EP0317577A1 - MANCHE de commande copilote a embrayage rapide - Google Patents

MANCHE de commande copilote a embrayage rapide

Info

Publication number
EP0317577A1
EP0317577A1 EP87907687A EP87907687A EP0317577A1 EP 0317577 A1 EP0317577 A1 EP 0317577A1 EP 87907687 A EP87907687 A EP 87907687A EP 87907687 A EP87907687 A EP 87907687A EP 0317577 A1 EP0317577 A1 EP 0317577A1
Authority
EP
European Patent Office
Prior art keywords
control stick
stud
housing
pivot
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP87907687A
Other languages
German (de)
English (en)
Other versions
EP0317577A4 (fr
Inventor
Andrew Smith
Frank Wolstencroft
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Bell Helicopter Textron Inc
Original Assignee
Bell Helicopter Textron Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Bell Helicopter Textron Inc filed Critical Bell Helicopter Textron Inc
Publication of EP0317577A1 publication Critical patent/EP0317577A1/fr
Publication of EP0317577A4 publication Critical patent/EP0317577A4/fr
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
    • B64C13/02—Initiating means
    • B64C13/04—Initiating means actuated personally
    • B64C13/12—Dual control apparatus

Definitions

  • This invention relates to aircraft flight control systems and, in particular, to a disengageable copilot control stick that can be reconnected quickly without jamming.
  • the copilot's control column or stick is linked to the pilot's control stick so that both controls move together in a parallel manner.
  • the dual controls are designed to allow either the pilot or the copilot to have full control over the aircraft at all times during flight.
  • copilot control sticks In some aircraft having dual controls, such as helicopters and military aircraft, it may be advantageous to disengage the copilot's control stick from the pilot's controls during certain phases of the flight. For example, when the copilot is not actively piloting the aircraft, the copilot may be occupied with other tasks, such as navigation, radar operation, and computer system operation. While the copilot is performing these other tasks, inadvertent jolts or pressures on the copilot's control stick can cause undesirable and possibly unsafe inputs to the aircraft flight controls. Because this problem can affect flight safety, copilot control sticks have been designed to be disengageable from the aircraft flight control system.
  • Disengageable copilot -control sticks which are designed for convenience and safety, can become a safety hazard if they are slow or difficult to reengage, or if it is possible for them to become jammed while being reconnected with the aircraft flight control system.
  • any malfunction of the stick-throttle interconnect i.e. the pilot
  • Disengageable copilot control sticks currently available have not been totally satisfactory because they are difficult and/or slow to reengage and because they can become jammed during reconnection if the copilot attempts to apply any force to the stick before it is fully connected.
  • Some disengageable copilot sticks utilize a ball or stud which is spring-loaded into a socket at the bottom of a bowl or inverse-conical shaped receptacle. These sticks are disengaged by overcoming the spring force to remove the ball or stud from the socket in the bottom of the bowl. Reconnection of these control sticks is accomplished by allowing the spring to urge the ball or stud down the sloping sides of the bowl and into the socket. However, reconnection cannot be accomplished if the copilot applies a force to the copilot's control stick counter to the force applied through the pilot's stick. Furthermore, the bowl- shaped receptacle is particularly suited for catching dirt and foreign objects that can jam the ball or stud and prevent its reinsertion into the socket of the receptacle.
  • a need has been identified for a disengageable copilot control stick that can be rapidly reconnected to the aircraft flight control system.
  • Such a control stick should also provide some degree of aircraft control before it is fully connected, should not provide a catch-basin for dirt and other foreign objects, and should not become jammed during reconnection even if the copilot inputs control stick forces counter to those of the pilot.
  • the present invention is a disengageable copilot's quick connect cyclic control stick for dual controlled aircraft.
  • the copilot's stick is designed to be easily disengaged from the aircraft flight control system and rapidly reconnected without jamming.
  • the present invention comprises a copilot's control stick that is releasably connected to a pivot assembly at the base of the control stick.
  • the lower portion of the control stick comprises a fork that is attached to the outside of a gimbal member which is mounted in a support assembly.
  • the pivot assembly is joined by means of a uni-ball bearing to the inside of the gimbal member.
  • a single shaft extends through the fork of the stick, the gimbal member, and the uni-ball bearing of the pivot assembly.
  • the pivot assembly includes a stud extending forward and upward along the axis of the lower end of the control stick.
  • the stud fits into a socket at the forward and upper end of a cone or bell-shaped housing or receptacle attached to the control stick.
  • An extension of the housing is slidably mounted in a sleeve of the control stick.
  • a lever assembly is pivotally mounted on the control stick and attached to the receptacle. Pivoting the lever assembly forces the housing to move in a forward and upward direction in the sleeve of the stick so as to lift the housing off the stud of the pivot assembly.
  • the end of the lever assembly remote from the end attached to the housing can be pivoted to engage a hitch under the copilot's seat and secured thereto by a lock/release catch. Engagement of the lever assembly on the hitch disengages the socket from the stud of the pivot assembly and locks the control stick in a central fixed position.
