WO2001020261A1 - Systeme de navigation integre pour differents types d'aeronefs - Google Patents

Systeme de navigation integre pour differents types d'aeronefs Download PDF

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Publication number
WO2001020261A1
WO2001020261A1 PCT/RU2000/000340 RU0000340W WO0120261A1 WO 2001020261 A1 WO2001020261 A1 WO 2001020261A1 RU 0000340 W RU0000340 W RU 0000340W WO 0120261 A1 WO0120261 A1 WO 0120261A1
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WO
WIPO (PCT)
Prior art keywords
aircraft
sisτemy
navigatsiοnnοy
vyχοd
κοmπleκsnaya
Prior art date
Application number
PCT/RU2000/000340
Other languages
English (en)
Russian (ru)
Inventor
Dmitry Anatolievich SAFIAN
Anatoly Dmitrievich SAFIAN
Original Assignee
Grudzinsky, Mikhail Alexandrovich
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 Grudzinsky, Mikhail Alexandrovich filed Critical Grudzinsky, Mikhail Alexandrovich
Publication of WO2001020261A1 publication Critical patent/WO2001020261A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D43/00—Arrangements or adaptations of instruments

Definitions

  • the signals of the multi-channel signal 32 are fed into the signal in the form of a network signal connected to the current components of the LH calculated by the receiver of 32 ⁇ 32, this is coupled with the same speed signal in the same video signal.
  • the simultaneous air carrier 33 calculates the parameters of the positive traffic, including the disconnection of the body of the vehicle at the same time as the calculation of the decrease in the rate of increase of the voltage Taking into account the movement of the vehicle on Fig. 3), it constantly changes and, by performing maneuvers and turns of the vehicle, in automatic mode, it is inactive at the same time and towards the direction of the sowing line of the PPP is already at the initial stage of decline (other 4). From the above, it is also obvious that the whole process of reducing the input and the loss of power is completely eliminated visually on the display screen 37 (Fig. 5).
  • the visualization of the power supply unit by the electronic components of the live network of the user on the network of the main lines at the initial stage of the reduction of the medical equipment means that the P ⁇ tsess imaging ⁇ PPL ⁇ P ele ⁇ nnymi ⁇ eds ⁇ vami important not itself ⁇ itself, but due tog ⁇ that this ⁇ i ⁇ bes ⁇ echivae ⁇ sya naib ⁇ lee accurate and namn ⁇ g ⁇ ⁇ e ⁇ ezhayu- conductive v ⁇ v ⁇ emeni vyv ⁇ d L ⁇ in s ⁇ v ⁇ and na ⁇ avlenie ⁇ sev ⁇ y line ⁇ PPLLP ⁇ a ⁇ in avtoma ⁇ iches ⁇ m, ⁇ a ⁇ and ⁇ uchn ⁇ m ⁇ ezhima ⁇ ⁇ il ⁇ i ⁇ vaniya.
  • switching to an optical visual board with a signal from a pulsed pulsed light circuitry prevents the output from being damaged.
  • the electronic visual board which is available in the optical channel for completing the landing, provides one of the most common means of communication with us.
  • ⁇ dina ⁇ y toche ⁇ 11 and 14 (on ⁇ is.2) s ⁇ ve ⁇ s ⁇ vuyu ⁇ to ⁇ tsu ⁇ PP and mee ⁇ am ⁇ as ⁇ l ⁇ zheniya ⁇ e ⁇ v ⁇ y ⁇ a ⁇ y IS ⁇ 7 and 12 and 13 ⁇ ch ⁇ i lezha ⁇ on ⁇ bei ⁇ sto ⁇ na ⁇ ⁇ PP and s ⁇ ve ⁇ s ⁇ vuyu ⁇ as ⁇ l ⁇ zheniyu v ⁇ y ⁇ a ⁇ y IS ⁇ on u ⁇ vne ⁇ gney ⁇ izemleniya 6.
  • the direct lines 18 and 20, which correspond to the slots of the CPT and the whole line 19, are located on the separate memory card of the 33 memory slots and the slots for the slots are slots for the memory of the slots.
  • Shifting to an optical visual plane is connected to the ship on the IS-7, which is a light-emitting diode operating in the run.
