WO2001002875A2 - Systeme et procede de localisation et de positionnement d'objets dans un espace libre - Google Patents

Systeme et procede de localisation et de positionnement d'objets dans un espace libre Download PDF

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Publication number
WO2001002875A2
WO2001002875A2 PCT/US2000/016720 US0016720W WO0102875A2 WO 2001002875 A2 WO2001002875 A2 WO 2001002875A2 US 0016720 W US0016720 W US 0016720W WO 0102875 A2 WO0102875 A2 WO 0102875A2
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WO
WIPO (PCT)
Prior art keywords
aircraft
reference point
pseudo
tanker
board
Prior art date
Application number
PCT/US2000/016720
Other languages
English (en)
Other versions
WO2001002875A3 (fr
Inventor
Sheng T. Wang
Original Assignee
Lockheed Martin Corporation
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 Lockheed Martin Corporation filed Critical Lockheed Martin Corporation
Priority to AU11863/01A priority Critical patent/AU1186301A/en
Publication of WO2001002875A2 publication Critical patent/WO2001002875A2/fr
Publication of WO2001002875A3 publication Critical patent/WO2001002875A3/fr

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/02—Systems using the reflection of electromagnetic waves other than radio waves
    • G01S17/06—Systems determining position data of a target
    • G01S17/42—Simultaneous measurement of distance and other co-ordinates
    • 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
    • B64D39/00—Refuelling during flight
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/14—Receivers specially adapted for specific applications
    • G01S19/18—Military applications
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
    • G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/42—Determining position
    • G01S19/51—Relative positioning
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S5/00—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations
    • G01S5/0009—Transmission of position information to remote stations
    • G01S5/0072—Transmission between mobile stations, e.g. anti-collision systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/003—Transmission of data between radar, sonar or lidar systems and remote stations
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/88—Lidar systems specially adapted for specific applications
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/88—Lidar systems specially adapted for specific applications
    • G01S17/93—Lidar systems specially adapted for specific applications for anti-collision purposes
    • G01S17/933—Lidar systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft

