• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    - Structuring missile wall, in particular for thermal protection cap. - The structural wall (10) of a missile, in particular a protective cap (2) of the missile, comprises a structural part (11) provided with an outer face (12) and an inner face (13). ), and at least at a front end of the structural part (11), on its outer face (12) an outer layer (14) of thermal protection, and on its inner face (13) an inner layer (15). ) of thermal protection, the inner layer (15) being made of a material having a lower density of a ratio of between 2 and 20 than that of the material of the outer layer (14).
    公开号:FR3022885A1
    申请号:FR1401422
    申请日:2014-06-25
    公开日:2016-01-01
    发明作者:Clement Quertelet
    申请人:MBDA France SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a structural wall of a missile. Although not exclusively, this structuring wall relates more particularly to a missile thermal protection cap, which is intended to be mounted at the front of a missile, and is described more specifically on the basis of such a protective cap . However, the invention can be applied to different parts of the wall of a missile, in particular at the level of the structuring body thereof, of any structuring wall subjected to a large thermal or aerothermal flow. Moreover, the present invention may especially apply to a missile comprising at least one propellable propellant stage and a terminal vehicle which is arranged at the front of the propulsion stage. Such a terminal vehicle generally comprises, in particular, a sensor forming for example part of a homing device and capable of being sensitive to temperature. Although not exclusively, the present invention can thus be applied more particularly to a missile having a flight domain 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, as well as electronic equipment including embedded sensors . For this reason, it is necessary to provide a protective cap. Due to the dynamic and kinematic capabilities of the missile, the protective cap must be able to support not only high temperatures, but also significant mechanical stress. Furthermore, at least one device which is arranged inside the cap and which is intended to achieve the opening of the cap must also be protected thermal flows possibly transmitted by the cap on which it is attached.
    [0002] One solution is to cover the structural part of the wall of the cap, outside, with a large and thick layer of thermal protection so as to thermally protect the interior of the cap and in particular the terminal vehicle, but also to keep the structuring material of the cap (structural part) at a relatively low temperature (so that it does not suffer losses of its mechanical characteristics). However, as such a thick layer must have thermal protection characteristics and also mechanical protection characteristics, it has a large mass, which is detrimental to the performance of the missile.
    [0003] The present invention relates to a missile structuring wall, in particular a missile protection cap, which is intended to remedy this drawback. For this purpose, according to the invention, said structuring wall comprising a structural part provided with an external face and an internal face, is remarkable in that it further comprises, at least at a portion of the structural part: - on the external face of the structural part, at least one external layer of thermal protection; and on the internal face of the structural part, at least one inner layer of thermal protection, and in that the inner layer is made of a material having a lower density of a ratio of between 2 and 20 than that of the material. of the outer layer. Thus, thanks to the invention: the outer layer, which is advantageously configured to also perform mechanical protection and has a high density, has a reduced mass due to a reduced thickness; and the inner layer makes it possible to compensate for the reduction in thermal protection generated by the reduction in thickness of the outer layer, by making it possible to prevent or at least greatly reduce a harmful heat transfer from the structural part to internal equipment. Wall.
    [0004] In the case, for example, of a wall of a thermal protection cap, the invention makes it possible to reduce a harmful heat transfer towards a sensor of a terminal vehicle or an opening device of the protective and ejection cap. of the terminal vehicle.
    [0005] This new wall structure does not reduce the performance of the missile, whose internal parts are thermally protected (by the combination of the outer and inner layers) and mechanically (by the structural part, with the participation of the outer layer to the mechanical strength ). In addition, because of the very low density of the material of the inner thermal protection layer, which has a reduced mass, there is obtained a cover wall at least three layers (outer layer, structural part, inner layer) whose mass overall is much lower than that of a aforementioned cap including in addition to the structural part a thick outer protection (and heavy). We thus obtain a more efficient set. Thus, in the context of the present invention, instead of seeking to obtain a relatively low temperature of the structural part, it is tolerated that it is higher by providing a much thinner outer layer, but simultaneously preventing the appearance adverse effects on equipment via the inner layer. In a preferred embodiment: the outer layer comprises a material based on silicone or graphite provided with elements (fibers, fabrics, ...) integrated; and / or the inner layer comprises a fibrous material; and / or - the structural part is made of one of the following materials: a metallic material, a thermo-structural composite material, a ceramic material. Furthermore, in a particular embodiment, the structuring wall, preferably of a protective cap, comprises at least two shells bonded together at the level of connection zones (or junction), the outer layer covers said outer face as well. at said connection areas, and the inner layer releases said bonding areas on said inner face. Thus, the structuring wall is provided with a thermal protection covering on the outside the free edges (at the level of connecting zones), which contributes to the sealing of the structuring wall. The outer layer of thermal protection is torn, at the connection areas, during the separation of the shells, for example during a release or a cap opening. Furthermore, advantageously, the structuring wall, preferably of a protective cap, comprises at least one internal part, for example a pyrotechnic actuator, which is connected by at least one of its ends to the structural part. The inner part is connected to the inner face of the structural part via a thermal protection interface element, through an opening provided in the inner layer. Preferably, the interface element is made of a material identical to that of the outer layer. Note that the connection of internal parts, such as pyrotechnic actuators for example, directly to the structural part of the wall (including a cap) can not be suitable because the temperature (exceeding for example 200 ° C) is likely to degrade the operation of the pyrotechnic actuator or to trigger it inadvertently. Moreover, in a first embodiment, said outer and inner layers are arranged on all said structural part, which allows to obtain an overall protection, for example a protective cap. In addition, in a second embodiment, said outer and inner layers are arranged only on one part (preferably the front end in the case of a protective cap) of the structural part, which makes it possible to reduce the mass of the structuring wall, while applying protection to the hottest areas, for example to the nose of the protective cap. In this second embodiment, advantageously, the structural part is made of a thermo-structural composite material or a ceramic material, which has good thermal protection.
