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WO1996015514A1 - Simulateur de vol pouvant effectuer une rotation complete en roulis - Google Patents

Simulateur de vol pouvant effectuer une rotation complete en roulis Download PDF

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Publication number
WO1996015514A1
WO1996015514A1 PCT/US1995/014975 US9514975W WO9615514A1 WO 1996015514 A1 WO1996015514 A1 WO 1996015514A1 US 9514975 W US9514975 W US 9514975W WO 9615514 A1 WO9615514 A1 WO 9615514A1
Authority
WO
WIPO (PCT)
Prior art keywords
die
occupant
station
control
rotating
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
PCT/US1995/014975
Other languages
English (en)
Inventor
Eduard Feuer
Ronald L. Brown
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to AU42842/96A priority Critical patent/AU4284296A/en
Publication of WO1996015514A1 publication Critical patent/WO1996015514A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • G—PHYSICS
    • G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
    • G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
    • G09B9/00—Simulators for teaching or training purposes
    • G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
    • G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
    • G09B9/12—Motion systems for aircraft simulators
    • G09B9/14—Motion systems for aircraft simulators controlled by fluid actuated piston or cylinder ram

Definitions

  • the present invention relates generally to the field of amusement rides which simulate aircraft or space flight with visual presentations and motion.
  • the flight simulator provides for independent control of rotation about a pitch axis and roll axis including the capability for complete inversion of an occupant station simulating a cockpit.
  • Motion simulators for training and amusement are well known in the art. Aircraft simulators for use by the military and airlines incorporate highly sophisticated hydraulic drive systems often offering up to six axes of motion for relatively short dimensional excursions. Amusement rides offering motion simulation for automobiles, space flight, aircraft and other fantasy travel have typically employed technology very similar to the high fidelity training simulators while somewhat reducing complexity and cost.
  • a typical system employs a platform having an occupant station which incorporates a means for visual simulation through motion picture or computer-generated scenery imaging. The occupant platform is mounted on or suspended from multiple hydraulic actuators which impart motion to the platform. The number and mounting location of the actuators is determined in engineering tradeoffs for size of the actuators and the equations of motion to be used for the simulation. Three actuator systems and six actuator systems are common with mounting in a triangular pattern on the motion platform.
  • the flight simulator of the present invention incorporates an operator station having seating and operating controls for an occupant.
  • a visual simulation system incorporating approximately 120° forward field of view is provided employing color projection from three projectors using reflected beams to semi-spherical screens on the cabin face separated by simulated window frames.
  • a reflected beam system allows a compressed arrangement of the projectors relative to the screen reducing the necessary size for the operator station.
  • the operator station is attached to a structural support through a rotating axle assembly providing unlimited angular rotation about a first axis, preferably the simulated roll axis of the operator station.
  • the axle assembly is mounted through a transverse bearing pin which provides limited angular rotation about a second axis, preferably the pitch axis for the operator station.
  • An axle running through the rotating axle assembly, with tapered roller bearings supporting the axle within a case or hub of the axle assembly, is attached to the operator station through a rigid flange.
  • a motor and gear reduction system provides rotation of the axle within the case for rotational about the first axis.
  • a linear actuator attached to a lever arm depending from the case bottom provides leverage for pivotal rotation of the axle about the second axis.
  • the motor and linear actuator are controlled through digitally controlled hydraulic valves driven by a two axis motion controller. Inputs from the controls in the operator station are provided to a control computer which provides commands to the two axis motion controller for creating motion in the linear actuator and rotating axle derived from control equations responsive to the motion of the operator controls.
  • a rotating electrical coupling concentric with the axle allows arrangement of the control computer system on board the operator station, with the coupling conducting motion control signals to the two axis motion controller, or mounting of the motion control computer off board on the support structure for*direct connection to the motion controller with signals from the operator control on board the operator station provided through the rotating coupling.
  • FIG. 1 is a top view of a first embodiment of the invention employing a single seat operator station.
  • FIG. 2 is a side elevational view of the first embodiment of FIG. 1.
  • FIG. 3 is a block diagram schematic of the control system for the first embodiment with off board mounting of the control computer.
  • FIG. 4 is a schematic of the control signals provided through the rotating coupling for the embodiment of FIG. 3.
  • FIG. 5 is a schematic block diagram of the control system arrangement for a second embodiment employing on board mounting of the control computer.
  • FIG. 6 is a schematic of the control signals for the embodiment of FIG. 5.
  • FIG. 7 is a detail sectional side elevation view of the rotating axle assembly.
  • FIG. 1 discloses a first embodiment of the invention for a single seat motion simulator.
  • the operator station or seat capsule 10 incorporates a structural cage 12 mounted to a back plane 14.
  • a floor 16 mounted within the cage supports a seat 18 for the occupant or patron.
  • Operator controls in the form of an aircraft type stick 20 and throttle 21 are mounted proximate the seat for operation by the occupant.
  • a visual display for the occupant is provided by a projector system which incorporates three projectors 22a, 22b and 22c.
  • Each projector provides three color imagery in a folded reflection arrangement by directing the projection substantially rearward to a first surface mirror 24a, 24b and 24c, respectively, which reflects the imagery to a semi-spherical screen 26.
  • three projectors provide three reflected images of approximately 40° each to three separate spherical screen segments 26a, 26b and 26c.
  • the three screens are separated by simulated window frame posts 28 in the embodiment shown.
  • projection arrangements for seamless imagery projection by the three projectors may be employed.
  • the operator station is supported from the back plane by the axle assembly 30 which is attached to the structural support frame 32.