Definitions

  • the present invention relates generally to locating and maintaining objects in free space, and more particularly to systems and methods for locating and maintaining objects in free space using laser radar (LADAR) and pseudo-relative GPS.
  • LADAR laser radar
  • pseudo-relative GPS pseudo-relative GPS
  • GPS Global Position Systems
  • SATCOM Satellite Communications
  • the refueling procedure takes place between a tanker aircraft and a receiving aircraft under various conditions.
  • mid-air refueling involves the use of a fuel line in the form of a boom extending downwards and away from the tanker aircraft.
  • the boom can be controlled from within the tanker to aid in coupling it to the receiving aircraft.
  • a coupling mechanism can connect the boom to a refuel receptacle on the receiving aircraft.
  • the receiving aircraft Prior to establishing a suitable position for receiving fuel from the tanker, the receiving aircraft must first locate the tanker by employing radar, GPS, and/or SATCOM.
  • the 'refueling envelope' is defined as the volume of space behind the tanker within which the refueling boom can physically be maneuvered.
  • the receiver aircraft must rely on visual contact with the tanker from a point of several hundred yards to properly position the aircraft within the 'refueling envelope' .
  • the boom operator and receiving aircraft pilot are required to quickly, yet precisely, couple and maintain the tanker and receiving aircraft during refueling. This task becomes even more difficult during night refueling when excess light is used to flood the fuel receptacle on the receiving aircraft.
  • the present invention provides a system and method for precisely locating and maintaining two bodies in space that substantially eliminates or reduces disadvantages and problems associated with previously developed systems and methods used for precisely locating and maintaining two bodies in space.
  • a first broad aspect of the present invention provides a method for locating a first body with reference to at least one second body in free space.
  • the system for locating and maintaining objects in free space includes determining the distance between a reference point on the first body and at least one reference point on at least one second body using laser radar (LADAR) .
  • the method further includes maintaining the desired distance between the first body and at least one second body. This desired distance is achieved by translating the first body or the at least one second body.
  • An additional embodiment of the first broad aspect of the present invention includes the case in which the first body is a tanker aircraft and the at least one second body is a receiving aircraft to be refueled.
  • the tanker may include a boom which is used to interface with a fuel receptacle on the receiving aircraft.
  • An additional embodiment of the first broad aspect of the present invention further comprises the case where the first body is a lead aircraft and the at least one second aircraft is at least one aircraft flying in formation relative to the lead aircraft.
  • a second broad aspect of the present invention provides a method for locating a first body with reference to at least one second body in free space. This method further comprises determining the vector between the first body and at least one second body. In addition, this method includes a pseudo-relative GPS system to achieve and maintain the desired distance between the first body and at least one second body. This desired distance is achieved and maintained by translating the first body or the at least one second body.
  • An additional embodiment of the second broad aspect of the present invention includes the case where the first body is a tanker aircraft and the at least one second body is an aircraft to be refueled.
  • the tanker aircraft further comprises a boom which is used to interface with a fuel receptacle on the receiving aircraft.
  • Another embodiment of the second broad aspect of the present invention includes the situation in which the first body is a lead aircraft in a formation and the at least one second body is at least one aircraft being guided by the lead aircraft in the formation.
  • Still another embodiment of the third broad aspect of the present invention includes the case in which the first body is an aircraft and the second body is a ground target.
  • a third body enables precise location of the target and transmits the information to the first body.
  • One technical advantage of the present invention is that it is stealthy.
  • the laser technology being implemented emits extremely low energy radiation. This low energy radiation is not detectable by detection equipment on other aircraft or on the ground.
  • Another technical advantage of the present invention is that it is eye-safe.
  • the power level of the laser is extremely low and is not harmful to the human eye. This is particularly important for refueling situations where the pilot may be exposed to the laser from the tanker plane .
  • Still yet another technical advantage of the present invention is that the pseudo-relative GPS system is not jammable.
  • Pseudo-relative GPS implements encrypted digital data and frequency hopping which is not jammable.
  • Another technical advantage is that the laser technology is extremely precise down to centimeters and it can be continuously updated. Due to its precision, this allows for quick refueling of aircraft which, in turn, results in reduced cost.
  • Yet another technical advantage of the present invention is quick and accurate location of a ground target. Precision targeting reduces the potential for unwanted collateral damage, as well as the costs associated with retargeting due to errors. Most importantly, the present invention provides a safer solution than the prior art methods for mid-air refueling of aircraft and formation flying. This reduces the risk of an accident which in turn reduces potential human and monetary losses.
  • FIGURE 1 is one embodiment of the first broad aspect of the present invention.
  • FIGURE 2 is another embodiment of the first broad aspect of the present invention.
