EP2207003A1 - Système de guidage de missiles - Google Patents

Système de guidage de missiles Download PDF

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Publication number
EP2207003A1
EP2207003A1 EP09250055A EP09250055A EP2207003A1 EP 2207003 A1 EP2207003 A1 EP 2207003A1 EP 09250055 A EP09250055 A EP 09250055A EP 09250055 A EP09250055 A EP 09250055A EP 2207003 A1 EP2207003 A1 EP 2207003A1
Authority
EP
European Patent Office
Prior art keywords
missile
target
data
acquired
control data
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
EP09250055A
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German (de)
English (en)
Inventor
designation of the inventor has not yet been filed The
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.)
MBDA UK Ltd
Original Assignee
MBDA UK Ltd
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 MBDA UK Ltd filed Critical MBDA UK Ltd
Priority to EP09250055A priority Critical patent/EP2207003A1/fr
Priority to PCT/GB2010/050022 priority patent/WO2010079361A1/fr
Priority to EP10700591A priority patent/EP2386052A1/fr
Priority to US12/672,443 priority patent/US8471186B2/en
Publication of EP2207003A1 publication Critical patent/EP2207003A1/fr
Priority to ZA2011/05475A priority patent/ZA201105475B/en
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details

Definitions

  • This invention relates to missile guidance systems particularly but not exclusively to systems of the type known as "command to line of sight” (CLOS).
  • CLOS command to line of sight
  • the tracking of the target and the missile are conducted at the viewing location which often also is the command location.
  • this may be a ground station, a ship, a manned aircraft or another airborne platform such as an unmanned aerial vehicle (UAV).
  • UAV unmanned aerial vehicle
  • the relative angular positions of target and missile are mensurated (measured), and multiplied by the estimated range from sensor to missile to estimate the linear position of the missile with respect to the sightline to the target.
  • Guidance (manoeuvring) commands are then computed in accordance with a suitable control algorithm and transmitted to the missile.
  • This configuration has the advantage that the data sent to the missile are simple, and the resources required on board the missile to process and implement the data are small. This of course is important because the cost of the missile, being an expendable vehicle, has to be minimised.
  • a method of guiding a missile to a target comprises: acquiring, via sensor means at a location remote from the missile, data at least partially indicative of the relative positions of the missile and the target; transmitting the acquired data to the missile; utilising the acquired data on board the missile to generate control data for guiding the missile to the target; and controlling the missile in accordance with the control data to direct it to the target.
  • the acquired data may be transmitted to the missile and used to generate the control data on board the missile.
  • the relative positional data may be transmitted to the missile in a signal which is also transmitted to a command location.
  • the method may comprise receiving the relative positional data at a location (e.g. a surface based or manned airborne command location) remote from the airborne platform, utilising the control data at said location to generate the control data and transmitting the control data to the missile.
  • the control data may be transmitted to the missile via the airborne platform.
  • Preferred embodiments of the invention may comprise utilising the acquired data to mensurate the position of the missile relative to a line of sight from the sensor means to the target and generating the control data to direct the missile onto the said line of sight.
  • the acquired data may be contained in an image acquired by the sensor.
  • Preferably the said data is acquired in a single field of view of the sensor.
  • the method may include launching the missile from the airborne platform.
  • the missile may be launched from a third remote location, and be guided initially by other means into the field of view of the sensor.
  • the method may include sensing radiation from a rearwardly - radiating source on the missile.
  • the radiation source may be an active source.
  • the radiation may be code-modulated, and/or may be controlled in response to data acquired via the sensor.
  • the invention provides a missile guidance system comprising: sensor means configured for acquiring, at a location remote from the missile, data at least partially indicative of the relative positions of the missile and the target, and for transmitting the acquired data to the missile; and data processing means configured for installation on the missile for utilising the acquired data on board the missile to generate control data for guiding the missile to the target,
  • the invention provides a missile guidance system comprising: means, configured for installation on an airborne platform other than the missile, for acquiring data at least partially indicative of the relative position of a missile and a target and for transmitting the acquired data from the airborne platform; data processing means configured for installation other than on the airborne platform for receiving the acquired data, for utilising it to generate control data for guiding the missile to the target.
  • the data processing means may be configured to mensurate the position of the missile relative to a line of sight from the sensor means to the target and to generate the control data to direct the missile on to the said line of sight.
  • the invention also provides a missile having a controller as set forth above and control means responsive to the control data for directing the missile to the target.
  • the missile may have means for directing radiation, preferably code-modulated radiation, rearwardly from the missile.
  • FIG 2 shows the architecture of the missile control system used in Figure 1 .
  • the airborne platform 10 is a UAV.
  • Its sensor 20 is a video camera which acquires an image of the target 12 in its field of view and tracks it by means of a target tracker function 22 in its onboard computer.
  • the UAV also sends the image via an operator data link 24 to a surface command station (e.g. a land vehicle or a ship).
  • the UAV controller at the surface station assesses the target and if appropriate instructs the UAV via the data link to engage it.
  • the UAV launches the missile which in due course enters the field of view of the sensor as described above, and is tracked by missile tracker function 26 in the onboard computer.
