EP0448423B1 - Système de détection pour aéronef stabilisé en roulis - Google Patents

Système de détection pour aéronef stabilisé en roulis Download PDF

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Publication number
EP0448423B1
EP0448423B1 EP91400422A EP91400422A EP0448423B1 EP 0448423 B1 EP0448423 B1 EP 0448423B1 EP 91400422 A EP91400422 A EP 91400422A EP 91400422 A EP91400422 A EP 91400422A EP 0448423 B1 EP0448423 B1 EP 0448423B1
Authority
EP
European Patent Office
Prior art keywords
aircraft
rotary
roll axis
window
crown
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.)
Expired - Lifetime
Application number
EP91400422A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0448423A1 (fr
Inventor
Joseph Bensimon
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.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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 Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0448423A1 publication Critical patent/EP0448423A1/fr
Application granted granted Critical
Publication of EP0448423B1 publication Critical patent/EP0448423B1/fr
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
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • 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
    • F41G7/22—Homing guidance systems
    • F41G7/222—Homing guidance systems for spin-stabilized missiles
    • 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
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves

Definitions

  • the present invention relates to a detection system for an aircraft stabilized in roll.
  • US Patent 3,942,446 relates to an enemy aircraft detection system for a roll stabilized missile.
  • this prior system there are provided rings of detectors disposed at the periphery of said missile. To be able to cover the entire field around the roll axis of the missile, each ring has a plurality of detectors. The multiplicity of said detectors results in a high cost of the system and a complex management of the information transmitted by said detectors.
  • This latter detection system is only intended to guide a projectile towards a target and only requires the observation of a limited region of space.
  • the object of the present invention is to remedy the drawbacks mentioned above. It relates to a detection system which comprises a limited number of detectors and which is particularly, although not exclusively, suitable for the self-protection of a missile flying at high altitude, vis-à-vis other ground / air or air missiles / air tending to destroy it and can come from any direction.
  • document US-A-4,193,688 describes processing means receiving signals from photosensitive detectors and means for measuring the angular position of a rotary part
  • document GB-A-1,511,643 shows that a detector can be placed elsewhere than in the nose of an aircraft.
  • these last two documents like document US-A-4 142 696, describe detection devices for guiding towards a target or for firing near a target requiring only the limited observation of a region of space.
  • said rotary crown To detect an enemy which could be anywhere relative to the missile of the invention, it is advantageous for said rotary crown to rotate continuously around the roll axis of said aircraft. However, in the case where the enemy missile is necessarily on one side of the missile of the invention, it may be sufficient for said rotary crown to oscillate back and forth around the axis of roll of said aircraft. This is for example the case when the missile of the invention flies at very high altitude and must monitor enemy missiles arriving from below.
  • said photosensitive means, said measurement means and said processing means some are integral with said aircraft and others with said rotary ring, so that a device with a rotating joint or the like is provided for electrically supply said means and to link them together.
  • said crown may include a journaled shaft in the aircraft, it is preferable for said rotary crown to rotate around a shaft integral with said aircraft.
  • said aircraft can be produced in two removable parts, nestable by means of said shaft.
  • said rotary crown can be mounted on said shaft when said parts of the aircraft are dismantled.
  • said rotary crown which can be produced in two parts which can be assembled around said shaft.
  • said aircraft can be in one piece.
  • the peripheral wall of said rotary crown is flush with the external face of the skin of said aircraft.
  • this results in slots on either side of said crown, and therefore discontinuities, which can generate undesirable aerodynamic effects.
  • the peripheral wall of said rotary crown is set back from the external face of the skin of said aircraft and the part of said skin opposite said rotary crown is made at least partly of a material transparent to radiation. to which said photosensitive means are sensitive.
  • the external face of the skin of the aircraft can be continuous.
  • said material transparent to radiation forms a complete crown of said skin of the aircraft.
  • said transparent material may form only one segment of the crown of the skin of the aircraft, this segment corresponding to the maximum stroke of the rotating crown.
  • said window includes an objective of the fish eye type making it possible to cover a field of 180 ° in the rotary plane passing through the center of said window and through the roll axis of said aircraft.
  • said photosensitive means consist of several individual detectors and an observation window is associated with each of said individual detectors, the field scanned by each individual detector-window pair being part of the total field in the plane rotary passing through the center of said window and through the roll axis of said aircraft.
  • Figure 1 shows, schematically, a missile according to the present invention, of which only the outer contour has been shown in phantom, while the rotary crown which it comprises is shown in solid lines.
  • FIG. 2 is a diametral section, through a plane passing through the roll axis of the missile, of the crown shown in FIG. 1.
  • Figure 3 is a block diagram illustrating the detection system according to the invention, partly secured to the missile and partly secured to the crown.
  • FIG. 4 illustrates the operation of the system of FIGS. 1 to 3.
  • FIGS. 5A and 5B illustrate two modes of mounting the rotary crown on the missile.
  • FIGS. 6A and 6B illustrate an alternative embodiment of the mounting of the crown on the missile.
  • FIGS. 7A, 7B and 7C illustrate alternative arrangements of the rotary crown in the missile.
  • Figure 8 is a cross section of the observation window provided in the rotating crown.
