公开(公告)号：CA1246717A

公开(公告)日：1988-12-13

申请号：CA458431

申请日：1984-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COOPER DEAN E ,  HOWLETT JAMES J

IPC: B64C27/14 ,  B64C27/00 ,  B64C27/12 ,  B64D31/00 ,  B64D31/06 ,  G05D1/08 ,  H02P23/00

Abstract: Rotorcraft Load Factor Enhancer Rotor speed is maintained at a reference speed by a closed-loop fuel control system. Load factor potential is enhanced by increasing the reference speed as a function of the helicopter pitch rate when undergoing positive pitch rate maneuvers.

公开(公告)号：IT1196439B

公开(公告)日：1988-11-16

申请号：IT2100886

申请日：1986-07-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOWLETT JAMES J ,  ALANSKI IRVIN B

IPC: B64C20060101 ,  B64C

Abstract: During the first few seconds after an engine failure, autorotation is established automatically by an Automatic Flight Control System. The system has collective, pitch, roll, and yaw channels and receives engine failure signal, and signals of rotor speed, a rotor speed reference value for autorotation, rotor acceleration, load factor limit for the helicopter, a load factor as measured, pitch rate, airspeed, roll angular acceleration, yaw acceleration, and a yaw reference signal of desired yaw attitude during autorotation. A shaping circuit (21) is responsive to rotor speed (NR), rotor acceleration (NR), and to a pilot-selected desired rotor speed (22) to provide a collective command signal (theta 0) on a line (24), through the switch (14) when armed, to the collective channel of an Automatic Flight Control System (AFCS) (26) for automatically adjusting the collective pitch of the rotor so as to maintain a desirable autorotation rotor speed, such as 100% NR.

公开(公告)号：FR2601326B1

公开(公告)日：1988-10-21

申请号：FR8610219

申请日：1986-07-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOWLETT JAMES J ,  ALANSKY IRVIN B

IPC: B64C27/57 ,  G05D1/00 ,  G05D1/08 ,  B64D31/06 ,  B64C27/12

公开(公告)号：CA1198192A

公开(公告)日：1985-12-17

申请号：CA425723

申请日：1983-04-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MORRISON TERRY ,  HOWLETT JAMES J ,  ZAGRANSKI RAYMOND D

IPC: F02C3/10 ,  F02C9/28 ,  G05D1/00 ,  G05D1/08 ,  F02C9/26

Abstract: Helicopter Cruise Fuel Conserving Engine Control A digital fuel control (53) for a helicopter engine (20) controls fuel flow (52) to the engine in response to a turbine reference speed (62) determined in a normal mode (Fig. 5) to be a rated speed, in a fade-in mode (Fig. 6) to be incremented (117, 120) to an estimated optimum minimum speed (114, 115, 125), in an optimizer mode (Fig. 7) to be incremented (138) in a direction (137) leading to least fuel consumption (135), and in a fade-out mode (Fig. 8) to be incremented (151, 153) back to rated speed (154). The invention provides an engine reference speed which results in minimum fuel consumption during cruise flight.