EP0809084A1 - Vorrichtung zur Rollwinkelbestimmung eines Flugkörpers, insbesondere einer Munition - Google Patents

Vorrichtung zur Rollwinkelbestimmung eines Flugkörpers, insbesondere einer Munition Download PDF

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Publication number
EP0809084A1
EP0809084A1 EP97401026A EP97401026A EP0809084A1 EP 0809084 A1 EP0809084 A1 EP 0809084A1 EP 97401026 A EP97401026 A EP 97401026A EP 97401026 A EP97401026 A EP 97401026A EP 0809084 A1 EP0809084 A1 EP 0809084A1
Authority
EP
European Patent Office
Prior art keywords
antenna
gps
ground
vector
plane
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.)
Granted
Application number
EP97401026A
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English (en)
French (fr)
Other versions
EP0809084B1 (de
Inventor
Jean-Paul Thomson-CSF SCPI Labroche
Charles Thomson-CSF SCPI Dussurgey
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.)
TDA Armements SAS
Thales Avionics SAS
Original Assignee
TDA Armements SAS
Thales Avionics SAS
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Publication date
Application filed by TDA Armements SAS, Thales Avionics SAS filed Critical TDA Armements SAS
Publication of EP0809084A1 publication Critical patent/EP0809084A1/de
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Publication of EP0809084B1 publication Critical patent/EP0809084B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F41G7/305—Details for spin-stabilized missiles