  • the ISP ensures the reliable designation of the control unit for all its functions. and with accuracy, the corresponding optical processing channel. calculates the approximate range of the tangent of the contact, the magnitude of the linear charge, the magnitude of the negative the current flight altitude of the calculated values of ⁇ , GL , ⁇ p and unacceptable ⁇ -
  • both L TM and ⁇ GL are transfered to the 'automatic planting system.
  • Figure 1 General diagram of the function of the integrated navigation system Fig. 2. Scheme of the disposal of public transport points 11, 12, 13, 14, 15, 16 at the airport of destination
  • the image on the screen is a flat display at the initial stage of lowering it and entering the landing.
  • Figure 4 Display on the screen of a flat display at a time when the dynamics of the exit of the LV to the terminal and to the direction of the sowing line of the SPP destination are affected.
  • FIG. 1 General diagram of the function of a complex navigation system. (Fig. 1), consists of the satellite 1 on the Earth, separated from the navigation systems ⁇ 5 and GLONASS. On-site equipment for LH (2), in particular for the US, is lower in this section.
  • the transmitting part of the control system of pulsed light beacons 10, is located at the air terminal at the airborne control unit.
  • the distance between the neighboring IS pairs is 400-500 m; the second end of the ISR couple is located on the line of the KPP, the middle part of which corresponds to the other contact point.
  • ISA operates in the visible and partial in the UF and their range of light radiation and operates in the speed of a traveling wave.
  • Pi ⁇ anie IS ⁇ vs ⁇ aivae ⁇ sya in Li- power The NIJ susches ⁇ vuyuschi ⁇ ⁇ gney ⁇ PP 8 and avton ⁇ mn ⁇ e u ⁇ avlenie i ⁇ ⁇ ab ⁇ toy ⁇ susches ⁇ vlyaetsya ⁇ ⁇ mandn ⁇ y ⁇ adi ⁇ linii, and ⁇ e ⁇ eda ⁇ chi ⁇ an ⁇ enna ⁇ to ⁇ y na ⁇ - dya ⁇ sya on ⁇ n ⁇ ln ⁇ y vysh ⁇ e ae ⁇ a 10 and ⁇ ul ⁇ u ⁇ avleniya na ⁇ di ⁇ sya in ⁇ as ⁇ - ⁇ yazhenii aviadis ⁇ e ⁇ che ⁇ a.
  • the good control commands are different and provide for the automatic switching on / off of ISS 7 and the organization of higher levels by running waves in each of the 2 directions.
  • the UC, (Fig. 5) includes antenna 31, multi-channel receiver 32, aircomputer 33, remote control 34, and a telecom malfunction white flat display 37; One of the outputs of the airline 33 is connected to the outside of the external auto-propulsion system and automatic landing 38.
  • a single system is compatible, it can be, for example, a geocentric system is ⁇ , the system is supplementary wage withdraw admirably - 84 and others.
  • the calculated current outputs from the output of the receiver 32 are connected to the first input of the aircraft 33, the purpose of the connection is to perform the following functions:
  • a quick settlement is ⁇ L6 ⁇ 27, and also a long range of 23 and a ⁇ GL value are a result of a departure from the current calculation;
  • the output signal is a standard signal termed in real time and in the structure ⁇ , which contains a plot in the field of view of the camera and the calculated motion parameters ⁇ ; at this stage of the optical visual board in the event of an unacceptable defect in the chassis, a warning signal is generated.
  • the 35 camera is intended for signal conditioning, which includes a video camera, and, in particular, the PP / PP with pulsed lights and other lighting fixtures.
