EP0675334B1 - Engin largable à stabilisation et freinage aérodynamique - Google Patents
Engin largable à stabilisation et freinage aérodynamique Download PDFInfo
- Publication number
- EP0675334B1 EP0675334B1 EP19950400414 EP95400414A EP0675334B1 EP 0675334 B1 EP0675334 B1 EP 0675334B1 EP 19950400414 EP19950400414 EP 19950400414 EP 95400414 A EP95400414 A EP 95400414A EP 0675334 B1 EP0675334 B1 EP 0675334B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flaps
- missile
- dynamic pressure
- flap
- designed
- 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
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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
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/16—Wrap-around fins
-
- 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
Definitions
- the present invention relates to dropable vehicles from an aircraft, of the type fitted with passive stabilization means aerodynamics, such as fins, intended for take an initial trajectory after dropping substantially parallel to the speed of the aircraft.
- aerodynamics such as fins
- aircraft must be interpreted as covering both devices to rotary wing as those with fixed wing.
- the invention finds an important application in the field of infrared or electromagnetic decoys which, to be effective, begin to play their role nearby of the aircraft to cause the hang of a self-steering or radar of a hostile and then have to move away sufficiently progressive that the self-director or the radar stays on them, but fast enough so that a missile self-director or a radar cannot, after extinguishing the lure, hang on again the aircraft.
- CH-A-480 612 which corresponds to the preamble of claim 1
- a rocket having brake flaps deployable from a position where they are pressed against the body at a stop position, substantially perpendicular to the body.
- the shape and inclination of flaps remain unchanged regardless of the train, due that the flaps bear against a stop or are put in place by a drawer.
- DE-A-2 637 793 a dispersion munition provided with elastic lamellae, intended to bring the ammunition in a vertical position.
- the slats deploy as soon as the ammunition is out of its container and take an orientation of minus 10 °, typically around 20 °.
- the constitution of these slats gives them an effect that is not what you are looking for for the invention.
- the present invention aims in particular to provide a machine whose spacing law after release from an aircraft is almost insensitive to flight conditions, unlike previously known devices.
- the invention proposes for this purpose a machine according to the characterizing part of the claim 1.
- the machine whose general appearance is shown in Figures 1 to 3, is intended to be used as an infrared lure or electromagnetic. It has a body 10, of general appearance cylindrical, having a front cone and a boundary envelope a chamber 12 which contains the payload: a load pyrotechnic or a jammer as appropriate.
- the craft is designed to be placed in a magazine cell and for be evicted on demand by a charge of unloading represented.
- the charger itself may have a constitution known, for example that described in the patent application No. 93 10928 of the applicant (FR-A-2 710 025).
- the body carries aerodynamic stabilization means of the machine, intended to orient its longitudinal axis along of the trajectory.
- These purely passive means are formed by several fins or fins 14. These fins, four in number in the illustrated embodiment, are each fixed to two sockets 16 rotating on two aligned axes arranged in the body.
- Pre-compressed means tend to move the fins 14 from their folded position and bring them in the radial orientation where they are shown in Figures 1 and 2 and dashed in Figure 3.
- These means can be constituted by springs (not shown).
- the final orientation of the fins is fixed by support of these fins against a stop of the envelope.
- the machine further comprises flaps which can be deployed automatically after release.
- each of these flaps 17, four in number is constituted by a spring steel plate, the front part of which is held pressed against the body by fixing means, such as screws 18.
- the flaps 17 are kept applied against the body of the machine, under the fins 14, and are therefore compact. They are preformed in the deployed position, so that they are then under tension and in the absence of stress they take a free position making a determined angle a with the axis of the machine ( a ⁇ 45 ° for example).
- the elasticity of the flaps is such that the dynamic pressure exerted on them in flight gives them an angle relative to the axis of the body which depends directly on the dynamic pressure and which is less than a .
- the length of the flaps 17 and the fins 14 is such that they do not project beyond the rear of the body.
- each flap 17 is reinforced by shorter elastic blades 20 whose presence modifies the law of deformation. These additional blades will be or not present according to the law of variation of the drag at give to the craft. They are fixed flat on the shutters, for example by rivets 22.