  • FIGURE 3 is one embodiment of the second broad aspect of the present invention.
  • FIGURE 4 is another embodiment of the second broad aspect of the present invention
  • FIGURE 5 is another embodiment of the second broad aspect of the present invention in which the first body
  • FIGURE 6 is another embodiment of the second broad aspect of the present invention.
  • FIGURE 7 is another embodiment of the second broad aspect of the present invention.
  • FIGURES Preferred embodiments of the present invention are illustrated in the FIGURES, like numerals being used to refer to like and corresponding parts of the various drawings .
  • the present invention provides a system and method for locating and maintaining two bodies in space.
  • laser radar LADAR
  • Computer controlled navigation on board either body may use the information provided by the LADAR to achieve and maintain the two bodies at a desired distance.
  • pseudo-relative GPS data may be used as a navigational tool. Based on the displacement of the two bodies, digital radio transmits the displacement data as well as GPS data from one transmitting body to a receiving body. This enables the use of the pseudo-relative GPS data as a navigational tool for the receiving body.
  • FIGURE 1 represents an embodiment of the first broad aspect of the present invention.
  • a receiving aircraft 20 is to be refueled by a tanker 10.
  • the tanker 10 may include a fuel line 14 with a drogue 16 that interfaces with a probe 18 on the receiving aircraft 20.
  • the probe 18 is a fuel receptacle.
  • LADAR 12 may be on board the tanker 10. The LADAR 12 determines the range difference between the tanker drogue 16 and the receiving aircraft probe 18 by image returns from laser reflection. The distance between the drogue 16 and the probe 18 is labeled as R 3 in FIGURE 1.
  • the range difference R 3 may be determined by laser reflective markings 22, 24 previously established on the drogue 16 and probe 18 or by images stored in a memory data bank in the LADAR unit 12.
  • the laser reflecting material 22, 24 may be marked at an established offset point so that it will always be visible by the LADAR 12 when the probe 18 and drogue 16 are approaching one another.
  • the distance between the LADAR 12 and the probe 18 is denoted as R 2 on FIGURE 1, while the distance between the LADAR 12 and the drogue 16 is denoted as R x .
  • the LADAR 12 uses the vectors R ⁇ and R 2 for the drogue 16 and probe 18 to arrive at the connecting range R 3 .
  • the LADAR 12 may provide the vectors R 1 and R 2 to on-board software on the tanker 10 such that the drogue 16 can be controlled and guided to the probe 18.
  • the tanker 10 may communicate vector data R- L and R 2 to on-board software on the receiving aircraft 20 so that the drogue 16 may be kept stationary while the probe 18 is guided to the drogue 16.
  • This communication may be performed via a pseudo-relative GPS system.
  • a pseudo-relative GPS system may include on-board digital radios, computer-controlled navigation equipment, and a GPS.
  • FIGURE 2 represents a second embodiment of the first broad aspect of the present invention.
  • a lead aircraft 26 may be equipped with LADAR 12 can determine the range between the lead aircraft 26 and one or more subordinate aircraft 28 flying in formation. The ranges are denoted as R 1 ,R 2 ...,R N in FIGURE 2.
  • the subordinate aircraft 28 may or may not have a reflective material that enhances the laser reflection sensed by the LADAR 12.
  • the range information can be processed by software on board the lead aircraft 26 so that the lead aircraft 26 can alter its position relative to the subordinate aircraft 28. Alternatively, the range information and coordinate and speed information for the lead aircraft 26 may be transmitted to the subordinate aircraft 28.
  • FIGURE 3 represents one embodiment of the second broad aspect of the present invention in which pseudo- relative GPS is used to refuel an aircraft 20 by a tanker 10.
  • the aircraft 20 may require the following on-board equipment : a LADAR that contains any USA or other refueling tanker's perpendicular tailplane image profile in its memory and that is capable of doing ranging, a digital radio that is interfaced digitally with navigation software, and a GPS that is also linked digitally to the navigation software.
  • the tanker 10 may also be GPS capable and carry a digital radio.
  • the receiving aircraft 20 may approach the tanker 10 at approximately one nautical mile behind the tanker 10 using GPS or using ground direction.
  • the aircraft 20 may implement the LADAR and then use the LADAR to fly to the tanker's perpendicular tailplane position.
  • the aircraft 20 can then determine the exact range, labeled as "D" in FIGURE 1, to the tanker's tailplane using the LADAR.
  • the aircraft 20 can relate the range "D" information to the tanker 10 using the digital radio on board the aircraft 20.
  • the tanker 10 can communicate back to the aircraft 20 at a 25 Hz rate with the tanker's GPS data merged with the range "D" information provided by the aircraft 20.
  • the pseudo-relative GPS data 32 may include X,Y,Z coordinates of the tanker 10, distance "D" between tanker 10 and aircraft 20, velocity of the tanker 10, and current time.
  • the pseudo-relative GPS data 32 may change dynamically and is refreshed at a 25 Hz rate.
  • This pseudo-relative GPS data 32 may become the receiving aircraft's GPS and navigation aid data.
  • the tanker 10 may continue to transmit the digital pseudo-relative GPS 32 at a 25 Hz rate to the aircraft 20 and to monitor the aircraft's position.
  • the tanker 10 may guide the aircraft 20 to either a drogue or a boom for refueling, or to other positions relative to the tanker 10.
  • FIGURE 4 represents another embodiment of the second broad aspect of the present invention.
  • This embodiment includes a lead aircraft 26 with at least one subordinate aircraft 28 flying in formation.
  • the subordinate aircraft 28 may have the following on-board equipment: a LADAR that contains any USA or other lead aircraft's perpendicular tail image profile in memory, a digital radio that may be interfaced digitally with navigation software, and a GPS that is also linked with navigation software.
