EP0481795A1 - Bouée aeroportée largable - Google Patents

Bouée aeroportée largable Download PDF

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Publication number
EP0481795A1
EP0481795A1 EP91309607A EP91309607A EP0481795A1 EP 0481795 A1 EP0481795 A1 EP 0481795A1 EP 91309607 A EP91309607 A EP 91309607A EP 91309607 A EP91309607 A EP 91309607A EP 0481795 A1 EP0481795 A1 EP 0481795A1
Authority
EP
European Patent Office
Prior art keywords
buoy
petals
launched
band
windflap
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.)
Withdrawn
Application number
EP91309607A
Other languages
German (de)
English (en)
Inventor
Patrick John Green
Nigel Axford
Peter Ridgewell
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.)
BAE Systems Electronics Ltd
Original Assignee
GEC Marconi Ltd
Marconi Co 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 GEC Marconi Ltd, Marconi Co Ltd filed Critical GEC Marconi Ltd
Publication of EP0481795A1 publication Critical patent/EP0481795A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/50—Brake flaps, e.g. inflatable
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B22/00—Buoys
    • B63B22/003—Buoys adapted for being launched from an aircraft or water vehicle;, e.g. with brakes deployed in the water

Definitions

  • This present invention relates to air-launched buoys and especially to air launched bathythermal buoys.
  • Bathythermal buoys are normally launched in to the sea from an aircraft, or helicopter, and it is necessary to control their decent in order that they land in the most favourable attitude.
  • an air launched buoy comprising a generally cylindrical body having a front end and a rear end, a plurality of hinged petals disposed around the circumference of said buoy, said hinged petals in the pre-launch condition of said buoy being retained in a forwards pointing direction against said body, a flexible cylindrical skirt being provided around said body and between said body and said petals, said petals when said buoy is launched being partially released from said body whereby due to the forwards movement of said buoy said petals and said flexible skirt are caused to assume a rearwards and outwards configuration, said skirt being outwardly of said petals, for controlling the descent of said buoy.
  • said petals are made of plastics material and are conveniently formed integrally with a cylindrical band which is circumferentially disposed on said body.
  • each petal is formed by a reduced thickness portion at its junction with said cylindrical band, said cylindrical band being retained on said body by a circumferential retaining wire which extends around said body and across the reduced thickness portion of said petals.
  • each of said petals bears against said circumferential wire to control the rearwards and outwards movements of said petals.
  • the buoy comprises a circumferential retaining band which in the pre-launch mode of said buoy retains said petals against the body of said buoy, a windflap being provided associated with said retaining band, said windflap when said buoy is launched causing said retaining band to be released to partially release said petals.
  • the buoy may conveniently comprise an aerial attached to the rear end of said body, in which case said aerial may be retained against said body by said windflap and is released when said windflap is released.
  • FIG. 1 of the drawings there is shown a bathythermal buoy 1 in the position where it has just been launched from an aircraft (not shown) to descend into the sea (not shown).
  • the buoy 1 comprises a body 2 having a front end 3 and a rear end 4.
  • a cylindrical band 5 of plastics material which has integrally formed with it a plurality, typically 18, of forwards pointing petals 6 disposed around the circumference of the body 2.
  • Each of the petals 6 is provided at its junction with the band 5 with a reduced thickness portion 7 by means of which the petals 6 are effectively hinged to the band 5.
  • the band 5, and thus the petals 6, are retained on the body 2 of the buoy 1 by means of a circumferential retaining wire 8 the ends (not shown) of which are twisted together to clamp the band 5 to the body 2.
  • a flexible cylindrical skirt 9 one circumferential edge of which is secured to the body 2 in the vicinity of the band 5.
  • the buoy 1 of Figure 1 also comprises a plastics windflap 10 which, in the pre-launch condition, is retained on the body 2 of the buoy 1 by means of a retaining band 11, the ends of which attach to the windflap 10, the retaining band 11 also extending around the petals 6 to retain them against the body 2 of the buoy 1.
  • the buoy 1 of Figure 1 further comprises an aerial 12 which, in the pre-launch condition, is folded back against the body 2 of the buoy 1 and is retained in position by the windflap 10.
  • the buoy 1 described with reference to Figure 1 operates as follows. When the buoy is launched from an aircraft, wind gets between the windflap 10 and the body 2 of the buoy 1 and causes the windflap to be detached from retaining band 11 allowing it and the retaining band 11 to be separated from the buoy 1. This releases the petals 6 and also releases the aerial 12 which is of the self-erecting kind and adopts a position in which it extends rearwards from the rear end 4 of the body 2 as shown in broken lines 13.
  • Movement of the buoy 1 in the air stream thereof causes the body 2 to adopt a position shown in Figure 2 of the drawings in which the petals 6 and the flexible skirt 9 are bent back on themselves to adopt a rearwards and outwards position as shown, the flexible skirt 9 being outside of the petals 6 relative to the body 2, the combined effect of the petals 6 and the skirt 9 being to retard and stabilise the ballistic flight of the buoy 1 through the air such that it enters the sea front end 3 first in a controlled manner.
  • buoy 1 When the buoy 1 enters the sea it floats on the surface thereof front end 3 downwards, and a sea-water entry switch (not shown) may be activated to energise the electronics (not shown) thereof. After a suitable delay a probe unit (not shown) may be released from the front end 3, the probe unit being allowed to descend in the sea in order to make the necessary bathythermal measurements which are transmitted back to a control centre via the aerial 12 which, in the floating mode of the buoy 1 extends substantially vertically upwards from the rear end 3 of the buoy which is out of the sea.
  • a sea-water entry switch (not shown) may be activated to energise the electronics (not shown) thereof.
  • a probe unit (not shown) may be released from the front end 3, the probe unit being allowed to descend in the sea in order to make the necessary bathythermal measurements which are transmitted back to a control centre via the aerial 12 which, in the floating mode of the buoy 1 extends substantially vertically upwards from the rear end 3 of the buoy which is out
  • FIG 3 of the drawings there is shown a cross-sectional side view of part of the buoy of Figures 1 and 2 showing the disposition of the petals 6 in the pre-launch mode.
  • part of the body 2 of the buoy 1 is shown together with the cylindrical band 5 of plastics material having the petals 6 formed integrally with it.
  • the petals 6 are hinged to the band 5 by means of the reduced thickness portion 7.
  • the band 5 and the petals 6 are retained on the body 2 of the buoy by means of the circumferential retaining wire 8.
  • the skirt 9 may be attached to the body 2 in the vicinity of the hinges 7 in any suitable way.
  • the petals 6 are retained against the body 2 of the buoy 1 by means of the retaining band 11.
  • petals 6, integral cylindrical band 5, skirt 9, windflap 10 and retaining band 11 may all be made of plastics material and therefore add very little to the weight of the buoy 1 and provide a very advantageous alternative to the parachute arrangements used with existing air launched buoys.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
EP91309607A 1990-10-19 1991-10-17 Bouée aeroportée largable Withdrawn EP0481795A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9022740 1990-10-19
GB9022740A GB2248804A (en) 1990-10-19 1990-10-19 Air-launched buoys