- FIG 3 shows that the addition of the flaps of aerodynamic braking does not imply a decrease in payload of decoy and modifies very little the outer geometry of the machine.
- the bulges that represent the sockets needed to articulate the fins 14 and allow them to fold over the flaps take place easily, in the cells, square in shape, of the charger. It will simply be necessary, in general, to give each of the flaps 17 a width less than the body diameter, as shown in Figure 3.
- the overall dimensions extra due to the fins is shown in the figure 3 by a dashed frame. Deployment of the fins, such as indicated by the arrow f, releases the flaps 17 and allows them to deploy in turn.
- the shape of the fins 14 and that of the flaps 17, as well that the nature of the flap fixing means depend on of the intended application. We can indicate as an example that in the case of a device consisting of a lure with a gauge of 30 mm and about twenty centimeters long, four flaps without reinforcing blades, spring steel 0.6 mm thick, fixed to the body by a few solder points.
- each flap 17a is constituted by an elastic metal blade (spring steel in general), articulated on the body to the back of the skates.
- each flap 17a can be welded to one of the elements of a hinge 24 placed immediately behind the rear sockets 16.
- the hinges have a limited clearance, so that the flap in the free state, once turned towards the rear , make an angle b of about 45 ° with the axis of the body, near the hinge.
- the flap 17a is intended to be folded towards the nose of the machine when it is stored and kept pressed against the body by a fin 14 ( Figure 4).
- the shutter can be preformed to take the form shown in solid lines in FIG. 5 as soon as the machine is ejected and the fins 14.
- the flaps 17a have a raised beak 26
- their deployment is caused by the action of the wind on beak.
- the wind action can be replaced or supplemented by that of other means, for example by a pincer spring mounted on the hinge 24, a spring intended to take off slightly the flap of the body when released, or a wire of traction connected to the corresponding fin.
- the flaps 17a take a form which depends on the dynamic pressure acting on them, intermediate between the form indicated in dashed lines and the form indicated in dashes in figure 5. If necessary, the hinge 24 can be fitted with a retractable or destructible stop under a given constraint, so as to release the shutter beyond a given dynamic pressure and to reduce then maximum drag.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
- la figure 1 montre les éléments concernés par l'invention d'un dispositif constituant un premier mode de réalisation, vu en demi-élévation avec coupe partielle, alors que les volets sont repliés ;
- la figure 2, similaire à la figure 1, montre les volets totalement déployés ;
- la figure 3 est une vue en coupe suivant la ligne III - III de la figure 2 ;
- les figures 4 et 5, similaires à la fig. 1, montrent un autre mode de réalisation, les volets étant représentés à l'état replié (figure 4) et à l'état déployé (figure 5).
Claims (10)
- Engin largable depuis un aéronef, muni de moyens passifs de stabilisation aérodynamique, destiné à prendre une trajectoire initiale sensiblement parallèle à la vitesse de l'aéronef après largage, comportant, à l'arrière, des volets de freinage (17,17a) déployables automatiquement après largage, caractérisé en ce que les volets sont constitués et montés sur le corps de l'engin de façon à prendre dès largage une orientation tournée vers l'arrière, telle que la pression dynamique qui s'exerce sur les volets modifie automatiquement l'inclinaison ou la forme des volets dans un sens tel que la traínée supplémentaire donnée par les volets varie en fonction inverse de ladite pression dynamique, en assurant une auto-adaptation aux conditions de vol.
- Engin selon la revendication 1, caractérisé en ce que les volets (17,17a) présentent une flexibilité telle qu'ils se déforment à partir de leur position déployée dans un sens réduisant le coefficient de traínée lorsque la pression dynamique s'exerçant sur eux augmente.
- Engin selon la revendication 2, caractérisé en ce que l'avant desdits volets (17) est fixé à plat sur le corps (10) de l'engin.
- Engin selon la revendication 2 ou 3, caractérisé en ce que la partie avant des volets est renforcée par des lames plus courtes (20) fixées à plat sur les volets (17).