  • ⁇ s ⁇ benn ⁇ e ⁇ yu ⁇ ame ⁇ y 35 are vys ⁇ aya chuvs ⁇ viteln ⁇ s ⁇ and ⁇ az ⁇ eshayuschaya e ⁇ s ⁇ bn ⁇ s ⁇ , ada ⁇ atsiya ⁇ sl ⁇ zhn ⁇ mu ⁇ ds ⁇ ilayuschemu ⁇ nu, Te ⁇ aches ⁇ vennye ⁇ a ⁇ a ⁇ e ⁇ is ⁇ i ⁇ i, ⁇ to ⁇ ye ⁇ bes- ⁇ echivayu ⁇ ⁇ bna ⁇ uzhenie IS ⁇ and d ⁇ ugi ⁇ ⁇ gney on ma ⁇ simaln ⁇ v ⁇ zm ⁇ zhn ⁇ y daln ⁇ - s ⁇ i.
  • the flat display 37 black-and-white or color, is intended for visualization of the operational and navigation information on all parts of the charger, without taking off the charger and the device.
  • the 34 remote control is intended for the execution of the following functions 1. Disconnection / disconnection of the consumer equipment and the use of the “disconnectable phone” "Class aer ⁇ réelle.” “Airplane” - “Earth”. 10
  • any suitable conditions for the take-off run and take-off mode are used in the main unit 33, 35, 36, and the 37W is fully operational.
  • the crew In general, at any time during the run-up, the crew has accurate and efficient information from the operating or neglected operating modes. 0 After retrieval of basic equipment, the unit is used in e-traffic mode. Gyu echelon movement
  • the step of reducing the initial departure from the echelon depends on the distance between the departure and destination airports. For this, the distance could be chosen equal to 30-35 km, but in principle it can be much larger.
  • Angular and linear values on the network of standard lines in Fig. 4 a, b, c) correspond to their every second updated values.
  • the silhouette of L is indicated and the negative line that goes from it corresponds to the vector of the normal speed ⁇ $.
  • the components of the unit are read out from the memory of the aircraft, they are also used at a time (are used).
  • the large number of fixed lines ⁇ and ⁇ (Fig. 4 a, b, c) shows the scale of the electronic card, which is the only thing that can be done if there is a decrease in the number of lines.
  • Total image shown in FIG. 4 a, b does not save only the visual process of leaving the place of the landing, and there is no noticeable movement. These last ones are transferred to the external system of the autopilot 38 for operation in the automatic mode. Calculation of the safety and navigation parameters and their malfunctions due to the calculation of the reduction (the actual signals of the crucible) may be at risk of
  • the next step - ⁇ bna ⁇ uzhenie sve ⁇ vy ⁇ ⁇ ien ⁇ i ⁇ v ⁇ PP knowledge chiteln ⁇ ⁇ anee vys ⁇ y ⁇ inya ⁇ iya ⁇ esheniya ⁇ P ⁇ ) and ⁇ e ⁇ e ⁇ d ⁇ iches ⁇ y on visual monitoring of ⁇ le ⁇ - ⁇ bes ⁇ echivae ⁇ ⁇ iches ⁇ y ⁇ anal ⁇ S, e ⁇ m ⁇ schnye im ⁇ ulsnye freshly ⁇ maya ⁇ i toemn ⁇ g ⁇ ⁇ b ⁇ ud ⁇ vaniya, ⁇ ab ⁇ ayuschie in ⁇ em ⁇ e running v ⁇ lny; in the C version for helicopters, it’s 3 or 4 light beacons - they are very quick, but the camera and the aircraft are in flight.
  • the luminous illumination direction of the offense increases not only the spectacular efficiency, but also the increase in the efficiency of the solutions.
  • Iz ⁇ b ⁇ e ⁇ enie m ⁇ zhe ⁇ by ⁇ is ⁇ lz ⁇ van ⁇ navigation ⁇ il ⁇ i ⁇ uemy ⁇ and infinite ⁇ il ⁇ tay ⁇ L ⁇ lyuby ⁇ ⁇ lass ⁇ v, av ⁇ mataches ⁇ g ⁇ u ⁇ avleniya ⁇ letom and ⁇ e ⁇ tsii ⁇ u ⁇ sa on vee ⁇ e ⁇ a ⁇ a ⁇ ⁇ le ⁇ a, ⁇ i vy ⁇ lnenii ⁇ is ⁇ v ⁇ -s ⁇ aea ⁇ elny ⁇ ⁇ e ⁇ atsy and ⁇ sad ⁇ i ve ⁇ toletov on ⁇ sad ⁇ chnye ⁇ l ⁇ schad ⁇ i maly ⁇ ⁇ azme ⁇ v.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)
  • Navigation (AREA)
  • Traffic Control Systems (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)

