Rotorcraft autopilot system, components and methods
First Claim
1. An autopilot system for a helicopter, comprising:
- an autopilot display unit that is mounted in an instrument console of the helicopter at least for displaying autopilot flight data to a pilot of the helicopter;
an autopilot main unit enclosure that is removably mounted to the helicopter proximate to a cyclic control of the helicopter and which defines a main unit interior;
a set of actuators supported within the main unit interior including a pitch actuator having a pitch actuator output shaft and a roll actuator having a roll actuator output shaft such that no more than the pitch actuator shaft and the roll actuator shaft of the set of actuators extend at least partially outward from said autopilot main unit enclosure for providing mechanical control forces to the cyclic control of the helicopter; and
a main unit electronics section supported within said main unit interior and in electrical communication with said autopilot display unit and with said set of actuators for providing electrical control signals to the actuators such that the main unit electronics section and the set of actuators are commonly housed within the main unit interior.
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Accused Products
Abstract
An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.
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Citations
12 Claims
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1. An autopilot system for a helicopter, comprising:
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an autopilot display unit that is mounted in an instrument console of the helicopter at least for displaying autopilot flight data to a pilot of the helicopter; an autopilot main unit enclosure that is removably mounted to the helicopter proximate to a cyclic control of the helicopter and which defines a main unit interior; a set of actuators supported within the main unit interior including a pitch actuator having a pitch actuator output shaft and a roll actuator having a roll actuator output shaft such that no more than the pitch actuator shaft and the roll actuator shaft of the set of actuators extend at least partially outward from said autopilot main unit enclosure for providing mechanical control forces to the cyclic control of the helicopter; and a main unit electronics section supported within said main unit interior and in electrical communication with said autopilot display unit and with said set of actuators for providing electrical control signals to the actuators such that the main unit electronics section and the set of actuators are commonly housed within the main unit interior. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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Specification