 Power factor correction system |
| Briefly, a power factor correction (PFC) system in accordance with the present invention is coupled ... |
|
| Concentric ring antenna |
| To overcome the limitations of the prior art, a method and apparatus is provided to permit exciting ... |
|
| Doppler frequency impulse radar system with displaced pulse sequence |
| I claim: 1. A doppler frequency impulse radar system, comprising a transmitting circuit for ... |
|
| Method of screening infra-red radiation |
| I claim: 1. A method of screening infra-red radiation which comprises forming between the source of ... |
|
| Electrical noise detector for detecting power line gap defects |
| In accordance with the present invention, a device for identifying a defect in power line equipment ... |
|
| Test bench for wideband radio link |
| What we claim is: 1. A radio link test bench system, comprising: (1) transmission station means, ... |
|
| Apparatus for accomplishing autoport selection |
| It is, therefore, an object of the present invention to reduce the need for technicians to make ... |
|
| Refuse compacting and transporting system |
| Referring to the drawings in detail, wherein like numerals designate like parts, a refuse ... |
|
| Humane animal trap |
| What I claim is: 1. An animal trap comprising a casing, said casing including opposed upper and ... |
|
|
Servo control system for a co-axial rotary winged aircraft
| Details |
Inventors: Cycon, James P.; Schneider, George S.; Tenerowicz, Gregory P.;
Assignee: United Technologies Corporation (Hartford, CT)
Primary Examiner: Peters, Jr.; Joseph F.
Assistant Examiner: Ellis; Christopher P.
Attorney, Agent or Firm:
A servo control system for a radio controlled co-axial rotor helicopter includes a receiver 4 to provide signals indicative of operator desired pitch, yaw, roll, and collective commands to an electronic mixer unit 30 which translates these command signals into six control signals 34-42 utilized by servos 50-60 to properly displace the rotor blades 256, 258. |
|
DETAILED DESCRIPTION We claim: 1.
A servo control system for a co-axial rotary winged aircraft having an upper and lower rotor comprising: command means for providing electronic command signals indicative of operator control commands in the pitch, yaw, roll, and collective axes of the aircraft; electronic mixing means for providing at least three upper, and three lower, rotor electrical servo control signals in response to said command signals; a plurality of upper swash plate servo means for controlling the pitch of the upper rotor blades of the aircraft in response to said upper rotor electrical servo control signals; and a plurality of lower swash plate servo means for controlling the pitch of the lower rotor blades of the aircraft in response to said lower rotor electrical servo control signals.
2.
The servo control system for a co-axial rotary winged aircraft according to claim 1, wherein said servo means are mounted a distance from the rotors on the same order of magnitude as the distance required to permit necessary attitude orientation of the swash plates.
3.
The servo control system for a co-axial rotary winged aircraft according to claim 1, wherein said command means comprises: transmitter means for providing transmitted electronic signals indicative of operator control commands; and receiver means for receiving said transmitted electronic signals and providing received electronic signals indicative of said transmitted signals.
4.
The servo control system for a co-axial rotary winged aircraft according to claim 1, wherein said command means comprises a flight control computer.
5.
The servo control system for a co-axial rotary winged aircraft according to claim 1, further comprising: flight parameter means for providing electronic flight parameter signals indicative of the dynamic flight parameters of the aircraft; differential rotor control means responsive to said flight parameter signals for providing electronic differential rotor control signals; and wherein said electronic mixing means is further responsive to said differential rotor control signals
|
|
Telecommunications 