  • the pivot assembly which is connected by a linkage to the pilot's stick and the aircraft flight control system, remains free to pivot about the uni-ball bearing without interference from the disengaged copilot's control stick.
  • the open lower end of the housing surrounds the stud and circumscribes the movement of the stud as the pivot assembly moves independently of the disengaged control stick.
  • the copilot's stick is reconnected to the aircraft flight control system by releasing the lock/release so that the lever assembly is free to pivot back to its normal position.
  • the housing is spring loaded in the sleeve of the control stick so as to be forced downward and aft onto the stud of the pivot assembly.
  • the interior conical surface of the housing centers the housing on the stud so that the stud is reengaged in the socket of the housing.
  • the housing of the present invention opens downward, it does not form a basin for catching dirt and foreign objects which might jam the controls during reconnection of the stick.
  • the shape of the housing is designed to encompass all movements of the stud while the stick is disconnected so that the housing always confines the stud during reconnection of the control stick.
  • copilot inputs to the control stick during reconnection will have at least partial effect on the aircraft flight controls due to the force of the housing on the stud even before the stud is reinserted into the socket.
  • FIGURE 1 is a partially exploded isometric view of the copilot quick connect cyclic stick of the present invention
  • FIGURE 2 is a partially cutaway left side plan view of the control stick of the present invention.
  • FIGURE 3 is a bottom plan view of the housing of the present invention as viewed from the section line 3-3 of FIGURE 2.
  • FIGURES 1 and 2 the copilot quick connect cyclic stick of the present invention is generally identified by the reference numeral 10.
  • the control stick 10 is mounted on a support assembly 12, which is typically bolted to the floor of the aircraft beneath the copilot's seat 13.
  • a gimbal member 14 is mounted for pivotal motion in the support assembly 12.
  • the control stick 10 comprises a fork assembly 15 at its lower end.
  • the fork 15 is mounted on the outside of the gimbal member 14 by bearings 16 and a shaft 17 which extends through the bearings 16 and the gimbal member 14.
  • the control stick 10 is pivotable left and right on the gimbal member 14 and forward and aft on the shaft 17.
  • a pivot member 18 is mounted to the inside of the gimbal member 14 by means of a uni-ball bearing 20.
  • the shaft 17 extends through the bearings 16, the gimbal member 14, and the uni.-ball bearing 20.
  • the uni-ball bearing 20 allows the pivot member 18 to pivot left, right, forward, and aft independently of the motion of the control stick 10.
  • a bearing 21 of the pivot member 18 provides a connection for mechanical linkage 19 to the aircraft flight controls.
  • the pivot member 18 also includes a stud 22 that extends forward and upward from the pivot member 18.
  • a cone or bell-shaped receptacle or housing 24 is positioned between the forks 15 and slidably mounted within a sleeve 26 of the control stick 10.
  • a coil spring 27 inside the sleeve 26 urges the housing 24 downward and aft so that the stud 22 of the pivot member 18 plugs into a socket 25 at the vertex of the housing 24.
  • the control stick 10 and the pivot member 18 are rigidly connected and pivot in unison on the gimbal member 14 and the shaft 17.
  • a lever assembly 30 is pivotally mounted on the control stick 10 and attached to arms 32 which are connected to the housing 24.
  • a coil spring 34 biases the lever assembly 30 upward and away from the pivot member 18. Actuation of the lever assembly toward the pivot member 18 causes the housing 24 to slide forward and upward against the spring 27 in the * sleeve 26 so as to unplug the stud 22 from the socket 25. As shown in FIGURE 2, the actuated lever assembly 30 is pivoted to engage a hitch 40 mounted on or under the copilot's seat 13. A catch 42 is used to lock the lever assembly 30 on the hitch 40.
  • the control stick 10 With the lever assembly 30 locked on the hitch 40, the control stick 10 is rigidly fixed in a central position and disengaged from the pivot member 18, which remains free to pivot about the uni-ball bearing 20 independent of the control stick 10.
  • the housing 24 extends around and circumscribes the full extent of the movement of the stud 22 (as illustrated in phantom by 22a and 22b in FIGURE 2) while the pivot member 18 moves and the control stick 10 remains fixed in place.
  • the disengaged control stick 10 is quickly reengaged with the aircraft flight control system simply by releasing the catch 42 to unlock the lever assembly 30. With the catch 42 released, the spring 34 pivots the lever assembly 30 off the hitch 40 and away from the pivot member 18 as illustrated in phantom by 30a.
  • the conical-shaped interior of the housing 24 guides the stud 22 into the socket 25 to rigidly reconnect the control stick 10 to the pivot member 18, whereupon the control stick 10 and the pivot member 18 pivot in unison on the gimbal 14 and the shaft 17.
  • the control stick 10 of the present invention cannot jam the aircraft flight controls during reconnection because the stud 22 never departs from the confines of the conical-shaped housing 24.
  • the housing 24 opens downward so that dirt and foreign objects will not fall into the socket 25 to prevent reconnection of the control stick 10 to the pivot member 18.
  • the housing 24 of the present invention provides some input tq.-the flight control system due to the force of the housing against the stud 22 even when the stud 22 is not inserted in the socket 25.

