EP2960618B1 - Missile pourvu d'une coiffe de protection séparable - Google Patents

Missile pourvu d'une coiffe de protection séparable Download PDF

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Publication number
EP2960618B1
EP2960618B1 EP15290152.6A EP15290152A EP2960618B1 EP 2960618 B1 EP2960618 B1 EP 2960618B1 EP 15290152 A EP15290152 A EP 15290152A EP 2960618 B1 EP2960618 B1 EP 2960618B1
Authority
EP
European Patent Office
Prior art keywords
missile
terminal vehicle
terminal
protective cap
vehicle
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.)
Active
Application number
EP15290152.6A
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German (de)
English (en)
French (fr)
Other versions
EP2960618A1 (fr
Inventor
Clément Quertelet
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.)
MBDA France SAS
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MBDA France SAS
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Publication date
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Publication of EP2960618A1 publication Critical patent/EP2960618A1/fr
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Publication of EP2960618B1 publication Critical patent/EP2960618B1/fr
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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
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the present invention relates to a missile provided with a releasable or separable protective cap.
  • a missile is described in EP 1 013 546 A2 .
  • the present invention applies to a missile comprising at least one propulsion stage which is intended to propel the missile and which can be separated from the latter, and a terminal vehicle which is arranged at the front of this stage. propulsive and which makes a terminal flight towards a target.
  • a terminal vehicle comprises at least one sensor, for example part of a homing device, which is sensitive to temperature.
  • the present invention applies more particularly to a missile having a flight range remaining in the atmosphere and which has kinematic performance to bring the terminal vehicle at hypersonic speeds. At these high speeds, the surface temperature of the missile can reach several hundred degrees Celsius under the effect of the aerothermal flow, which can be detrimental to the strength and performance of structures, and electronic equipment and sensors present.
  • the missile is generally provided at the front of a protective cap, which generally comprises several individual shells and which is intended to thermally and mechanically protect the vehicle terminal.
  • This protection cap must be removed at the appropriate time, especially to allow the use of the sensor placed on the terminal vehicle in the terminal phase of the flight.
  • a localized protection cap is often provided which is thus relatively light. But it is then necessary to thermally protect directly parts of the terminal vehicle that are not covered by the protective cap.
  • the set is generally lighter but once the terminal vehicle disheveled, its agility is penalized by the mass of these elements of thermal protection.
  • an architecture that provides that the hulls of the protective cover are articulated on the terminal vehicle generates a large residual mass on the vehicle, due in particular to the mass of hinges or hull joints used for this purpose, and penalizes its performance during the terminal flight.
  • the present invention aims to overcome this disadvantage.
  • the invention comprises the features of claim 1. It relates to a missile comprising at least one separable propellant stage and a terminal vehicle which is arranged at the front of the propulsion stage, said missile being provided at the front of a separable (or releasable) protective cap comprising at least two individual shells.
  • said missile comprises a connecting piece linked to said missile, rearward beyond the position of the rear end of the terminal vehicle, and said protective cap, when mounted on the missile, surrounds all said terminal vehicle and is connected by a rear end to the connecting piece by means of articulated connecting elements.
  • a protection cap that is encompassing, that is to say, which completely surrounds the terminal vehicle in normal protection position.
  • Such an encompassing protective cap is certainly larger and therefore heavier than a localized protection cap, but this bounding cap structure which is linked to the missile, rearward beyond the position of the rear end of the terminal vehicle (via the connecting piece), minimizes the residual mass on the terminal vehicle after the separation, as specified below. This minimization of the mass maximizes the performance of the terminal vehicle in the terminal phase (which is the most sensitive).
  • said connecting piece has a general shape of a ring.
  • said connecting piece is an intermediate part of the body of the missile, which is arranged between the terminal vehicle and the propulsion stage.
  • this intermediate piece is able to be separated from said terminal vehicle.
  • the protective cap, the connecting piece and the rotary connection elements form a one-piece assembly, the connecting piece being adapted to be fixed on a so-called support part of the missile.
  • this support part is an intermediate part of the body of the missile, which is arranged between the terminal vehicle and the propulsion stage, and which is capable of being separated from said terminal vehicle.
  • the missile comprises at least one unit for regulating the internal pressure.
  • this internal pressure regulating unit comprises at least one valve arranged in at least one channel generating an air passage between the inside of the protective cap and the outside of the missile.