    [0006] In a particular embodiment, the structuring wall thus relates to the wall of a thermal protection cap which is intended to be mounted at the front of the missile. The present invention also relates to a missile which comprises the structuring wall, and in particular a protective cap, such as those described above. The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements. Figures 1 and 2 schematically show an example of a missile to which a protective cap is applied according to the present invention, respectively, in a position mounted on the missile and in a position of release or opening. Figure 3 is a schematic sectional view of a portion of a wall of the protective cap.
    [0007] FIG. 4B illustrates an example of a hull link zone, according to a view in a plane shown diagrammatically in FIG. 4A. Figure 5 shows the arrangement of a thermal protection interface element. The present invention applies to a missile 1 shown schematically in FIGS. 1 and 2, and it relates to a structuring wall 10 of the missile 1. This structuring wall can correspond to any part of the wall of the missile 1, which must be protected in particular thermally and also mechanically. Preferably, but not limited to, the invention is described below with reference to a wall 10 of a protective cap 2.
    [0008] This protective cap 2 is arranged at the front of the missile 1 (in the direction of movement F of said missile 1). This protective cap 2 comprises a plurality of shells 3 and 4, in this case two shells 3 and 4 in the example of Figures 1 and 2.
    [0009] In these FIGS. 1 and 2, the invention is applied to a missile 1 having a longitudinal axis XX, which 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 movement F) of this propulsion stage 5. In general, such a flying 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 temperature sensitive. The propulsion stage 5 and the terminal vehicle 6, which may be of any conventional type, are not described further in the following description. In the usual way, 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. To do this, the terminal vehicle 6 includes all the usual means (not further described), which are necessary to achieve this terminal flight. Before implementing the terminal phase, the protective cap 2 is released (or at least open), after a separation of the various shells 3 and 4, for example by pivoting, to release the terminal vehicle 6 (flying) which is then separates from the rest of the missile 1. In the situation of Figure 1, the protective cap 2 is mounted on the missile 1 in an operating position (or protection). The vehicle terminal 6 mounted inside the protective cap 2 is shown in phantom.
    [0010] In addition, in the situation of FIG. 2, the shells 3 and 4 are being separated, for example by being pivoted via hinge elements 7 (or rotation) shown diagrammatically in FIG. 2, as illustrated respectively by FIG. arrows al and a2, during a phase of opening or release of the protective cap 2. This opening or release phase of the protective cap 2 allows the release of the terminal vehicle 6, which can for example be ejected out of the missile 1 by means of appropriate ejection means (not shown). Although not exclusively, 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 providing a protective cap 2 effective to allow the holding and performance of structures, and electronic equipment and in particular embedded sensors. The protective cap 2 which is intended to be mounted at the front of the missile 1 to cover, at least in part and preferably entirely, the terminal vehicle 6 has a wall 10 provided with a structural part (or layer). 11, as shown in FIG. 3. FIG. 3 shows a portion of the wall 10 in cross section along the axis XX (for example along a plane P shown in FIG. 4A). This structural portion 11 has an outer face 12 and an inner face 13, respectively defined outwardly and inwardly of the missile 1 (or the longitudinal axis X-X of the missile 1).
    [0011] According to the invention, the wall 10 further comprises, at least at one end (or part) before 16 of the structural part 11: - on the outer face 12 of the structural part 11, an outer layer 14 of protection thermal; and - on the inner face 13 of the structural part 11, an inner layer 15 of thermal protection.