  • a rearward facing marker 28 assists the tracker function 28 to acquire this missile.
  • the target and missile tracking data are combined at 30 and further processed at 32 to provide control data (guidance corrections) for the missile.
  • These data in the form of lateral acceleration commands about the pitch and yaw axes of the missile, are transmitted to the missile via a command data link transmitter 34.
  • control data are received in data link receiver 36 and passed to a controller (autopilot) 38, which also receives inputs from on-board inertial sensors (gyros, accelerometers) in an inertial measuring unit 40.
  • controller 38 commands appropriate movements to actuators 42 of the flight control surfaces of the bomb to guide it to its target.
  • the distinction of this implementation is that all the algorithmic processing required for missile guidance is hosted on the missile.
  • the advantage comes from a clarification of responsibilities and a consequent reduction in the integration difficulties.
  • the missile becomes a self contained module, its guidance requiring only an image sequence, and the platform is simplified, becoming merely a provider of the images.
  • the imaging sensor 20 on the UAV acquires the target and sends real-time image data to the command station 44 as before, via data link transmitter 2.
  • the transmitted signal is received also by a data link receiver 46 in the missile, which supplies it to an on-board computer running the target tracker and missile tracker algorithms 22, 26 hitherto implemented on the UAV.
  • the target and missile tracking data are combined at 30 and further processed by the missile's computer to provide control data at 32 which commands the autopilot 38, all as previously described with reference to Figure 2 except that all of the functions are performed on-board the missile.
  • a target tracker 22' is still provided on the UAV so that the operator can require the UAV to track a nominated target before launch of the missile, and maintain the sensor field of view on the target after launch.
  • This tracker however need not be customised to suit the particular missile or missiles covered by the UAV. That said, a more sophisticated approach would be for the UAV to utilise (alternatively or in addition to the tracker 22') a clone of the missile's tracker 22 before launch, and to port its output to the operator 44 via the datalink 24. This will give the operator greater insight into the engagement as it proceeds.
  • the transmission of real-time video image data requires significant bandwidth, but can be achieved using known compression techniques.
  • the signal transmitted by data link transmitter 24 is relatively powerful, in order to reach the command station 44 when the UAV is at its extreme range.
  • the missile launched from the UAV will be relatively much closer to the UAV, and so the data link receiver 46 on the missile can be of much lower sensitivity than the one at the command station.
  • a rearward-looking directional antenna on the missile is provided to receive the datalink signal. This configuration may give some resistance to jamming from jamming sources ahead of the missile.
  • the rearwardly radiating marker 28 is chosen according to the electromagnetic band of the sensor 20. It may be active (e.g. a flare, or other radiation emitting beacon, or the residual heat of a rocket motor if the missile is powered).
  • the beacon 28 may be a pulsed beacon, allowing continuous jammers to be filtered out using ac coupled filters. This of course can still be mimicked in such a way as to mislead the tracking system, by a pulsed jamming system.
  • the best counter-countermeasure (CCM) is for the beacon to be coded in such a way that the jammer cannot mimic.
  • CCM counter-countermeasure
  • the closed loop control of the beacon 28 also allows adaptation to the frame timing (typically 30Hz) of the sensor 20. If the sensor cannot immediately detect the beacon, the missile tracker function 26 in the missile computer progressively shifts the phase of the beacon pulses until the sensor detects the beacon and the tracker locks on to it, in a manner similar to that used to synchronise GPS systems.
  • each missile beacon can be given a different code. Then the UAV can engage several targets simultaneously without requiring additional functionality on the UAV, provided all the targets are within the field of view of the sensor 20.
  • FIG 4 shows another embodiment of the invention. Whilst this embodiment does not integrate all guidance functions on-board the missile, it still results in the UAV being relieved of guidance responsibilities. The UAV thus remains a relatively simple platform requires little modification to add the missile capability
  • the UAV 10 transmits relative positional (video) data 50 to the command location 44, which in this embodiment houses the target tracker 22, missile tracker 26 and control data synthesising functions 30, 32.
  • the control data 52 is transmitted back to the UAV 10 via the uplink between data link terminals 24, 44 and is then relayed via transmitter and receiver 34, 36 ( Figure 2 ) to the missile 16, to guide it to the target.
  • the control data 52 may be transmitted directly to the missile rather than via the UAV. In either case the beacon of the missile is controlled remotely from the command location, but functionally in the same way as described with reference to Figure 3 .
  • the invention also includes any novel features or combinations of features herein disclosed, whether or not specifically claimed.
  • the abstract of the disclosure is repeated here as part of the specification.
  • target and missile tracking data e.g. video image data are acquired on a UAV and transmitted to the missile where they are processed to provide guidance control data to the missile.
  • video image data may be transmitted to a command station where the guidance control data is generated and transmitted to the missile, preferably via the UAV.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP09250055A 2009-01-09 2009-01-09 Système de guidage de missiles Ceased EP2207003A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP09250055A EP2207003A1 (fr) 2009-01-09 2009-01-09 Système de guidage de missiles
PCT/GB2010/050022 WO2010079361A1 (fr) 2009-01-09 2010-01-08 Système de guidage de missile
EP10700591A EP2386052A1 (fr) 2009-01-09 2010-01-08 Système de guidage de missile
US12/672,443 US8471186B2 (en) 2009-01-09 2010-01-08 Missile guidance system
ZA2011/05475A ZA201105475B (en) 2009-01-09 2011-07-25 Missile guidance system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09250055A EP2207003A1 (fr) 2009-01-09 2009-01-09 Système de guidage de missiles