  • said at least one channel is formed in said intermediate piece.
  • the internal pressure regulating unit makes it possible to prevent the cap from deforming in flight and creates an opening allowing the introduction of the aerothermal flow that can damage structures, equipment and a sensor of the terminal vehicle.
  • said intermediate piece is configured to support the terminal vehicle and comprises ejection elements of the latter.
  • the missile comprises intermediate support elements arranged between the protective cap and the end vehicle, these intermediate support elements being fixed on an inner face of the protective cap and simply being in contact with each other. an outer face of the terminal vehicle.
  • the missile also comprises at least one shear force recovery system between the shells of the protective cap.
  • the hulls do not have to be too thick (and therefore too mass) to be able to benefit from sufficient stiffness.
  • the missile also comprises means configured to create electrical continuity between adjacent shells, electrically conductive, of the protective cap, which allows in particular to provide electromagnetic protection.
  • the present invention applies to a missile 1 diagrammatically represented on the figures 1 and 2 , which is provided at the front (in the direction of movement F of said missile 1) of a protective cap 2.
  • This protective cap 2 comprises a plurality of shells 3 and 4, in this case two shells 3 and 4 on the example of Figures 1 to 4 .
  • the X-X longitudinal axis missile 1 comprises at least one releasable propulsion stage (at the rear) and a terminal vehicle 6 which is arranged at the front (in the direction of displacement F) of this propulsion stage 5.
  • such a flying terminal vehicle 6 comprises, in particular, at least one sensor 8 arranged at the front, forming for example part of a homing device and capable of being sensitive to temperature.
  • the propulsion stage 5 and the terminal vehicle 6, which may be of any conventional type, are not described further in the following description.
  • the propulsion stage or stages 5 of such a missile 1 are intended for the propulsion of said missile 1, from the firing until the approach of a target (to be neutralized by the missile 1).
  • the terminal phase of the flight is, in turn, carried out autonomously by the terminal vehicle 6, which uses in particular the information from the onboard sensor 8, for example an optoelectronic sensor intended to assist in the detection of the target.
  • the terminal vehicle 6 includes all the usual means (not further described), which are necessary to achieve this terminal flight.
  • the protective cap 2 is dropped or at least open, after separation of the different shells 3 and 4, by example by pivoting, to release the terminal vehicle 6 (flying) which then separates from the rest of the missile 1.
  • the missile 1 is therefore provided at the front of a separable protection cap 2 which is intended, in particular, to thermally and mechanically protect the terminal vehicle 6.
  • This protective cap 2 must however be able to be removed at the appropriate time, particularly for allow the use of the sensor 8 placed on the terminal vehicle 6 in the terminal phase of the flight.
  • the protective cap 2 is mounted on the missile 1 in an operating position (or protection).
  • the vehicle terminal 6 is mounted inside the protective cap 2 which is shown in thick lines.
  • the shells 3 and 4 are separating, for example by being pivoted via rotary connection elements 7 shown schematically on the figure 2 , as illustrated respectively by arrows ⁇ 1 and ⁇ 2, during a phase of opening or release of the protective cap 2.
  • the release of the shells 3 and 4 and the pulse to generate the movements illustrated by the arrows ⁇ 1 and ⁇ 2, can be generated by a suitable device 13, for example a pyrotechnic actuator preferably arranged in front of the cap 2 (inside the latter), as shown in the figures 1 , 3 and 4 .
  • This phase of opening or release of the protective cap 2 allows the release of the terminal vehicle 6, which can for example be ejected out of the missile 1 with the aid of appropriate ejection means (not shown).
  • the present invention can be applied more particularly to a missile 1 having a flight domain remaining in the atmosphere and which has kinematic performance to bring the vehicle terminal 6 at hypersonic speeds. At these high speeds, the surface temperature of the missile 1 can reach several hundred degrees Celsius under the effect of the aerothermal flow, which requires to provide a protective cap 2 effective to allow the performance and performance of structures, electronic equipment and embedded sensors.
  • said missile 1 comprises a connection piece 10A, 10B linked to the missile 1, towards the rear (in the direction opposite to the direction of movement F) beyond the position P1 of the rear end 11 of the terminal vehicle 6 when mounted on the missile 1.
  • the protective cap 2 when it is mounted on the missile 1, the protective cap 2 surrounds all said terminal vehicle 6 and is connected by a rear end 12 to the connecting piece 10A, 10B via articulated connecting elements 7, in particular hinges or other conventional rotation elements.
  • the protection provided by the protective cap 2 thus benefits not only the sensor 8, but also the entire terminal vehicle 6.
  • the protective cap 2 encompasses the entire vehicle terminal 6 and is removed just before the use of the sensor 8 and the autonomous flight of the terminal vehicle 6.
  • the autonomous flight time of the vehicle terminal 6 (with a use of the sensor 8 ) being short, it can indeed do without thermal protection during the terminal phase of the flight.