  • the axle assembly incorporates a case 34 with bearings 36 supporting an axle 38 as best seen in detail in FIG. 7.
  • the axle is rigidly attached to the occupant station back plane through a flange 40.
  • a hydraulic motor 42 rotationally drives the axle through a planetary gear box 44 employed to obtain proper rotational speeds and mechanical advantage.
  • a hydraulic brake assembly 46 is employed for positive positioning control.
  • the hydraulic motor comprises a Von Ruden model RSB04S while the planetary gear box comprises a Von Ruden series 300 providing a 10/1 gear reduction and the hydraulic brake comprises a Von Ruden B045228.
  • a transverse mounting pin 50 supported in a sleeve 52 welded to the case transverse to the rotational axis of the axle.
  • the pin is supported in bearings 54 which are mounted in trunnions 55 on support arms 56 which are in turn attached to the remainder of the structural support and appropriately braced.
  • a lever arm 58 as best seen in FIGs. 2 and 7 is connected to the case and provides attachment for a linear actuator such as hydraulic cylinder 60 which is in turn pivotally mounted to the support frame.
  • Rotation about the first axis by driving of the axle with the hydraulic motor is unlimited due to the novel structural arrangement of the present invention.
  • the first axis comprises a roll axis for the occupant station
  • simulation of complete 360° and greater rolls are possible.
  • Rotation about the second axis transverse to the first axis is accomplished by actuation of the hydraulic cylinder.
  • pitch rotation of approximately ⁇ 60° is possible for total excursion of the operator station of approximately 120° in the pitch plane.
  • the simple mechanical structure of the present invention allows dramatic simulation of two axes of motion using only two motion sources, the hydraulic motor driving the axle for roll motion and the hydraulic cylinder providing the linear actuator for pitch motion.
  • Control of the simulator is accomplished through a computer simulation system which employs inputs from the operator control stick and throttle as representing the desired motion.
  • a first embodiment of the control system is shown in FIG. 4 wherein a control computer 70 is mounted off board from me operator station. Communications with the control CPU by the imaging system comprising the three projectors 22, the control stick 20 and a throttle 21 is accomplished through a rotatable coupling comprising a slip ring assembly 72.
  • the slip ring assembly comprises a 29 circuit slip ring carrying the signals disclosed in FIG. 4. 120v power for the projectors is provided through three connections on the slip ring.
  • a switch reference voltage, a potentiometer reference voltage and a potentiometer common employ three rings while switch return circuits for door position switch, gun trigger, gun select and radar on/off comprise four rings.
  • Pitch and roll potentiometer return signals from the control stick comprise two rings while the potentiometer return from the throttle comprises one ring.
  • Audio communications are provided on two channels with an audio return on a third ring.
  • a projector ground is provided and red, blue and green projection signals with horizontal sync are provided for each projector.
  • die preferred slip ring is a Fabricast model 2462-3.627- 29-36U.
  • motion of the seat capsule simulates the flight of an aircraft.
  • Inputs from the control stick 20 in the occupant station are provided to die control computer which calculates position and motion equations in time sequence based on d e control inputs.
  • the dirottle provides a positive or negative velocity component for the control equations.
  • the equations of motion derived by the computer are provided to d e two axis motion control system 74, which provides servo control for digitally controlled valves in the hydraulic power unit 76 to drive die motor 44 and hydraulic cylinder 60 for roll and pitch motion respectively.
  • the two channels of d e motion controller compare position information commanded by me computer with current encoded position and provide velocity commands to die hydraulics for motion control.
  • an XTAR flight dynamics computer system is employed to simulate aircraft flight.
  • the XTAR flight dynamic system incorporates equations of motion to create occupant station position and motion to simulate aircraft flight.
  • the visual display in the operator station is also controlled by die equations of motion provided by d e XTAR flight dynamics computer.
  • Digital imagery is generated in the control computer and provided to d e projectors for display on die screens in the occupant station.
  • FIG. 5 A second embodiment of die control system employing on board mounting of die control computer is shown in FIG. 5.
  • the occupant station or capsule control computer 78 is mounted on board die occupant station.
  • Control inputs provided by d e operator control stick and throtUe as previously described are available directly to an I/O card in the capsule control computer.
  • die capsule control computer provides image data for die projectors to be displayed on die screens in d e occupant station.
  • Placement of me control computer on board using a Pentium ® based processor allows substantially unlimited expansion of the control input capability for the system.
  • a plurality of controls can now be available including pitch velocity and roll velocity from the control stick, missiles, bombs, shield, etc. from switch controls, and velocity and reverse dirust from the throttle.
  • Expansion of die occupant station to a two seat configuration is easily accomplished allowing additional inputs from a second joy stick in die system providing signals such a vertical control beaming retinal and additional bombs and shield controls.
  • a standard I/O card 80 interfaces the capsule control computer to die various control signals.
  • placing of die control computer on board allows simplification of die rotating electrical coupling system to a slip ring 82 widi a reduced number of circuits.
  • Communication from the capsule control computer employs standard four wire Ethernet ® communication for all control functions. This allows the use of an eleven circuit slip ring which employs three circuits for 120v AC power, four circuits for die Ediernet ® , two individual circuits for safety interlocks such as a door switch, and two capsule to control console audio communication lines.
  • a preferred slip ring for use in die second embodiment is a Maurey Instruments model SR 2775-6-11-3.627 slip ring connector system.
  • die motion controller 84 which in die second embodiment comprises a 486 processor.
  • the motion control system interfaces widi die digitally controlled hydraulic valves for control of die motor and linear actuator as previously described.
  • an administrative computer 86 is employed for communication widi die motion controller on a bus 88 having die capacity to communicate widi a plurality of motion control computers.
  • the administrative CPU may provide system interlocks to activate die motion controllers for each of a plurality of motion simulators.

