WO1988010209A1 - Manche cyclique copilote a embrayage rapide - Google Patents

Manche cyclique copilote a embrayage rapide Download PDF

Info

Publication number
WO1988010209A1
WO1988010209A1 PCT/US1987/001360 US8701360W WO8810209A1 WO 1988010209 A1 WO1988010209 A1 WO 1988010209A1 US 8701360 W US8701360 W US 8701360W WO 8810209 A1 WO8810209 A1 WO 8810209A1
Authority
WO
WIPO (PCT)
Prior art keywords
control stick
stud
housing
assembly
pivot
Prior art date
Application number
PCT/US1987/001360
Other languages
English (en)
Inventor
Andrew Smith
Frank Wolstencroft
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.
Priority to PCT/US1987/001360 priority Critical patent/WO1988010209A1/fr
Priority to BR8707802A priority patent/BR8707802A/pt
Priority to AU83258/87A priority patent/AU606114B2/en
Priority to US07/132,949 priority patent/US4865277A/en
Priority to JP88500771A priority patent/JPH02500661A/ja
Priority to EP19870907687 priority patent/EP0317577A4/fr
Priority to IL86729A priority patent/IL86729A/xx
Priority to CA000569412A priority patent/CA1285196C/fr
Publication of WO1988010209A1 publication Critical patent/WO1988010209A1/fr

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.
PCT/US1987/001360 1987-06-15 1987-06-15 Manche cyclique copilote a embrayage rapide WO1988010209A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
PCT/US1987/001360 WO1988010209A1 (fr) 1987-06-15 1987-06-15 Manche cyclique copilote a embrayage rapide
BR8707802A BR8707802A (pt) 1987-06-15 1987-06-15 Manche desengatavel para controle de aeronave e manche de copiloto com controle ciclico de rapida conexao
AU83258/87A AU606114B2 (en) 1987-06-15 1987-06-15 Copilot quick connect cyclic stick
US07/132,949 US4865277A (en) 1987-06-15 1987-06-15 Copilot quick connect cyclic stick
JP88500771A JPH02500661A (ja) 1987-06-15 1987-06-15 副操縦士用迅速連結サイクリツク操縦棒
EP19870907687 EP0317577A4 (fr) 1987-06-15 1987-06-15 MANCHE de commande copilote a embrayage rapide.
IL86729A IL86729A (en) 1987-06-15 1988-06-13 Copilot quick connect cyclic stick
CA000569412A CA1285196C (fr) 1987-06-15 1988-06-14 Manche cyclique a connexion rapide pour le copilote

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 (1)

Publication Number Publication Date
WO1988010209A1 true WO1988010209A1 (fr) 1988-12-29

Family

ID=22202414

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1987/001360 WO1988010209A1 (fr) 1987-06-15 1987-06-15 Manche cyclique 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
CN1046449C (zh) * 1994-01-28 1999-11-17 曼内斯曼股份公司 生产薄板坯的连续铸锭设备和方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA3021904A1 (fr) * 2016-04-22 2017-10-26 Ratier-Figeac Sas Pivot de manche de commande

Citations (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
US4473203A (en) * 1982-04-07 1984-09-25 Societe Nationale Industrielle Et Aerospatiale Disengageable control column for a copilot of an aircraft

Patent Citations (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
US4473203A (en) * 1982-04-07 1984-09-25 Societe Nationale Industrielle Et Aerospatiale Disengageable control column for a copilot of an aircraft

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP0317577A4 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1046449C (zh) * 1994-01-28 1999-11-17 曼内斯曼股份公司 生产薄板坯的连续铸锭设备和方法

Also Published As

Publication number Publication date
JPH02500661A (ja) 1990-03-08
AU606114B2 (en) 1991-01-31
BR8707802A (pt) 1989-10-17
EP0317577A1 (fr) 1989-05-31
EP0317577A4 (fr) 1989-12-14
AU8325887A (en) 1989-01-19

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