived by pick-ups 13, 12 on a vertical gyroscope 11 mounted in the fuselage, a short-term heading signal is derived from a fluxvalve 14 stabilized in a horizontal plane by the gyroscope 11 and a long-term heading signal is derived from a second flux-valve 24 pendulously mounted at the tip of a wing or vertical stabilizer of the aircraft, the compass card 32 being positioned under the influence of both the short- and longterm heading signals. As shown in Fig.1, the output signals from the gyrostabilized flux-valve 14 are fed through a synchro differential 15 to a control transformer 16, the rotor of which is positioned by a high gain fast response servoloop 23. The output of fluxvalve 24 is applied to a control transformer 25 positioned by servoloop 23. Any error signal at the output of the control transformer 25 is removed by positioning synchro differential 15 using a low gain or slow response servoloop 26. As shown in Fig.3, a single servomotor 21 receiving error signals from an algebraic summer 36 positions control transformers 16 and 25. The servomotor 21 reacts to short-term error signals from control transformer 16 and to long-term error signals from control transformer 46. The gain of the long-term loop is about 40 times that of the short-term loop. Undesirable stop-functions in the short-term loop due to switching on or off D.C. equipment near the flux-valve 14 are neutralized by a circuit 51 to 56. The holding circuit need not be perfect, since the long-term loop will correct the errors during the gradual decay of the neutralizing signal. |