Definitions

  • the invention relates to a device for determining the roll orientation of a flying object, for example of ammunition. It applies in particular to the improvement of the effectiveness of artillery ammunition especially in the context of munitions with increased range.
  • Improving the effectiveness of artillery ammunition notably involves reducing the dispersion of their point of impact on the ground.
  • a known method currently for reducing the imprecision of impact, consists notably in correcting the pointing angles of the tube, on the basis of information provided by advanced observers on the actual impact points of first projected munitions. There then remains in the dispersion, in addition to the error of appreciation of the observers, only the random part specific to each projectile and due to atmospheric turbulence.
  • the object of the invention is to determine the orientation in particular of a munition with respect to a terrestrial reference, for example the vertical plane.
  • the angle of orientation thus defined is similar in fact to the roll angle of the munition.
  • the main advantages of the invention are that it allows the correction of trajectories in range and lateral without additional equipment of the vertical detector type on board the munition, that it allows trajectory correction calculations carried out on the ground, that it is simple to implement and is economical in particular insofar as it does not require a complete system on board in ammunition or any other flying vehicle.
  • FIG. 1 shows an example of the difference between a theoretical trajectory 1 and an actual trajectory 2 of an ammunition.
  • the actual impact point Ir has a deviation ⁇ x in range and ⁇ y laterally from the theoretical impact point I t .
  • the orders of magnitude of the deviations ⁇ x and ⁇ y are respectively 200m and 120m.
  • ⁇ y represents a deviation from the vertical plane 3 of the theoretical trajectory.
  • the correction of the real trajectory requires knowing the angle that the ammunition makes with respect to a plane, preferably vertical, the angle considered being an angle of roll of the ammunition or of rotation around itself. In the remainder of the description, the determination of this angle will be applied for a munition with the aim in particular of correcting its trajectory.
  • the invention can be applied to determine the roll angle of all types of flying machines regardless of the subsequent use of this angle.
  • the flying devices can for example be shells, bombs, rockets, or missiles.
  • the invention is particularly suitable for vehicles having rolling speeds of the order of, for example, from 10 to 50 revolutions per second.
  • FIG. 2 illustrates a possible embodiment of a device according to the invention. It includes elements on board the fired munition 21 and elements on the ground.
  • One of the advantages of the invention is to place on the ground most of the complex and expensive elements, the elements placed in the munition being of low cost. Ground elements are common to several munitions, in practice to a large number of munitions.
  • the invention uses the known GPS system, this second expression coming from the Anglo-Saxon expression "Global Positioning System”.
  • the GPS system is used in particular to obtain the coordinates and the speed vector of the munition 21.
  • munition 21 does not include a GPS receiver, an expensive system, but only a GPS antenna, with an annular structure for example, then means for re-transmitting this signal towards the ground.
  • the retransmission means comprise at least one retransmission antenna 23 with an anisotropic structure in the rolling plane of the munition 21, that is to say in a plane perpendicular to its longitudinal axis 24.
  • the combination of the GPS signal and of a signal produced by the quality of anisotropy of the retransmission antenna 23 makes it possible according to the invention to determine the roll angle of the munition 21.
  • a transponder 25 is for example interposed between the GPS antenna 22 and the retransmission antenna 23.
  • the GPS antenna receives a signal from a satellite and then the transponder 25 transposes the frequency of the signal received into another frequency band, from higher frequency preference.
  • the transponder 25 for example transposes the GPS signal into the S band, any other frequency band can be envisaged depending on the application. Frequency transposition is preferable to avoid re-transmitting in the frequency band reserved for GPS signals and thus to avoid any risk of confusion.
  • the device On the ground, the device comprises at least one GPS receiver 26 and calculation means 27 which make it possible to define the angle made by a singular point of the retransmission antenna 23 with a reference plane passing through the roll axis of the ammunition 21, in fact its longitudinal axis 24, in particular from a particular signal picked up by the GPS reception means on the ground, when the singular point passes for example as close as possible to the latter.
  • the angle thus defined represents the roll angle of the ammunition.
  • a reception antenna 28, operating for example in S-band receives the signal 32 re-emitted by the antenna 23 of the ammunition 21.
  • the antenna 28 is for example connected to means 29 for transposing the received signal, for example in S-band , in the frequency band of GPS signals.
  • the transposition means 29 are connected to the GPS receiver 26 via a two-position switch 30 for example. In a first position the switch 30 connects the GPS receiver 26 to an antenna 31. In a second position, it connects the frequency transposition means 29 to the GPS receiver 26. In the first position, the GPS system makes it possible to know the position of the antenna 31. When the switch switches to its second position, that is to say at the time of the firing, the receiver then indirectly exploits the signals received by the ammunition 21 and locates the latter as if it were on board .