  • FIG. 9 illustrates, in a view identical to FIG. 1, an alternative embodiment of the rotary crown.
  • Figure 10 is a section of the crown of the system of Figure 9, by a plane orthogonal to the roll axis of the missile.
  • Figures 11, 12 and 13 correspond respectively to sections along lines XI-XI, XII-XII and XIII-XIII of Figure 10.
  • Figures 14, 15 and 16 show the system according to the present invention, mounted respectively on a satellite and aircraft.
  • the missile 1, shown diagrammatically in FIG. 1, is stabilized in roll around its longitudinal axis, or roll axis, L-L.
  • the missile 1 comprises a hollow rotary crown 3, capable of turning around said roll axis L-L.
  • the crown 3 comprises, near its center, bearings 7A.
  • the crown 3 has an observation window 5, with a center 6.
  • the crown 3 is rotatably mounted by means of the bearings 7A, on a shaft 7, integral with the missile 1.
  • photosensitive means 8 arranged opposite the observation window 5.
  • the photosensitive means 8 are for example produced in the form of bars or arrays of elements CCD type photosensitive, sensitive to infrared radiation.
  • These photosensitive means are integral in rotation with the crown 3.
  • the latter comprises a motor 9, integral in rotation with said crown, and rotating a pinion 10 meshing with a toothed wheel 11 integral of the shaft 7.
  • the shaft 13 of the motor 9, on which the pinion 10 is wedged, is journalled in a frame 12 secured to the rotary crown 3.
  • the shaft 13 is also secured to an indexing disc 14 cooperating with an angular position encoder 15, integral with the crown 3.
  • An electrical supply device 16, integral with the missile 1, is provided for supplying the photosensitive means 8, the motor 9, as well as a device 17 for processing information, this device 17 being integral with the missile 1.
  • a rotating joint or manifold device 18 is provided to allow the photosensitive means 8 and the motor 9 to be supplied from the supply device 16, as well as to transmit the information coming from the photosensitive means 8 to the processing device 17 and of the encoder 15.
  • FIG. 3 there is shown, in block diagram, the supply and data transmission links between the devices 16 and 17 linked to the missile 1 and the devices 8, 9, 14 and 15 linked to the rotary crown 3. It has been shown that these connections pass through the rotary joint device or the like 18, and that the crown 3 was linked to the missile 1 by the drive 10, 11.
  • the motor 9 is controlled to drive the crown 3 in rotation about the axis LL, either continuously over 180 °, or alternately back and forth, around from a middle position over an angular amplitude less than or equal to 180 °.
  • the photosensitive means 8 are arranged so as to cover, in the axial plane passing through the center 6 of the observation window 5 and through the roll axis LL, a field A (see FIG. 1) of opening as close as possible 180 °.
  • this field A Due to the rotation of this field A around the roll axis LL with the rotation of the crown 3, the field A sweeps, or the entire environment around the missile 1 (continuous rotation of the crown 3), or part of this environment (alternative rotation of said crown 3).
  • the device 17, receiving the information from the photosensitive means 8 and from the angular position encoder 14, 15, is capable of determining the coordinates of any missile M located around the missile 1, by example in the form of the angular coordinates ⁇ and ⁇ illustrated in FIG. 4.
  • the photosensitive means 8 indicate the position of the missile M in the field A
  • the encoder 14, 15 indicates the position of the field A around the 'axis LL.
  • the missile 1 is composed of two parts 1A and 1B which can be assembled to one another by means of the shaft 7.
  • the shaft 7 is integral with the cylindrical part 1B and can enter a recess 20 provided in the conical part 1A.
  • FIG. 5B it has been assumed that the shaft 7 was integral with the conical part 1A and could penetrate into a recess 21 in the cylindrical part 1B. In both cases, we sees that it is easy to arrange the crown 3 on the shaft 7 before assembling the two parts 1A and 1B.
  • FIGS. 6A and 6B it has been assumed that the missile 1 was in one piece, while the crown 3 was composed of two half-crowns 3A and 3B, diametrically assembled by means of devices 22. In this case, we see that the crown can be easily put in place on the shaft 7 and assembled on it thanks to the device 22.
  • FIG. 7A shows an embodiment of the system according to the present invention, in which the external peripheral wall 4 of the crown 3 is flush with the external face 30A of the skin 30 of the missile 1.
  • transverse slots 31 appear on either side of the rotary crown 3.
  • Figures 7B and 7C there is shown an embodiment in which the outer peripheral wall 4 of the crown 3 is set back relative to the outer wall 30A of the skin 30 of the missile.
  • the part 32 of the skin 30 is constituted by an omega transparent to the radiation to which the photosensitive elements are sensitive 8.
  • this irdcons constitutes a complete crown 32, as shown in FIG. 7B, or only part of the crown 33, as shown in FIG. 7C.
  • the observation window 5 is advantageous for the observation window 5 to be constituted by an objective 34 in the shape of a fish eye, allowing the field A to cover 180 °.
  • FIGS. 9 to 13 several observation windows 35, 36 and 37 are provided in the external peripheral wall 4 of the crown 3. At each of these observation windows 35, 36 and 37 are associated photosensitive means respectively bearing the references 38, 39 and 40.
  • the window 35 couple - photosensitive means 38 is oriented towards the front of the missile, to embrace part A1 of the field A.
  • the window couple 37 - photosensitive means 40 is oriented towards the rear of the missile to embrace part A3 of field A.
  • the pair of window 36 - photosensitive means 39 is oriented so as to embrace the middle part A2 of field A.
  • FIG. 14 there is shown an artificial satellite 41 having a rotating ring 3, as described above, rotating around its roll axis L-L.
  • FIGS. 15 and 16 an observation plane 42 and a combat aircraft 43 are respectively shown, comprising a crown 3 rotating around their roll axis.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Length Measuring Devices By Optical Means (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Length Measuring Devices With Unspecified Measuring Means (AREA)
EP91400422A 1990-03-16 1991-02-18 Système de détection pour aéronef stabilisé en roulis Expired - Lifetime EP0448423B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9003410 1990-03-16
FR9003410A FR2659747B1 (fr) 1990-03-16 1990-03-16 Systeme de detection pour aeronef stabilise en roulis.