Publications (1)

Publication Number Publication Date
EP0481795A1 true EP0481795A1 (fr) 1992-04-22

Family

ID=10683991

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91309607A Withdrawn EP0481795A1 (fr) 1990-10-19 1991-10-17 Bouée aeroportée largable

Country Status (6)

Country Link
EP (1) EP0481795A1 (fr)
JP (1) JPH04260897A (fr)
AU (1) AU8595491A (fr)
CA (1) CA2052993A1 (fr)
GB (1) GB2248804A (fr)
NO (1) NO914072L (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994012848A1 (fr) * 1992-12-03 1994-06-09 Giat Industries Dispositif de positionnement pour sous-munition dispersable
EP0767356A1 (fr) * 1995-10-06 1997-04-09 Giat Industries Perfectionnement apporté à un système de freinage aérodynamique d'une sous-munition éjectée d'un obus cargo en étant animée d'un mouvement de rotation
GB2365952A (en) * 2000-08-16 2002-02-27 Secr Defence Drag brake for a munition

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2769287B1 (fr) * 1997-10-08 1999-12-24 Lacroix Soc E Dispositif de freinage de la chute d'une charge
CN114954789B (zh) * 2022-05-24 2023-11-21 西北工业大学 一种基于旋翼无人机的可快速布放和回收浮标装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3695177A (en) * 1964-09-17 1972-10-03 Us Navy Air brake for airborne missiles
FR2445510A1 (fr) * 1978-12-30 1980-07-25 Dynamit Nobel Ag Missile d'exercice a stabilisation par effet gyroscopique
EP0305040A1 (fr) * 1987-07-15 1989-03-01 Gec-Marconi Limited Dispositif de freinage et d'orientation pour un projectile
WO1989009919A1 (fr) * 1988-04-12 1989-10-19 Thomson-Brandt Armements Dispositif de separation de freinage aerodynamique d'un corps
EP0348201A1 (fr) * 1988-06-24 1989-12-27 British Aerospace Public Limited Company Ensemble d'ailettes pour projectile

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2456049A1 (fr) * 1979-05-10 1980-12-05 France Etat Dispositif d'ejection automatique du conteneur d'une charge telle qu'une bouee d'ecoute
FR2464179A2 (fr) * 1979-08-28 1981-03-06 Thomson Csf Bouee aeroportee largable

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3695177A (en) * 1964-09-17 1972-10-03 Us Navy Air brake for airborne missiles
FR2445510A1 (fr) * 1978-12-30 1980-07-25 Dynamit Nobel Ag Missile d'exercice a stabilisation par effet gyroscopique
EP0305040A1 (fr) * 1987-07-15 1989-03-01 Gec-Marconi Limited Dispositif de freinage et d'orientation pour un projectile
WO1989009919A1 (fr) * 1988-04-12 1989-10-19 Thomson-Brandt Armements Dispositif de separation de freinage aerodynamique d'un corps
EP0348201A1 (fr) * 1988-06-24 1989-12-27 British Aerospace Public Limited Company Ensemble d'ailettes pour projectile

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994012848A1 (fr) * 1992-12-03 1994-06-09 Giat Industries Dispositif de positionnement pour sous-munition dispersable
FR2698957A1 (fr) * 1992-12-03 1994-06-10 Giat Ind Sa Dispositif de positionnement pour sous-munition dispersable.
EP0767356A1 (fr) * 1995-10-06 1997-04-09 Giat Industries Perfectionnement apporté à un système de freinage aérodynamique d'une sous-munition éjectée d'un obus cargo en étant animée d'un mouvement de rotation
FR2739682A1 (fr) * 1995-10-06 1997-04-11 Giat Ind Sa Perfectionnement apporte a un systeme de freinage aerodynamique d'une sous-munition ejectee d'un obus cargo en etant animee d'un mouvement de rotation
GB2365952A (en) * 2000-08-16 2002-02-27 Secr Defence Drag brake for a munition

Also Published As

Publication number Publication date
GB2248804A (en) 1992-04-22
GB9022740D0 (en) 1990-12-05
CA2052993A1 (fr) 1992-04-20
JPH04260897A (ja) 1992-09-16
NO914072L (no) 1992-04-21
AU8595491A (en) 1992-04-30
NO914072D0 (no) 1991-10-17

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