  • this protective covering cap 2 which is removed before the autonomous flight of the terminal vehicle 6, the mass linked to the protection function (necessary only before this autonomous flight) is not impinged on the terminal vehicle 6.
  • Said connecting piece 10A has a general shape of ring, whose outer diameter is substantially equal to the diameter of the body of the missile 1 in the part where is provided this connecting piece 10A.
  • the connecting piece 10A is an intermediate piece 15 of the body of the missile 1, which is arranged between the terminal vehicle 6 and the propulsion stage 5. This intermediate piece 15 is able to be separated from said terminal vehicle 6.
  • the shells 3 and 4 of the protective cap 2 are thus articulated on the intermediate part 15 and the associated connecting means, in particular the rotary connection elements 7, are integral with this intermediate part 15. which can separate from the terminal vehicle 6 before the autonomous flight of the latter.
  • the support portion 18 is an intermediate part of the body of the missile 1, which is arranged between the terminal vehicle 6 and the propulsion stage 5, for example similarly to the intermediate part 15 of the first embodiment mentioned above.
  • This second embodiment makes it easier to manufacture and integrate the protective cap 2.
  • the connecting piece 10B and possibly the fixing means 19 it is possible to easily adapt the assembly. 16 to different types of existing missile.
  • the missile 1 comprises at least one unit 20 for regulating the internal pressure.
  • this unit 20 for regulating the internal pressure comprises at least one channel 21 creating an air passage between the inside 22 of the protective cap 2 and the outside 23 of the missile 1, and at least one valve 24 which is arranged in said channel 21.
  • the channel or channels 21 are formed in said intermediate piece 15 as shown in FIG. figure 1 , or in the middle piece 18 of figures 3 and 4 .
  • the internal pressure regulating unit 20 is arranged far from the aerothermal flow (i.e. far from the nose 27 of the protective cap 2), which makes it possible to increase the efficiency.
  • the valve 24 may, for example, consist of a ball and a return spring thereof, sized so that the internal pressure in the protective cap 2 never exceeds a predetermined threshold (for example a few millibars ).
  • a predetermined threshold for example a few millibars
  • Other usual embodiments of valve architecture can be used.
  • the pressure difference between the inside 22 and the outside 23 of the protection cap 2 may be important, the unit 20 for regulating the internal pressure makes it possible to prevent the protective cap 2 from deforming in flight and creates an opening allowing the aerothermal flow to be introduced, which may damage the structures. , the equipment and in particular the sensor 8 of the terminal vehicle 6.
  • the intermediate part 15 interfaces with the propulsion stage 5 and the junction with the vehicle terminal 6, and serves as a passage for the channel 21 and also a hinge support for the protective cap 2.
  • the intermediate piece 15, 18 is configured to support the terminal vehicle 6, and it is provided with conventional ejection elements (not shown) to eject the latter.
  • the terminal vehicle 6 also participates in maintaining the protective cap 2, which ensures a reasonable dimensioning (sufficiently low mass) of the latter.
  • the terminal vehicle 6 (having in particular a large dimension) does not sag inside the protective cap 2.
  • the missile 1 also comprises at least one system 28 for taking up shear forces between the shells 3 and 4 of the protective cap 2, as shown in FIGS. Figures 5 and 6 .
  • This system 28 makes it possible to take up the shear forces between the shells 3 and 4, which do not have to be thick (and therefore too much mass) to benefit from sufficient stiffness.
  • junctions are possible between the shells 3 and 4 of the protective part 2.
  • an internal covering with edges of cooperating shapes or with a connection of type tenon / mortise, over the entire periphery of the junction or a large part of it.
  • the shells 3 and 4 of the protective cap 2 are electrically conductive, either by being made of an electrically conductive material, or by including electrical conduction means.
  • electrical conduction means such as a metal film or a metal braid which covers a structural part of each of the shells.
  • the missile 1 also comprises means for ensuring electrical continuity between the electrically conductive shells 3 and 4 of the protective cap 2.
  • These means may comprise, as shown by way of example on the figure 6 , a seal 32, in particular a charged elastomer or a metal braid, which is arranged at the junction between the two shells 3 and 4 so as to provide electrical continuity.
  • This particular embodiment makes it possible to avoid the generation of electric arcs at the junction and to provide electromagnetic protection.
  • a protective cap 2 which is encompassing, that is to say which completely surrounds the vehicle terminal 6 in normal protection position.
  • a protective covering cap 2 is certainly heavier than a localized protection cap, but it minimizes the residual mass on the terminal vehicle 6 after the separation, since the means 7, 26 for protecting and articulating the shells 3 and 4 are not attached to the vehicle terminal 6 but dropped elements. This minimization of the mass maximizes the performance of the terminal vehicle 6 in the terminal phase (the most sensitive).
  • a possible loss of performance of the missile 1 in the first phase of the launch, with a protection cap 2 encompassing heavier than a localized protection cap, is compensable, including providing one or more powerful propulsion stages 5 .