Landscapes

  • Engineering & Computer Science (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Control Devices (AREA)
  • Graft Or Block Polymers (AREA)
  • Branch Pipes, Bends, And The Like (AREA)
  • Silicon Polymers (AREA)

Abstract

La présente invention concerne des chaînes de pilotage d'aéronefs et, en particulier, un manche copilote débrayable pouvant être ré-embrayé rapidement sans s'enrayer. Un manche de pilotage d'aéronef (10) est monté sur un cardan (14) assurant son pivotement vers la gauche, la droite, l'avant et l'arrière. Un logement en forme de cloche (24) est monté coulissant sur le manche (10). Le logement (24) est sollicité par un ressort vers le bas en direction du pivot (18) de sorte qu'un goujon (22) faisant saillie vers le haut par rapport à ce dernier s'emboîte dans une douille (25) ménagée dans le logement (24). Le logement (24) orienté vers le bas limite tout mouvement éventuel du goujon (22) tandis que le manche (10) est débrayé. La libération de l'ensemble levier (30) permet à un ressort (27) de solliciter le logement (24) vers le bas en direction du goujon (22). L'intérieur conique du logement (24) guide le goujon (22) jusque dans la douille (25) pour permettre de reconnecter le manche (10) au pivot (18) et aux commandes de pilotage.
EP19870907687 1987-06-15 1987-06-15 MANCHE de commande copilote a embrayage rapide. Ceased EP0317577A4 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US1987/001360 WO1988010209A1 (fr) 1987-06-15 1987-06-15 Manche cyclique copilote a embrayage rapide

Publications (2)

Publication Number Publication Date
EP0317577A1 true EP0317577A1 (fr) 1989-05-31
EP0317577A4 EP0317577A4 (fr) 1989-12-14

Family

ID=22202414

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19870907687 Ceased EP0317577A4 (fr) 1987-06-15 1987-06-15 MANCHE de commande copilote a embrayage rapide.

Country Status (5)

Country Link
EP (1) EP0317577A4 (fr)
JP (1) JPH02500661A (fr)
AU (1) AU606114B2 (fr)
BR (1) BR8707802A (fr)
WO (1) WO1988010209A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109415117A (zh) * 2016-04-22 2019-03-01 拉蒂尔菲雅克股份有限公司 控制杆枢轴

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4403049C1 (de) * 1994-01-28 1995-09-07 Mannesmann Ag Stranggießanlage und Verfahren zur Erzeugung von Dünnbrammen

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB124363A (en) * 1918-07-26 1919-03-27 Frank Ford Peregrine Walsh Improvements in or relating to Aircraft Controls.
US4073199A (en) * 1976-10-22 1978-02-14 Paccar Inc Break-over shift lever assembly
FR2525000A1 (fr) * 1982-04-07 1983-10-14 Aerospatiale Manche de commande debrayable pour copilote d'aeronef

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
No further relevant documents have been disclosed. *
See also references of WO8810209A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109415117A (zh) * 2016-04-22 2019-03-01 拉蒂尔菲雅克股份有限公司 控制杆枢轴

Also Published As

Publication number Publication date
JPH02500661A (ja) 1990-03-08
AU606114B2 (en) 1991-01-31
BR8707802A (pt) 1989-10-17
EP0317577A4 (fr) 1989-12-14
WO1988010209A1 (fr) 1988-12-29
AU8325887A (en) 1989-01-19

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Legal Events

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PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

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17P Request for examination filed

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Effective date: 19891214

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