  • the accuracy of the device can be significantly improved by using a second, fixed receiver allowing said differential positioning.
  • the latter calculates corrections to be applied by the receiver 26, in the same way as a receiver carried by the munition.
  • the GPS information as such cannot provide any information on the orientation of the roll of the munition 21.
  • the device according to the invention exploits the anisotropy property of the retransmission antenna 23
  • This antenna provides the reception means 28, 29, 26 located on the ground with characteristic information at each turn that the munition 21 performs on itself.
  • FIG. 3 shows an example of a characteristic signal as provided by the retransmission antenna 23, anisotropic at least in the rolling plane of the munition.
  • the signal 32 retransmitted by the anisotropic antenna 23 is represented by its amplitude as a function of time t. This signal is for example in the S band.
  • the abovementioned characteristic is for example a signal peak 39.
  • This peak 39 appears each time that a singularity of the antenna passes opposite the reception means on the ground, for example in view of the S-band antenna 28.
  • the singularity causing this signal characteristic is in particular a cause of anisotropy of the retransmission antenna 23, which operates in S-band for example, when using a transponder 25 of band S.
  • the duration between two consecutive peaks 39 indicates the duration of a roll of the ammunition.
  • the aforementioned singularity can be achieved in different ways known to those skilled in the art.
  • the calculation means 27 use the signal of FIG. 3 as well as the GPS data made up in particular of the position and the speed vector of the ammunition 21. Digitization means not shown, for example integrated into the calculation means 27, deliver the data and the aforementioned characteristics directly exploitable by the latter.
  • FIG. 4 illustrates a possible processing carried out by the calculation means 27.
  • the latter use the base-munition direction, the base reference point being given by the signal received by the antenna 31 for receiving GPS on the ground. This direction is known with precision since the reference point of the base as well as the reference point of the ammunition 21 are perfectly determined by the GPS signals as it was seen previously.
  • the signal peak 29 as for example illustrated by FIG. 3 appears when the singularity 41 of the retransmission antenna 23 passes as close as possible, for example to the antenna 28 for receiving band S, that is to say precisely when the singularity 41 passes in the plane Ps formed by the axis 24 of the munition 21 and the base-munition direction.
  • the axis 24 of the ammunition is carried by a vector X ⁇ .
  • M being the reference point of the ammunition 21 and S being the reference point of the base on the ground
  • the direction base-ammunition is carried by the vector of origin S and of end M. Thereafter, the opposite vector MS ⁇ is taken into account.
  • the calculation means 27 exploit the fact that there is a correlation between the presence for example of a signal peak with a known direction in the terrestrial frame of reference, this known direction being carried by the vector MS ⁇ .
  • the calculation means 27 then determine the roll orientation of the ammunition 27 by performing, for example, appropriate calculations from position and direction data.
  • the direction of the singularity 41 of the retransmission antenna 23 is carried by a vector noted Y ⁇ .
  • the instant of appearance of a peak corresponds to the instant when the vector Y ⁇ is located in the plane Ps carried by the vectors X ⁇ and MS ⁇ .
  • the roll position of the munition 21 with respect to a reference plane is defined by the angle ⁇ made by the plane Ps with this reference plane.
  • the latter is for example the vertical plane P v .
  • the calculation means 27 can therefore determine the angle ⁇ made by the singularity with for example the vertical plane P v , which in fact gives an indication of l 'roll angle which is this calculated angle ⁇ .
  • the Ps plane varies during the time as a function of the trajectory of the munition 21.
  • the measurements of the roll angle are sampled over time, the sampling instants being the instants where the characteristic 41 of the retransmission antenna 21 meets the plane Ps formed in fact of the velocity vector V ⁇ of ammunition, approximately collinear to the vector X ⁇ , and the vector MS ⁇ defined by the reference points of the munition 21 and of the ground base 28, 29, 26.
  • the vector MS ⁇ and vector V ⁇ are derived from positioning and direction data provided by GPS signals.
  • the calculation means 27 can also carry out a processing operation to determine a correction order 33 to be sent to the munition 21.
  • This correction order is in particular a function of the position of the ammunition in the terrestrial frame of reference. , from the position of the lens of the ammunition in the same terrestrial reference, of the speed vector V ⁇ ammunition and roll angle ⁇ .
  • the invention offers several advantages. It allows in particular a trajectory correction in range and lateral without additional equipment, for example of the vertical detector type on board the munition.
  • the combination of GPS data and of the signal retransmitted by the anisotropic antenna 23 makes it possible according to the invention to determine the roll angle, necessary in particular for the correction of the trajectory in range and in side.
  • the cost of the materials on board the ammunition and necessary in particular for determining the roll angle ⁇ are reduced insofar as it only requires at most one GPS antenna 22, a transponder 25 and a re-emission antenna 23.
  • the costly means are placed on the ground and are common to all ammunition, these ground means are mainly the GPS receiver 26 and the means 27 for calculating the roll angle, then the antenna 28 for example of band S and the means of transposition 29.