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
EP15290152.6A 2014-06-25 2015-06-10 Missile pourvu d'une coiffe de protection séparable Active EP2960618B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1401421A FR3022995B1 (fr) 2014-06-25 2014-06-25 Missile pourvu d'une coiffe de protection separable

Publications (2)

Publication Number Publication Date
EP2960618A1 EP2960618A1 (fr) 2015-12-30
EP2960618B1 true EP2960618B1 (fr) 2017-05-10

Family

ID=52450143

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15290152.6A Active EP2960618B1 (fr) 2014-06-25 2015-06-10 Missile pourvu d'une coiffe de protection séparable

Country Status (8)

Country Link
US (1) US10054411B2 (es)
EP (1) EP2960618B1 (es)
JP (1) JP6548678B2 (es)
ES (1) ES2628256T3 (es)
FR (1) FR3022995B1 (es)
IL (1) IL249531B (es)
PL (1) PL2960618T3 (es)
WO (1) WO2015197922A1 (es)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3065521B1 (fr) * 2017-04-21 2019-06-28 Mbda France Missile pourvu d'une coiffe separable comprenant au moins une coque ejectable cooperant avec un element de support
JP6900294B2 (ja) * 2017-10-23 2021-07-07 株式会社Ｉｈｉエアロスペース ノーズフェアリングの開頭機構
CN109494469A (zh) * 2018-07-13 2019-03-19 中国航空工业集团公司济南特种结构研究所 一种回转体天线罩根部防差错结构
CN109141144B (zh) * 2018-09-29 2024-02-09 中国空空导弹研究院 一种红外制导导弹破碎型抛离罩
CN109625338B (zh) * 2018-12-12 2022-07-15 湖北航天飞行器研究所 可自抛离的整流罩以及火箭
EP3960639A4 (en) * 2019-04-26 2023-01-18 Kawasaki Jukogyo Kabushiki Kaisha BOW FAIRING
CN110749250B (zh) * 2019-10-30 2021-03-16 中国科学院力学研究所 一种高超声速飞行器保护罩
CN111392010B (zh) * 2020-04-06 2021-09-17 西北工业大学 一种航行器高速入水非对称缓冲头帽
CN111391992A (zh) * 2020-04-06 2020-07-10 西北工业大学 一种水下航行器高速入水缓冲头帽
US11220358B1 (en) * 2020-08-21 2022-01-11 Brandon West Hypersonic harmonic vehicle exciter and methods of use thereof
CN112413039B (zh) * 2020-11-19 2021-10-22 大连理工大学 一种阻尼式航行体入水缓冲装置
CN115164652A (zh) * 2022-06-30 2022-10-11 河北汉光重工有限责任公司 一种利用气动热进行抛罩的方法

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Also Published As

Publication number Publication date
JP6548678B2 (ja) 2019-07-24
ES2628256T3 (es) 2017-08-02
US10054411B2 (en) 2018-08-21
EP2960618A1 (fr) 2015-12-30
PL2960618T3 (pl) 2017-09-29
JP2017519177A (ja) 2017-07-13
US20170131076A1 (en) 2017-05-11
FR3022995A1 (fr) 2016-01-01
FR3022995B1 (fr) 2017-06-09
WO2015197922A1 (fr) 2015-12-30
IL249531B (en) 2020-05-31
IL249531A0 (en) 2017-02-28

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