Publications (1)

Publication Number Publication Date
EP2207003A1 true EP2207003A1 (fr) 2010-07-14

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EP09250055A Ceased EP2207003A1 (fr) 2009-01-09 2009-01-09 Système de guidage de missiles

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EP (1) EP2207003A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105425819A (zh) * 2015-11-25 2016-03-23 南京航空航天大学 一种无人机自动跟踪地面目标的制导方法
CN109885101A (zh) * 2019-01-04 2019-06-14 北京测威科技有限公司 一种利用无人飞行器模拟导弹末制导的方法及系统

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3876308A (en) * 1971-05-24 1975-04-08 Us Navy Automatic command guidance system using optical trackers
US4220296A (en) * 1976-11-03 1980-09-02 Licentia Patent-Verwaltungs-G.M.B.H Method for guiding the final phase of ballistic missiles
US4267562A (en) * 1977-10-18 1981-05-12 The United States Of America As Represented By The Secretary Of The Army Method of autonomous target acquisition
US5114227A (en) * 1987-05-14 1992-05-19 Loral Aerospace Corp. Laser targeting system
US20020154293A1 (en) * 2001-04-19 2002-10-24 Wells Michael L. Solid state modulated beacon tracking system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3876308A (en) * 1971-05-24 1975-04-08 Us Navy Automatic command guidance system using optical trackers
US4220296A (en) * 1976-11-03 1980-09-02 Licentia Patent-Verwaltungs-G.M.B.H Method for guiding the final phase of ballistic missiles
US4267562A (en) * 1977-10-18 1981-05-12 The United States Of America As Represented By The Secretary Of The Army Method of autonomous target acquisition
US5114227A (en) * 1987-05-14 1992-05-19 Loral Aerospace Corp. Laser targeting system
US20020154293A1 (en) * 2001-04-19 2002-10-24 Wells Michael L. Solid state modulated beacon tracking system

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105425819A (zh) * 2015-11-25 2016-03-23 南京航空航天大学 一种无人机自动跟踪地面目标的制导方法
CN105425819B (zh) * 2015-11-25 2019-01-11 南京航空航天大学 一种无人机自动跟踪地面目标的制导方法
CN109885101A (zh) * 2019-01-04 2019-06-14 北京测威科技有限公司 一种利用无人飞行器模拟导弹末制导的方法及系统
CN109885101B (zh) * 2019-01-04 2022-02-22 北京测威科技有限公司 一种利用无人飞行器模拟导弹末制导的方法及系统

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