  • the lead aircraft 26 may also contain GPS data and a digital radio which may be linked with the lead's navigational software.
  • the subordinate aircraft 28 may approach the lead aircraft 26 at approximately one nautical mile behind the lead aircraft 26.
  • the subordinate aircraft 28 may implement LADAR to determine the range between the lead aircraft 26 and the subordinate aircraft 28.
  • the subordinate aircraft 28 may implement digital radio to transmit the ranges to the lead aircraft 26.
  • the lead aircraft 26 may merge the range data with the GPS data of the lead aircraft 26 and transmit this back to the subordinate aircraft 28 via digital radio.
  • This data, the pseudo-relative GPS data 32 can then be used by the subordinate aircraft 28 as GPS data for navigation.
  • FIGURE 5 represents another embodiment of the second broad aspect of the present invention.
  • the tanker 10 may possess LADAR which determines the relative position of the aircraft 20 by obtaining the range "R" between the two aircraft via laser reflection.
  • the tanker's GPS coordinates (X,Y,Z) may be added to the range vector "R" to arrive at the relative position of the aircraft 20.
  • This pseudo-relative GPS data (X',Y',Z',R) is then transmitted to the aircraft 20 via digital radio on board the tanker 10.
  • This pseudo- relative GPS data 32 can be used as GPS data for navigation for the aircraft 20.
  • FIGURE 6 represents another embodiment of the second broad aspect of the present invention.
  • a lead aircraft 26 may include LADAR 12 which determines the relative position of one or more subordinate aircraft 28 by obtaining the ranges R 1 ,R 2 ,...R N between the subordinate aircraft 28 and the lead aircraft 26.
  • the lead aircraft's GPS coordinates (X,Y,Z) are added to the range vectors R1, E2 , ...R N to arrive at the relative positions of the subordinate aircraft 28.
  • pseudo-relative GPS data 32 may be transmitted to each subordinate aircraft 28 via digital radio on board the lead aircraft 26.
  • the pseudo-relative GPS data 32 can be used as GPS data for navigational purposes for each of the subordinate aircraft 28.
  • FIGURE 7 represents another embodiment of the second broad aspect of the present invention.
  • This embodiment may consist of three bodies: a first body represented as the aircraft 34, a second body represented as a target 36, and a third body represented as a ground figure 38.
  • the ground figure 38 may possess LADAR 12, as well as a digital radio and known GPS coordinates.
  • the ground figure 38 may approach the target 36 within approximately one mile.
  • the ground figure may implement the LADAR 12 to determine the range "R" between the ground figure 38 and the target 36.
  • the ground figure 38 can transmit "R" along with the figure's GPS data 40 to the first body 34.
  • An on-board digital radio of the aircraft may pass the pseudo-relative GPS data 42 to the on-board navigational software.
  • the software in turn, can determine the range "D" between the aircraft 34 and the target 36 from the pseudo-relative GPS data 42.
  • the range D can then be used in conjunction with on-board computer-controlled navigation and targeting equipment to enable the aircraft 34 to perform precise bombing of ground target 36.
  • An important technical advantage of the present invention is that it is stealthy.
  • the LADAR 12 being implemented emits extremely low energy radiation and after a distance of approximately one mile this energy is absorbed by the atmosphere and can no longer be detected. Therefore the LADAR 12 does not increase the danger of detection from ground equipment or other aircraft .
  • Another technical advantage provided by the present invention is that it is eye-safe. As discussed above, the power level of the laser included in the LADAR equipment 12 is extremely low. At this energy level, the laser is not harmful to the human eye. This is particularly important for situations of refueling where a pilot on a refueling aircraft 20 may be exposed to the laser from the tanker plane 10.
  • Still yet another technical advantage of the present invention is that the pseudo-relative GPS system is not jammable.
  • Pseudo-relative GPS implements encrypted digital data and frequency hopping. Therefore, when a first body 10, 26 is transmitting and receiving data from a second body 20, 28 the data 32 can be retained during transmission and not distorted or altered by large broadband noise signals used to jam aircraft communications in a hostile environment.
  • the LADAR 12 provides a technology that is precise down to centimeters. This, in turn, reduces the dangers and costs associated with mid-air refueling and formation flying. This precision allows for a more accurate location and control of a tanker drogue 16 and a receiving probe 18 when trying to refuel an aircraft 20.
  • the addition of reflective material 22, 24 can enhance laser reflection to the LADAR 12. Continuously updating the LADAR data at a rate of 25 Hz enables computer controlled navigation systems on board the tanker 10 and the receiving aircraft 20 to continuously control their movement relative to each other.
  • Yet another technical advantage of the present invention is the use of the LADAR 12 to perform more precise bombing of ground targets 36.
  • the LADAR 12 enables the ground figure 38 to transmit the location data 42 to the aircraft 34.
  • the ground figure 38 needs to be within approximately one mile of the target 36, the aircraft 34 needs only to be within range of the ground figure's digital radio.
  • the aircraft 34 may fly further from ground fire or detection, yet still aid ground forces in the task of strategic bombing.
  • LADAR LADAR
  • the present invention provides a safer solution than the prior art methods for mid-air refueling of aircraft and formation flying.
  • the reduced risk associated with the solution also reduces potential costs.
  • the present invention provides a method for precise bombing of strategic targets while reducing the risk of damage to the aircraft and the risk of unwanted collateral damage.

