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
  • F41G7/303—Sighting or tracking devices especially provided for simultaneous observation of the target and of the missile
• • 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
  • F41G7/306—Details for transmitting guidance signals
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F42—AMMUNITION; BLASTING
  • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
  • F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
  • F42B19/01—Steering control
  • F42B19/10—Steering control remotely controlled, e.g. by sonic or radio control

Definitions

• the present invention relates to a method and a device for firing on fixed targets, mobile or temporarily fixed and mobile.
• an aircraft flies over the ground to search for targets on the ground.
• the radar of the aircraft is used in different modes, either in SAR mode (Synthetic Aperture Radar) producing ground imagery by the known synthetic antenna method for the search of fixed targets, or in GMTI (Ground Moving Target Indicator) for the search for moving ground targets.
• SAR mode Synthetic Aperture Radar
• GMTI Green Moving Target Indicator
• FIG. 1a shows a detection scenario for a C-tank (target) by an aircraft A carrying a weapon 10.
• the radar R of the aircraft sweeps the presumed zone Z for positioning the tank to detect it.
• the coordinates of the target C are transferred to the weapon 10 which detaches from the aircraft to strike target.
• Figures 1b and 1c show two configurations of firing by an aircraft using two different types of weapons.
• FIG. 1b shows a first configuration using the weapon 10, for example a missile equipped with means, such as for example a homing device 12, enabling it to guide itself to the target C.
• the weapon is said to be self-guided.
• the radar R of the aircraft (carrier of the weapon 10) supplied to the initial coordinates of the target C weapon.
• the weapon 12 homing device 10 is activated refining or constantly correcting the coordinates of the target as and when measure his flight and direct the weapon towards the target that can be fixed or on the move.
• the initial coordinates supplied to the weapon 10 by the radar R of the aircraft A have little or no influence on the accuracy of the firing when the target C is in the search domain of the homing device of the aircraft. weapon, when activated.
• the disadvantage of such a self-directed weapon is its high cost due to the device for detecting and refreshing the coordinates of the target.
• FIG. 1c shows a second firing configuration using another weapon 16, which is less expensive than that of the first configuration.
• This other weapon 16 is provided only with guidance means from the initial coordinates of the target C provided by the radar R of the aircraft A and the coordinates of the weapon 16 provided, for example, by a GPS receiver of the weapon 16.
• the initial coordinates provided by the radar R of the aircraft and the quality of the navigation of the weapon 16 directly affect the accuracy of the shot.
• some weapons especially for air targets have data links that refresh the coordinates of the target.
• the aircraft transmits to the weapon, using the data link, new coordinates refreshes of the target from its radar detection and this during all or part of the flight time of the weapon.
• the accuracy of the measurement of the coordinates transmitted to the weapon is in this case related to the precision of detection of the target by the radar of the aircraft, generally insufficient to guide the weapon on the target.
• the state of the art then consists in, as in the first configuration, to equip the weapon with a homing device.
• the invention proposes a device for firing a weapon on at least one target, by an aircraft carrying the weapon, using a method with a detection mode for unambiguous broadband pulse Doppler radar for the detection and location of the targets, characterized in that it comprises at least one detection means operating on said Doppler radar detection mode locating both the weapon and the target in the same frame, with the same geometry.
• the detection mode for Doppler radar is configured so that the location of the weapon and the target is seen by the detection means in said same frame, with said same geometry.
• the fire control device includes a data link with the weapon to provide guidance information to the target.
• the device comprises several detection means cooperating together to improve the accuracy of the shot.
• the detection means are radars.
• the device comprises a plurality of radars cooperating together, making measurements distance from the target by transmitting at least one radar signal and receiving the respective radar echoes according to different radar positions relative to the target.
• a first set of N radars transmits detection signals and a second set of M radars receives the echoes of the detection signals emitted by the N radars, these
• N radars emitting the signals being, either in part or in whole chosen among the M radars receiving the echoes, or radars different from the M radars receiving the echoes.
• a single radar in a discrete mode of fire control comprising several radars cooperating together, a single radar emits a detection signal while remaining at a safe distance.
• the data link is a radio frequency link.
• the radio frequency link includes a radiofrequency transmitter on the carrier and a radio frequency receiver on the weapon.
• the invention in an example of an air / ground firing configuration of a weapon by an aircraft essentially consists of combining: a radar mode, mono or multicarrier, simultaneously locating the target and the weapon, this mode allowing detect and locate fixed or mobile targets regardless of their speed
• a main objective of the firing device according to the invention is its application to low-cost weapons while achieving superior firing efficiency. Another objective is to obtain an operational capability for moving targets through intelligent use of means intended for fixed targets.
• Another goal is to improve the performance of weapons with a homing device and identical performance lower their cost.
• FIG. 1a already described, shows a scenario of detection of a tank (target) by an aircraft carrying a weapon
• FIGS. 1b and 1c already described, show two firing configurations by an aircraft using two different types of weapons
• FIG. 2 shows a first fire control device according to the invention
• FIG. 3 shows a second fire control device, according to the invention, with improved shooting accuracy and; - Figure 4 shows a third fire control device according to the invention with discretion shooting control.
• FIG. 2 shows a first fire control device according to the invention.