Landscapes

  • 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)
  • Position Fixing By Use Of Radio Waves (AREA)
EP19970401026 1996-05-14 1997-05-07 Vorrichtung zur Rollwinkelbestimmung eines Flugkörpers, insbesondere einer Munition Expired - Lifetime EP0809084B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9605979A FR2748814B1 (fr) 1996-05-14 1996-05-14 Dispositif de determination de l'orientation en roulis d'un engin volant, notamment d'une munition
FR9605979 1996-05-14

Publications (2)

Publication Number Publication Date
EP0809084A1 true EP0809084A1 (de) 1997-11-26
EP0809084B1 EP0809084B1 (de) 2003-03-19

Family

ID=9492111

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970401026 Expired - Lifetime EP0809084B1 (de) 1996-05-14 1997-05-07 Vorrichtung zur Rollwinkelbestimmung eines Flugkörpers, insbesondere einer Munition

Country Status (3)

Country Link
EP (1) EP0809084B1 (de)
DE (1) DE69719852T2 (de)
FR (1) FR2748814B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6098547A (en) * 1998-06-01 2000-08-08 Rockwell Collins, Inc. Artillery fuse circumferential slot antenna for positioning and telemetry
EP1291600A1 (de) * 2001-09-07 2003-03-12 Tda Armements S.A.S. Verfahren zur Lenkung eines Gerätes, insbesondere einer Munition
CN112902768A (zh) * 2021-03-18 2021-06-04 星河动力(北京)空间科技有限公司 运载火箭滚转的控制方法、装置、运载火箭及存储介质

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105180728B (zh) * 2015-08-27 2017-01-11 北京航天控制仪器研究所 基于前数据的旋转制导炮弹快速空中对准方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2980363A (en) * 1952-10-29 1961-04-18 Erick O Schonstedt Fluid gyroscope for indicating orientation of a spinning missile
US3374967A (en) * 1949-12-06 1968-03-26 Navy Usa Course-changing gun-launched missile
DE1456151A1 (de) * 1965-11-10 1969-04-03 Messerschmitt Boelkow Blohm Verfahren zur Fernlenkung eines um seine Laengsachse rotierenden Flugkoerpers und Einrichtung zur Durchfuehrung des Verfahrens
EP0341772A1 (de) * 1988-05-09 1989-11-15 Hollandse Signaalapparaten B.V. System zur Kurskorrektur eines rotierenden Projektils
EP0453423A2 (de) * 1990-04-18 1991-10-23 Bofors AB Rollwinkelermittlung
WO1995028776A1 (en) * 1994-04-18 1995-10-26 Northrop Grumman Corporation Stock locator system using gps translator

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3374967A (en) * 1949-12-06 1968-03-26 Navy Usa Course-changing gun-launched missile
US2980363A (en) * 1952-10-29 1961-04-18 Erick O Schonstedt Fluid gyroscope for indicating orientation of a spinning missile
DE1456151A1 (de) * 1965-11-10 1969-04-03 Messerschmitt Boelkow Blohm Verfahren zur Fernlenkung eines um seine Laengsachse rotierenden Flugkoerpers und Einrichtung zur Durchfuehrung des Verfahrens
EP0341772A1 (de) * 1988-05-09 1989-11-15 Hollandse Signaalapparaten B.V. System zur Kurskorrektur eines rotierenden Projektils
EP0453423A2 (de) * 1990-04-18 1991-10-23 Bofors AB Rollwinkelermittlung
WO1995028776A1 (en) * 1994-04-18 1995-10-26 Northrop Grumman Corporation Stock locator system using gps translator

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6098547A (en) * 1998-06-01 2000-08-08 Rockwell Collins, Inc. Artillery fuse circumferential slot antenna for positioning and telemetry
EP1291600A1 (de) * 2001-09-07 2003-03-12 Tda Armements S.A.S. Verfahren zur Lenkung eines Gerätes, insbesondere einer Munition
FR2829593A1 (fr) * 2001-09-07 2003-03-14 Tda Armements Sas Procede de guidage d'un engin, notamment d'une munition
CN112902768A (zh) * 2021-03-18 2021-06-04 星河动力(北京)空间科技有限公司 运载火箭滚转的控制方法、装置、运载火箭及存储介质
CN112902768B (zh) * 2021-03-18 2022-09-09 星河动力(北京)空间科技有限公司 运载火箭滚转的控制方法、装置、运载火箭及存储介质

Also Published As

Publication number Publication date
FR2748814B1 (fr) 1998-08-14
FR2748814A1 (fr) 1997-11-21
DE69719852D1 (de) 2003-04-24
EP0809084B1 (de) 2003-03-19
DE69719852T2 (de) 2003-12-04

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