Helicopter control device

• US 4,134,560 A
• Filed: 09/19/1977
• Issued: 01/16/1979
• Est. Priority Date: 09/19/1977
• Status: Expired due to Term

• Current Assignee: Eugene D. Messerschmidt
• Original Assignee: Eugene D. Messerschmidt
• Inventors: Messerschmidt, Eugene D.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US05/834,233
• Time in Patent Office: 484 Days
• Field of Search: 244/17.11, 244/17.2 S, 244/83 R, 244/83 F, 244/83 B, 244/83 C, 244/17.13, 244/83 J, 74/471 R, 74/471 XY, 74/491
• US Class Current: 244/234
• CPC Class Codes: B64C 27/58 Transmitting means, e.g. interrelated with initiating means or means acting on blades means acting on blades B64C27/72
• CPC Class Codes: Y10T 74/20201 Control moves in two planes

Abstract

A helicopter control system for controlling cyclic pitch, collective pitch, throttle and rudder. A handle is secured to a vertical shaft slidable or telescopic within a cylindrical tube. A locking device permits the tube and shaft to be moved as a unit to control cyclic pitch. Vertical movement of the shaft controls collective pitch. Rotation of the shaft controls the tail rotor. A twist-grip on the handle is provided for throttle control. The handle may be adjusted through a ball joint for pilot comfort.

Claims

1. In a control system for a helicopter having:

(i) a collective pitch control mechanism for changing the pitch angle of the rotor blades;

(ii) a throttle control;

(iii) a tail rotor control for changing the pitch of the tail rotor blades; and

(iv) a cyclic pitch control mechanism for changing the tilt of the rotor disc;

an improved control comprising;

(a) a first control means pivotally mounted for pivotal movement in at least two directions, said first control means being operatively connected to said cyclic pitch control;

(b) second control means moveable relative to said first control means and operatively connected to said collective pitch control mechanism; and

(c) locking means for selectively engaging or disengaging said first and second control means whereby said first and second control means can be locked in unitary engagement and said first and second control means moved in one pivotal direction to change the cyclic pitch in the longitudinal axis and moved in the other pivotal direction to change the cyclic pitch in the lateral helicopter axis and whereby said first and second levers can be disengaged and said second control means can be moved relative to said first control means to control collective pitch and rotated to operate the tail rotor control.

2. The control system of claim 1 further including means associated with said second control means for adjusting said throttle.

3. The control system of claim 1 wherein said first control means comprises a hollow tube and said second control means comprises a shaft slidably disposed within said tube.

4. The control system of claim 3 wherein said shaft includes a horizontal handle portion.

5. The control system of claim 4 including means for selectively adjusting the position of said handle portion.