- Engin selon la revendication 2, 3 ou 4, caractérisé en ce que les volets sont préformés pour s'orienter à 45° environ de l'axe de l'engin à l'état libre.
- Engin selon la revendication 1, caractérisé en ce que les volets sont reliés au corps de l'engin par des moyens élastiques qui fléchissent sous l'action de la force exercée sur les volets, dans un sens réduisant le coefficient de traínée lorsque la pression dynamique augmente.
- Engin selon la revendication 1, caractérisé en ce que chaque volet (17a) est constitué d'une lame en métal élastique dont l'arrière est articulée sur le corps à l'arrière des patins par des moyens ayant un débattement limité, le volet étant prévu pour être replié vers le nez de l'engin lorsqu'il est stocké et être maintenu en appui contre le corps.
- Engin selon la revendication 7, caractérisé en ce que ledit volet (17a) présente un bec relevé (26) destiné à provoquer le déploiement par l'action du vent sur le bec.
- Engin selon la revendication 7 ou 8, caractérisé par des moyens à ressort à pincette de décollement des volets.
- Engin selon la revendication 7, 8 ou 9, caractérisé en ce que les moyens d'articulation (24) sont munis d'une butée escamotable ou destructible sous une contrainte déterminée, de façon à libérer le volet au-delà d'une pression dynamique donnée.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9402401A FR2716965B1 (fr) | 1994-03-02 | 1994-03-02 | Engin largable à stabilisation et freinage aérodynamique. |
FR9402401 | 1994-03-02 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0675334A1 EP0675334A1 (fr) | 1995-10-04 |
EP0675334B1 true EP0675334B1 (fr) | 2000-04-12 |
Family
ID=9460594
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19950400414 Expired - Lifetime EP0675334B1 (fr) | 1994-03-02 | 1995-02-27 | Engin largable à stabilisation et freinage aérodynamique |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0675334B1 (fr) |
DE (1) | DE69516200T2 (fr) |
FR (1) | FR2716965B1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2747464B1 (fr) * | 1996-04-16 | 1999-09-17 | Aerospatiale | Engin volant a aile deployable |
RU2552951C2 (ru) | 2009-01-09 | 2015-06-10 | Форвард Фарма А/С | Фармацевтический состав, содержащий один или более эфиров фумаровой кислоты в разлагаемой матрице |
US8278612B2 (en) * | 2010-07-27 | 2012-10-02 | Raytheon Company | Aerodynamic fin lock for adjustable and deployable fin |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1553980C3 (de) * | 1965-02-18 | 1975-05-22 | Breda Meccanica Bresciana S.P.A., Brescia (Italien) | Vorrichtung zum Einstellen der Schußweite von Raketengeschossen |
DE977742C (de) * | 1965-04-14 | 1969-04-30 | Kunststofftechnische Studienge | Flugkoerper mit entgegen der Luftrichtung ausklappbaren messerfoermigen Leitwerkfluegeln |
CH480612A (de) * | 1967-09-06 | 1969-10-31 | Oerlikon Buehrle Ag | Rakete mit Klappleitwerk und Bremsvorrichtung |
DE2154584A1 (de) * | 1971-11-03 | 1973-05-10 | Dynamit Nobel Ag | Flugkoerper zur bekaempfung von unterwasserzielen |
DE2637793C2 (de) * | 1976-08-21 | 1983-11-17 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Vorrichtung zur Verminderung der Fluggeschwindigkeit und zur Stabilisierung der Lage einer Streumunition |
-
1994
- 1994-03-02 FR FR9402401A patent/FR2716965B1/fr not_active Expired - Fee Related
-
1995
- 1995-02-27 DE DE1995616200 patent/DE69516200T2/de not_active Expired - Lifetime
- 1995-02-27 EP EP19950400414 patent/EP0675334B1/fr not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE69516200D1 (de) | 2000-05-18 |
DE69516200T2 (de) | 2000-11-23 |
FR2716965A1 (fr) | 1995-09-08 |
FR2716965B1 (fr) | 1996-05-03 |
EP0675334A1 (fr) | 1995-10-04 |
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