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • General Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Abstract

L'invention concerne un système et un procédé de localisation et de positionnement de deux objets dans l'espace. Dans un premier aspect général de la présente invention, un LADAR (radar à laser) est mis en oeuvre de manière à déterminer la distance séparant les deux objets. La navigation commandée par ordinateur à bord de chaque objet peut utiliser les informations fournies par LADAR pour réaliser une distance désirée entre les deux objets et la maintenir. Dans un deuxième aspect de la présente invention, des données GPS pseudo-relatives peuvent être utilisées comme outil de navigation. En fonction du déplacement des deux objets, une radio numérique émet les données de déplacement, ainsi que les données GPS à partir d'un objet émetteur vers un objet récepteur. Ceci permet à l'objet récepteur d'utiliser les données GPS pseudo-relatives comme outil de navigation.
PCT/US2000/016720 1999-06-21 2000-06-19 Systeme et procede de localisation et de positionnement d'objets dans un espace libre WO2001002875A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU11863/01A AU1186301A (en) 1999-06-21 2000-06-19 System and method for locating and maintaining objects in free space

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US33739499A 1999-06-21 1999-06-21
US09/337,394 1999-06-21

Publications (2)

Publication Number Publication Date
WO2001002875A2 true WO2001002875A2 (fr) 2001-01-11
WO2001002875A3 WO2001002875A3 (fr) 2001-05-03

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Cited By (12)

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FR2825815A1 (fr) * 2001-06-08 2002-12-13 Thales Sa Procede de gestion du ravitaillement en vol d'une flotille d'aeronefs
ITTV20090116A1 (it) * 2009-06-04 2010-12-05 Galileo Avionica Spa Sistema di rifornimento assistito in volo
EP2363731A1 (fr) * 2010-02-25 2011-09-07 Hitachi Ltd. Système d'évaluation d'emplacement
JP2013173523A (ja) * 2012-02-27 2013-09-05 Ge Aviation Systems Llc 相対ナビゲーションシステムによって支援された編隊飛行のための方法
EP2933656A1 (fr) * 2014-04-14 2015-10-21 The Boeing Company Systèmes et procédés de positionnement aérien
ES2584231A1 (es) * 2015-10-09 2016-09-26 Defensya Ingeniería Internacional, S.L. Sistema de localización del extremo del boom, de la boca del receptáculo de repostaje y del tanquero
EP3093241A1 (fr) * 2015-05-11 2016-11-16 BAE Systems PLC Système et procédé de couplage d'aéronef
ES2603430A1 (es) * 2016-04-18 2017-02-27 Defensya Ingeniería Internacional, S.L. Sistema de detección y procedimiento de contacto de punta del botalón volador y boca del receptáculo para operaciones de repostaje aéreo con botalón
US10732648B2 (en) 2015-05-11 2020-08-04 Bae Systems Plc Aircraft coupling method and system
CN114543664A (zh) * 2021-12-30 2022-05-27 中国航空工业集团公司沈阳飞机设计研究所 一种基于激光扫描的加油锥套定位方法及装置
US12077314B1 (en) 2021-04-08 2024-09-03 Onstation Corporation Transforming aircraft using low-cost attritable aircraft modified with adaptive suites
US12077313B1 (en) 2021-05-28 2024-09-03 Onstation Corporation Low-cost attritable aircraft modified with adaptive suites

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GB2237251A (en) * 1989-10-27 1991-05-01 Plessey Co Plc In-flight refueling apparatus
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US3917196A (en) * 1974-02-11 1975-11-04 Boeing Co Apparatus suitable for use in orienting aircraft flight for refueling or other purposes
FR2632755A1 (fr) * 1988-06-08 1989-12-15 Thomson Csf Systeme d'aide au deplacement de mobiles en formation groupee
US4949089A (en) * 1989-08-24 1990-08-14 General Dynamics Corporation Portable target locator system
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Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2002101685A1 (fr) * 2001-06-08 2002-12-19 Thales Procede de gestion du ravitaillement en vol d'une flotille d'aeronefs
US6832743B2 (en) 2001-06-08 2004-12-21 Thales Method for managing in-flight refuelling of a fleet of aircraft
FR2825815A1 (fr) * 2001-06-08 2002-12-13 Thales Sa Procede de gestion du ravitaillement en vol d'une flotille d'aeronefs
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