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WO1993011407A1 - Dispositif informant un pilote des assiettes d'un aeronef - Google Patents

Dispositif informant un pilote des assiettes d'un aeronef Download PDF

Info

Publication number
WO1993011407A1
WO1993011407A1 PCT/SE1992/000806 SE9200806W WO9311407A1 WO 1993011407 A1 WO1993011407 A1 WO 1993011407A1 SE 9200806 W SE9200806 W SE 9200806W WO 9311407 A1 WO9311407 A1 WO 9311407A1
Authority
WO
WIPO (PCT)
Prior art keywords
vehicle
light
light beam
source
navigation equipment
Prior art date
Application number
PCT/SE1992/000806
Other languages
English (en)
Inventor
Torbjörn SEGERSTRÖM
Original Assignee
Saab Missiles Aktiebolag
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 Saab Missiles Aktiebolag filed Critical Saab Missiles Aktiebolag
Publication of WO1993011407A1 publication Critical patent/WO1993011407A1/fr

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft

Definitions

  • the present invention relates to a device for directing the attitude of a vehicle, especially an air vehicle, especially in heading and pitch, the vehicle being provided with navigation equipment, designating the current attitudes of the vehicle in an earthrelated coordinate system.
  • An operator of an air vehicle i.e. an aircraft or a helicopter must today fetch steering information from a number of instruments located in the cockpit, such_ s compass and various equipment that works with radi ⁇ waves within the VHF range, such as VOR, Glidbane-Loc.finder, or within the MW/LW range, such as ADF.
  • navigation information e.g. a presentation on the cockpit screen or some sort of sight line indicator, a so-called Head Up display or a presentation built in a helmet to be carried by the operator.
  • Such devices have hitherto been very expensive and thereby available only to military aircraft and helicopters.
  • such a device is characterized by a combination of:
  • At least one source of light preferably a laser
  • a first direction means directing a light beam from said source of light forward according to a reference direction
  • a second direction means arranged to direct a light beam frcm the light source in accordance with at least one attitude direction, in relation to a direction given by said navigation equipment
  • the reference direction can be parallel with the longitudinal axis of the vehicle, but depending on the actual flight case, taking in account the velocity of the vehicle and wind direction, the reference direction can deviate considerably from a direction parallel with the longitudinal direction of the vehicle.
  • the reference direction shall therefore be adjustable.
  • the source of light is suitably located in front of the operator, outside cockpit, and directs as mentioned a light beam preferably in the reference direction, i.e. in its heading attitude.
  • the operator sees this light beam, if it is dark and especially if it is scmewhat foggy or rainy weather, i.e. particularly when the need for safe navigation information is great.
  • the operator so acts upon the vehicle attitudes with his steering means that the light beam in the direction of the vehicle coincides with a second light beam, whose direction is decided by the navigation equipment mentioned in the introduction, which gives attitude directions related to an earthrelated coodinate system, through which arrangement the vehicle will travel along the intended flight path, which has been programmed in the navigation equipment.
  • the navigation equipment gives information on both heading and pitch attitudes, i.e. is three-dimensionally designed, all the required steering information can be obtained.
  • the light source is followed by a beam expander for expanding the light beam.
  • the first direction means consists of a first, semi-opaque mirror and the second direction means of a second mirror, arranged to be adjusted by an adjustment means, acted upon by said navigation equipment.
  • the first and second direction means are combined to one optoacoustical modulator for deflecting the light beam.
  • Figure 1 shows schanatically a plan view of a part of a helicopter provided with a device according to the invention
  • Figure 2 shows schematically a plan view of a first embodiment of the device according to the invention
  • Figure 3 shows schanatically a plan view of a second embodiment of the device according to the invention.
  • a helicopter is designated by 1 with an operator outlined, designated by 2.
  • a source of light is suggested, and is marked by 3.
  • a light beam 4 goes out in the direction of the horizontal direction of the vehicle, showing the heading attitude, while a light beam 5 shows the attitude given and decided by the navigation equipment. In order that the vehicle shall be brought on the correct heading the operator must by acting on the steering means bring the light beams 4 and 5 to coincide.
  • FIG 2 shows schematically a device to achieve the light beams 4 and 5 in Figure 1.
  • a source of light comprises a laser 6, which can be a 5 mW Argon laser with the wavelength 543 nm.
  • a rigid semi-opaque first mirror 7 reflects some of the incident laser light beam 8 in the form of said light beam 4, whereas the rest of the laser light beam (8) goes on and is reflected by a second mirror 9, arranged movable by means of an adjustment means 10, which is acted upon by the navigation equipment 11 to set the mirror 9 so that the light beam 5 is directed in the direction that the actual attitude, in this case heading, is desired to take.
  • the operator thus controls the steering means, not shown, to steer in the vehicle, so that the light beam 4 coincides with the light beam 5, at which point the vehicle is on the correct heading.
  • the device When landing in the dark, the device points out the landing ground on the change over from_IFR-VRF, and designates the glidepath.
  • the device according to the invention which is shown schanatically in Figure 3, there is a laser 6, followed by a radiation expander 12, which expands the light beam ccming from the laser.
  • the aforementioned first and second direction means have been combined and consist in this case of an optoacoustical modulator (14) for deflecting the light.
  • the function is that the lasers are rapidly set on and off synchronically with two input signal values to the optoacoustic modulator, i.e. values partly corre ⁇ sponding to said reference direction, and partly the desired direction value given by the navigation equipment.
  • the quich change between laser on and laser off is not possible for the eye to perceive, and therefore during observation the eye perceives two different beams.
  • the device according to the invention can also be used to warn other vehicles, especially air vehicles in the vicinity of an airport, and can also serve to identify vehicles.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Navigation (AREA)