Abstract

L'invention relève de la navigation d'aéronefs (avions et hélicoptères) et peut être utilisée dans des conditions météo favorables ou compliquées lors du roulement au décollage, du décollage, de la descente et de l'approche. Le système, qui assure la correction automatique du cap et le contrôle visuel des paramètres de vol aux stades indiqués ci-dessus, utilise des données provenant de systèmes de navigation globaux par satellites tels que GPS et Glonass. Ces données provenant d'un récepteur multifonctions arrivent à l'entrée de l'ordinateur de bord; d'autres entrées de cet ordinateur sont reliées à la caméra vidéo embarquée et au panneau de commande du pilote. Les sorties de l'ordinateur de l'ordinateur de bord sont reliées aux entrées du pilote automatique et de l'écran. La partie terrestre du système de l'invention est constituée par les équipements lumineux conventionnels des aéroports ainsi que de puissantes balises lumineuses installées le long de la piste. Ces sont munies d'un système de commande. Le système fournit à l'équipage des informations précises, à jour et facilement visualisables lors des stades du vol les plus complexes.
PCT/RU2000/000340 1999-08-25 2000-08-15 Systeme de navigation integre pour differents types d'aeronefs WO2001020261A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU99119060A RU2182313C2 (ru) 1999-08-25 1999-08-25 Комплексная навигационная система для летательных аппаратов различных классов (варианты)
RU99119060 1999-08-25

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WO2001020261A1 true WO2001020261A1 (fr) 2001-03-22

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105197252A (zh) * 2015-09-17 2015-12-30 武汉理工大学 一种小型无人机降落方法及系统
CN105571585A (zh) * 2014-10-20 2016-05-11 霍尼韦尔国际公司 用于隔离飞行器中姿态故障的系统和方法
CN110088561A (zh) * 2016-12-16 2019-08-02 赛峰电子与防务公司 用于安装在移动载体上的通过恒星重置的目标定位装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011012138A1 (fr) * 2009-07-29 2011-02-03 Shcherbakov Andrei Yurievich Aéronef stratosphérique autonome plus léger que l'air et procédé pour assurer les liaisons radio et optiques, la télédiffusion et le monitorage
RU2598000C1 (ru) * 2015-12-21 2016-09-20 Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" Способ автономной навигации летательных аппаратов

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5136288A (en) * 1989-10-02 1992-08-04 Britec Method and installation for providing alignment guidance to an aircraft in the approach stage
RU2019472C1 (ru) * 1992-07-10 1994-09-15 Дмитрий Анатольевич Сафьян Телевизионная система для руления, взлета и посадки самолетов в сложных метеоусловиях
FR2744800A1 (fr) * 1996-02-09 1997-08-14 Sextant Avionique Procede et dispositif d'aide a la navigation aerienne, avec affichage d'instruments de navigation utilises
US5745863A (en) * 1995-09-22 1998-04-28 Honeywell Inc. Three dimensional lateral displacement display symbology which is conformal to the earth
US5841370A (en) * 1996-09-20 1998-11-24 Lempicke; Thomas A. Method and apparatus for determining aircraft bank angle using satellite navigational signals

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5136288A (en) * 1989-10-02 1992-08-04 Britec Method and installation for providing alignment guidance to an aircraft in the approach stage
RU2019472C1 (ru) * 1992-07-10 1994-09-15 Дмитрий Анатольевич Сафьян Телевизионная система для руления, взлета и посадки самолетов в сложных метеоусловиях
US5745863A (en) * 1995-09-22 1998-04-28 Honeywell Inc. Three dimensional lateral displacement display symbology which is conformal to the earth
FR2744800A1 (fr) * 1996-02-09 1997-08-14 Sextant Avionique Procede et dispositif d'aide a la navigation aerienne, avec affichage d'instruments de navigation utilises
US5841370A (en) * 1996-09-20 1998-11-24 Lempicke; Thomas A. Method and apparatus for determining aircraft bank angle using satellite navigational signals

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105571585A (zh) * 2014-10-20 2016-05-11 霍尼韦尔国际公司 用于隔离飞行器中姿态故障的系统和方法
CN105571585B (zh) * 2014-10-20 2020-11-06 霍尼韦尔国际公司 用于隔离飞行器中姿态故障的系统和方法
CN105197252A (zh) * 2015-09-17 2015-12-30 武汉理工大学 一种小型无人机降落方法及系统
CN110088561A (zh) * 2016-12-16 2019-08-02 赛峰电子与防务公司 用于安装在移动载体上的通过恒星重置的目标定位装置
CN110088561B (zh) * 2016-12-16 2020-04-07 赛峰电子与防务公司 用于安装在移动载体上的通过恒星重置的目标定位装置

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