• the weapon is for example a missile 30 carried by an aircraft A and the target a tank C.
• the tank may be stationary, on the move, or stationary for some periods of time and moving during other periods of time, the tank may change direction and speed while moving.
• the missile 30 and the aircraft A comprise a radio link 32 for transmitting information guiding the weapon by the aircraft.
• the aircraft A comprises a radio transmitter 34 and the missile a receiver 36.
• the accuracy of detection of the coordinates of the tank C by the radar R of the aircraft A which will be transmitted to the missile 30 is essential for the effectiveness of the shot.
• the detection and location mode of the radar R of the aircraft is such that it ensures a vision of both the tank C and the missile 30, in the same frame, with the same geometry.
• the location errors of the missile 30 and the tank C will therefore be common and in particular the propagation errors of the radar signals. These errors will be weaker as the missile approaches the tank.
• the radar R of the aircraft A can therefore measure, in real time, the trajectory error of the missile 30 with respect to the tank C and transmit it as a course correction via the data link 32 of the aircraft A worm missile 30.
• the aircraft A embeds a device for detecting and locating targets using an unambiguous broadband pulse Doppler radar method. based on distance migration compensation prior to Doppler analysis, for each velocity assumption. Such a method and the device for implementing the method are described in detail in French Patent No. 96 08509. This method ensures both the location of the weapon and the target.
• French Patent No. 96 08509 is a method for detecting targets for a low-frequency repetition and high-resolution wide range unambiguous pulsed Doppler pulse radar in which a burst of N is emitted. coherent pulses, the distance resolution ⁇ R, the period of recurrence of the pulses and the duration of the burst being such that there is a distance migration greater than a range distance of width ⁇ R for a target having a speed equal to the ambiguous speed radar, said method comprising the steps of:
• a degraded fire control may consist of using a radar mode of detection of moving targets provided that this detection mode always detects and locates both the target and the weapon. Nevertheless, the mode recommended above using an unambiguous impulse Doppler radar method and broadband remains preferable to overcome the case where the target stops during the flight of the weapon.
• the target location accuracy of the target by the radar of the aircraft is mediocre because this accuracy is derived from the angular measurements made by the radar.
• the accuracy of the firing device can be improved by cooperating two radars.
• FIG. 3 shows a second fire control device according to the invention, with improved shooting accuracy.
• the second fire control device according to the invention comprises two aircraft, a first aircraft A1 and a second aircraft A2 each equipped with a respective radar R1, R2.
• Each of the radars R1, R2 of the two aircraft makes measurements distance from the target by the emission of respective radar signals Sd1, Sd2 and the reception of the respective radar echoes Ed1, Ed2 at different positions relative to the target C.
• radars R1, R2 of the two aircraft A1, A2 cooperate with each other.
• the device comprising the two aircraft provided, in a known manner, coordinates of the target having an improved location accuracy in relation to that which would be obtained with a single radar.
• FIG. 4 shows a third fire control device, according to the invention, with discretion of fire control.
• the fire control device of FIG. 3 comprises the first A1 and the second A2 aircraft, each having a respective radar R1, R2 operating in so-called "multistatic" mode.
• the radar R1 of the first aircraft A1 emits a signal Sd1 to detect the target
• the radars R1, R2 of the two aircraft A1, A2 respectively receiving the echoes Ed1 and Ed2 to determine the coordinates of the target.
• a radio link 50 between the two aircraft A1, A2 makes it possible, as has been specified above, to determine, by the detection measurements of the two radars R1, R2, the target coordinates with greater precision than that which can be obtained with a single radar.
• the aircraft A1 comprising the radar R1 emitting the detection signal Sd 1 may be at a great distance from the target, out of reach of possible responses triggered by the detection of their presence.
• the other aircraft A2 totally silent receiving only echo Ed2 can be closer to the target and possibly be the carrier of the weapon.
• the device can be generalized to N radars that emit and M radars that receive.
• a first set of N radars transmits detection signals and a second set of M radars receives the echoes of the detection signals emitted by the N radar. program.
• These N radars emitting the signals being, in part or in whole, chosen from the M radars receiving the echoes, or radars different from the M radars receiving the echoes. In the latter case the device comprises M + N radars.
• the fire control device according to the invention is not limited to the examples described with aircraft comprising radars and ground targets, but can be extended to aerial targets, space targets and other types of carriers and means. lidar type detection, optronic.
• the fire control device has the advantage of being able to use low-cost weapons while obtaining the shooting efficiencies of more expensive and complex weapons. Another advantage of this device is that it improves the performance and success of the more sophisticated weapons firing, for example, a missile with a homing device.
• a weapon with a self-steering usually needs to be equipped with a scanning antenna, mechanical or electronic, to scan an area wide enough to detect the target.
• the firing device improves the performance and reduces the cost of such a weapon which can simply be equipped with a fixed antenna from the moment when the angular error of designation of the target is smaller than the angular opening of the homing device.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• General Engineering & Computer Science (AREA)
• Radar Systems Or Details Thereof (AREA)
• Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=40029109

Family Applications (1)

Country Status (3)

Citations (4)

Family Cites Families (8)

• 2008
  • 2008-03-07 FR FR0801272A patent/FR2928452B1/fr active Active
• 2009
  • 2009-03-05 EP EP09719737A patent/EP2255148A2/de not_active Withdrawn
  • 2009-03-05 WO PCT/EP2009/052609 patent/WO2009112424A2/fr not_active Ceased

Patent Citations (4)

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