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  • Engineering & Computer Science (AREA)
  • Theoretical Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Business, Economics & Management (AREA)
  • Physics & Mathematics (AREA)
  • Educational Administration (AREA)
  • Educational Technology (AREA)
  • General Physics & Mathematics (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)

Abstract

Ce simulateur de vol comprend une cabine (10) avec un siège (18) ainsi que des commandes (20) pour son utilisateur. Un système d'essieu rotatif (30) est fixé à la cabine d'une part, et à un châssis d'autre part. Ce système d'essieu rotatif peut faire pivoter la cabine sur plus de 360° dans l'axe de roulis. Ce simulateur de vol comprend également un ordinateur de contrôle (70), lequel reçoit les signaux électriques provenant des commandes et transmettant les différents ordres de mouvement, et gère le fonctionnement du moteur.
PCT/US1995/014975 1994-11-16 1995-11-16 Simulateur de vol pouvant effectuer une rotation complete en roulis Ceased WO1996015514A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU42842/96A AU4284296A (en) 1994-11-16 1995-11-16 Flight simulator with full roll rotation capability

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US34028794A 1994-11-16 1994-11-16
US08/340,287 1994-11-16

Publications (1)

Publication Number Publication Date
WO1996015514A1 true WO1996015514A1 (fr) 1996-05-23

Family

ID=23332710

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1995/014975 Ceased WO1996015514A1 (fr) 1994-11-16 1995-11-16 Simulateur de vol pouvant effectuer une rotation complete en roulis

Country Status (2)