Publications (2)

Publication Number Publication Date
EP0448423A1 EP0448423A1 (fr) 1991-09-25
EP0448423B1 true EP0448423B1 (fr) 1994-12-21

Family

ID=9394833

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91400422A Expired - Lifetime EP0448423B1 (fr) 1990-03-16 1991-02-18 Système de détection pour aéronef stabilisé en roulis

Country Status (6)

Country Link
US (1) US5381139A (es)
EP (1) EP0448423B1 (es)
CA (1) CA2038373C (es)
DE (1) DE69106018T2 (es)
ES (1) ES2067879T3 (es)
FR (1) FR2659747B1 (es)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7113779B1 (en) 2004-01-08 2006-09-26 Iwao Fujisaki Carrier
FR2867867B1 (fr) * 2004-03-19 2006-06-02 Thales Sa Systeme aeroporte avec mecanisme de contre-roulis
US10345087B2 (en) * 2017-08-01 2019-07-09 BAE Systems Informaticn and Electronic Systems Integration Inc. Mid body seeker payload

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2873381A (en) * 1957-08-29 1959-02-10 Thomas J Lauroesch Rotary scanning device
GB1511643A (en) * 1960-07-13 1978-05-24 Dehavilland Aircraft Missiles
US4142696A (en) * 1962-02-27 1979-03-06 Novatronics, Inc. Guidance devices
US4193688A (en) * 1970-10-28 1980-03-18 Raytheon Company Optical scanning system
SE396136B (sv) * 1974-06-25 1977-09-05 Bofors Ab Passivt ir-zonror
US3942446A (en) * 1974-09-06 1976-03-09 The United States Of America As Represented By The Secretary Of The Army Optical fuze and/or miss distance indicator
US3924826A (en) * 1974-12-20 1975-12-09 Us Air Force Rotatable window means
US4044251A (en) * 1976-05-18 1977-08-23 Minnesota Mining And Manufacturing Company Electromagnetic radiation detector with large area sensing medium
US4527158A (en) * 1982-07-29 1985-07-02 Runnels Russell W Aircraft collision pilot warning indicating system
DE3427020A1 (de) * 1984-07-21 1986-01-23 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Navigations- und flugfuehrungsverfahren
DE3615266A1 (de) * 1986-05-06 1987-11-12 Diehl Gmbh & Co Abstandszuendeinrichtung
US4755818A (en) * 1986-08-15 1988-07-05 The United States Of America As Represented By The Secretary Of The Army Aircraft collision warning system
FR2607917A1 (fr) * 1986-12-08 1988-06-10 Roche Kerandraon Oliver Guidage par infrarouge simplifie pour tout projectile

Also Published As

Publication number Publication date
CA2038373A1 (fr) 1991-09-17
FR2659747B1 (fr) 1992-08-14
US5381139A (en) 1995-01-10
EP0448423A1 (fr) 1991-09-25
CA2038373C (fr) 2001-10-16
FR2659747A1 (fr) 1991-09-20
DE69106018T2 (de) 1995-05-04
DE69106018D1 (de) 1995-02-02
ES2067879T3 (es) 1995-04-01

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