Abstract

Dispositif de commande des assiettes notamment d'un aéronef. Un équipement de navigation produit des informations relatives aux assiettes d'un aéronef dans un système de coordonnées terrestres. Le dispositif comprend une source lumineuse tel qu'un laser (6), un premier moyen d'orientation (7), (14) orientant un faiseau de lumière (4) vers l'avant selon une direction de référence, et un second moyen d'orientation (9, 10, 14) orientant un faiseau de lumière (5) dans une direction donnée par l'equipement de navigation (11). Le dispositif est agencé de manière que l'utilisateur a son champ de vision en ligne avec la direction de référence (4) et la direction donnée par l'équipement de navigation (11), obtenant ainsi des informations de pilotage. Les premier et second moyens directionnels peuvent être combinés (14).
PCT/SE1992/000806 1991-11-25 1992-11-24 Dispositif informant un pilote des assiettes d'un aeronef WO1993011407A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SE9103475-1 1991-11-25
SE9103475A SE9103475D0 (sv) 1991-11-25 1991-11-25 Presentationssystem foer navigering och vaegledning

Publications (1)

Publication Number Publication Date
WO1993011407A1 true WO1993011407A1 (fr) 1993-06-10

Family

ID=20384416

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE1992/000806 WO1993011407A1 (fr) 1991-11-25 1992-11-24 Dispositif informant un pilote des assiettes d'un aeronef

Country Status (2)

Country Link
SE (1) SE9103475D0 (fr)
WO (1) WO1993011407A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2502689A (en) * 2012-04-02 2013-12-04 Boeing Co Location determination and navigation using a searchlight
CN107589751A (zh) * 2016-07-07 2018-01-16 中兴通讯股份有限公司 一种信息获取方法和装置

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB848583A (en) * 1958-02-28 1960-09-21 Gen Electric Co Ltd Improvements in or relating to angle of approach indicators for aircraft landings
US4147056A (en) * 1977-09-23 1979-04-03 Sundstrand Data Control, Inc. Multi-segment head-up display for aircraft
EP0109809A2 (fr) * 1982-11-12 1984-05-30 AlliedSignal Inc. Horizon artificiel
WO1992008107A1 (fr) * 1990-10-25 1992-05-14 Donald Burkhardt Appareil de projection d'un horizon artificiel visionnable par la vision peripherique

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB848583A (en) * 1958-02-28 1960-09-21 Gen Electric Co Ltd Improvements in or relating to angle of approach indicators for aircraft landings
US4147056A (en) * 1977-09-23 1979-04-03 Sundstrand Data Control, Inc. Multi-segment head-up display for aircraft
EP0109809A2 (fr) * 1982-11-12 1984-05-30 AlliedSignal Inc. Horizon artificiel
WO1992008107A1 (fr) * 1990-10-25 1992-05-14 Donald Burkhardt Appareil de projection d'un horizon artificiel visionnable par la vision peripherique

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2502689A (en) * 2012-04-02 2013-12-04 Boeing Co Location determination and navigation using a searchlight
GB2502689B (en) * 2012-04-02 2014-12-10 Boeing Co Searchlight Location System
US8996203B2 (en) 2012-04-02 2015-03-31 The Boeing Company Searchlight location system
CN107589751A (zh) * 2016-07-07 2018-01-16 中兴通讯股份有限公司 一种信息获取方法和装置

Also Published As

Publication number Publication date
SE9103475D0 (sv) 1991-11-25

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