Country Link
AU (1) AU4284296A (fr)
WO (1) WO1996015514A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0808493A4 (fr) * 1995-02-06 2000-01-05 Maxflight Corp Simulateur de vol ameliore
WO2004006211A1 (fr) * 2002-07-04 2004-01-15 Don Reid Simulateur
WO2013153239A1 (fr) * 2012-04-12 2013-10-17 Virtual Fly, S.L. Structure pour simulateur de véhicule de transport
CN103623582A (zh) * 2013-11-13 2014-03-12 芜湖华强文化科技产业有限公司 一种安装在飞行体验装置上的刹车装置
CN103886782A (zh) * 2014-04-09 2014-06-25 陈京波 一种360度全向过载飞行仿真模拟器
US9289693B1 (en) 2014-11-26 2016-03-22 Hogan Mfg., Inc. Motion platform for a simulation device
US9430953B2 (en) 2014-11-26 2016-08-30 Hogan Mfg., Inc. Simulation device with motion stabilization
CN107008013A (zh) * 2017-04-27 2017-08-04 江苏金刚文化科技集团股份有限公司 万向运动装置及飞翔体验装置
WO2018141023A1 (fr) * 2017-02-02 2018-08-09 Advancing Projects Pty Ltd Simulateur de conduite de véhicule pour l'entraînement de conducteurs de voitures ou l'utilisation de dispositifs mobiles commandés ou occupés par des êtres humains
CN115527407A (zh) * 2021-06-26 2022-12-27 智崴资讯科技股份有限公司 移动模拟装置

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2485266A (en) * 1944-07-14 1949-10-18 Link Aviation Inc Training apparatus
US3281962A (en) * 1964-07-31 1966-11-01 Gen Precision Inc Motion system for an aircraft flight simulator
US3496650A (en) * 1967-08-30 1970-02-24 Us Navy Air cushion proprioceptive motion system
US3584429A (en) * 1967-07-20 1971-06-15 Link Miles Ltd Angular positioning apparatus for vehicle simulator
US4019261A (en) * 1975-05-09 1977-04-26 The Singer Company Motion system for a flight simulator
US4751662A (en) * 1986-07-14 1988-06-14 United States Of America As Represented By The Secretary Of The Navy Dynamic flight simulator control system
US5388991A (en) * 1992-10-20 1995-02-14 Magic Edge, Inc. Simulation device and system
US5453011A (en) * 1993-06-10 1995-09-26 Feuer; Eduard Flight simulator

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2485266A (en) * 1944-07-14 1949-10-18 Link Aviation Inc Training apparatus
US3281962A (en) * 1964-07-31 1966-11-01 Gen Precision Inc Motion system for an aircraft flight simulator
US3584429A (en) * 1967-07-20 1971-06-15 Link Miles Ltd Angular positioning apparatus for vehicle simulator
US3496650A (en) * 1967-08-30 1970-02-24 Us Navy Air cushion proprioceptive motion system
US4019261A (en) * 1975-05-09 1977-04-26 The Singer Company Motion system for a flight simulator
US4751662A (en) * 1986-07-14 1988-06-14 United States Of America As Represented By The Secretary Of The Navy Dynamic flight simulator control system
US5388991A (en) * 1992-10-20 1995-02-14 Magic Edge, Inc. Simulation device and system
US5453011A (en) * 1993-06-10 1995-09-26 Feuer; Eduard Flight simulator

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0808493A4 (fr) * 1995-02-06 2000-01-05 Maxflight Corp Simulateur de vol ameliore
WO2004006211A1 (fr) * 2002-07-04 2004-01-15 Don Reid Simulateur
WO2013153239A1 (fr) * 2012-04-12 2013-10-17 Virtual Fly, S.L. Structure pour simulateur de véhicule de transport
CN103623582A (zh) * 2013-11-13 2014-03-12 芜湖华强文化科技产业有限公司 一种安装在飞行体验装置上的刹车装置
CN103886782A (zh) * 2014-04-09 2014-06-25 陈京波 一种360度全向过载飞行仿真模拟器
US9289693B1 (en) 2014-11-26 2016-03-22 Hogan Mfg., Inc. Motion platform for a simulation device
US9430953B2 (en) 2014-11-26 2016-08-30 Hogan Mfg., Inc. Simulation device with motion stabilization
WO2018141023A1 (fr) * 2017-02-02 2018-08-09 Advancing Projects Pty Ltd Simulateur de conduite de véhicule pour l'entraînement de conducteurs de voitures ou l'utilisation de dispositifs mobiles commandés ou occupés par des êtres humains
CN107008013A (zh) * 2017-04-27 2017-08-04 江苏金刚文化科技集团股份有限公司 万向运动装置及飞翔体验装置
CN115527407A (zh) * 2021-06-26 2022-12-27 智崴资讯科技股份有限公司 移动模拟装置

Also Published As

Publication number Publication date
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