    [0012] In addition, according to the invention, the inner layer 15 is made of a material having a lower density of a ratio between 2 and 20 than the density of the material of the outer layer 14. Thus, the wall 10 comprises, more than the structural part 11, an outer layer 14 of thermal protection, which is combined with an inner layer 15 of thermal protection. More specifically: the outer layer 14, which is configured to also perform mechanical protection and has a high density for this purpose, has a reduced mass due to a reduced thickness E1; and the inner layer 15 makes it possible to compensate for the reduction in thermal protection generated by the reduction in thickness of the outer layer 14, by making it possible to prevent or at least greatly reduce a harmful thermal transfer of the structural part 11 towards internal equipment to the protective cap 2, and in particular to the sensor 8 of the terminal vehicle 6. This structure of the wall 10 does not reduce the performance of the missile 1, whose interior 17 is thermally protected (by the combination of the outer layer 14 and the inner layer 15). The wall 10 is also mechanically protected by the structural part 11, to which mechanical protection also participates the outer layer 14. In addition, because of the very low density of the material of the inner thermal protection layer 15, which has a reduced mass , the wall 10 of the protective cap 2, at least three layers (outer layer 14, structural portion 11, inner layer 15) has an overall mass which is much lower than that of a cap comprising a usual external protection thick and heavy. This produces a lighter protective cap 2 and therefore a more efficient missile 1. Thus, in the context of the present invention, instead of seeking to obtain a relatively low temperature of the structural part 11, it is tolerated that it is higher by providing an outer layer 14 much thinner, and removing the effects. corresponding adverse effects on the equipment via the inner layer 15. Moreover, in the particular example shown in Figures 3 and 4B in particular, the outer layer 14 has a reduced thickness E1 lower than the thickness E2 of the internal layer 15. In a particular embodiment: the outer layer comprises a silicone-based material that can be loaded with short fibers (carbon, glass, silica, aramid) or with fabrics (carbon, glass, silica, aramid) . It can also be made from graphite, phenolic resin or other usual materials; and the inner layer comprises a fibrous material, of the silica wool type, silica felts, magnesium silicate fibers, FCR (Refractory Ceramics Fibers), aluminum silicate fibers, polycrystalline fibers, etc. The inner layer 15 may be accompanied by a retaining fabric or comprise a sandwich material comprising several insulators. Such materials for the inner layer 15 have a great advantage over external thermal protection materials, namely a density of less than 0.5 (about two to twenty times less dense than the aforementioned materials for the outer layer 14). In return, these materials for the inner layer 15 have no mechanical strength, but this is not a problem since they are used inside the protective cap 2. In addition, the structural part 11 can be made of one of the following types of materials: - a metallic material, such as high-performance steels (type X4, X5, ...) or titanium alloys (for example Ti6Al4V); or a thermo-structural composite material, in particular of the CMC type (ceramic matrix composite); or - a ceramic material (silicon carbide, etc.).
    [0013] Moreover, in a particular embodiment, represented in FIG. 4B, which is a partial view, according to the arrow G of the transverse plane P shown in FIG. 4A, the two shells 3 and 4 are linked together at the level of connection zones. (or junction), such as the connecting zone 18. In this particular embodiment: the outer layer 14 covers said outer face 12 also at the level of the connecting zone 18 (defined by two radial edges 22 of structural part ); and - the inner layer 15 releases the connecting zone 18 on said inner face 13, stopping at the radial edges 22. Thus, the protective cap 2 is provided with a thermal protection covering on the outside 16 the free edges (at connection zones 18), which contributes to the sealing of the cap. The outer layer 14 of thermal protection is torn, at the level of the connection zones 18, during the separation of the shells 3 and 4 during the release or opening of the protective cap 2.
    [0014] This solution prevents the appearance of an opening at the connection zone 18 which would allow the introduction of aerothermal flow (capable of causing a harmful heating of the onboard equipment and in particular the sensor 8 before the hair removal). In a particular embodiment (not shown), it can provide an internal overlap of the inner layers of two adjacent shells. In addition, in this case, it can provide a pre-cutting to facilitate the tearing of the outer layer. Furthermore, the protective cap 2 comprises at least one inner part 19, for example a pyrotechnic actuator or any electronic equipment, which is connected by at least one 19A of its ends to the structural part 11. The inner part 19 is connected to the inner face 13 of the structural part 11 via a thermal protection interface element 20, in particular in the form of a soleplate, through an opening 21 provided in the inner layer 15, as shown in Figure 5.
    [0015] In a preferred embodiment, the interface element 20 is made of a material identical to that of the outer layer 14, for example a silicone material. The interface element 20 may also be made of an insulating ceramic of silicon nitride, mullite, zirconia or other type. In a particular embodiment, the protective cap 2 comprises a plurality of such internal parts 19. It will be noted that the connection of an internal part 19 such as a pyrotechnic actuator, directly to the structural part 11 of the protective cap 2 can not be suitable because the temperature is likely to degrade the operation of the pyrotechnic actuator or to trigger it inadvertently. Furthermore, in a first embodiment, said outer and inner layers 14, 15 are arranged on all said structural part 11, which makes it possible to obtain overall protection for the entire cap 2. In addition, in a second embodiment, said outer and inner layers 14, 15 are arranged only on a part or front end of the structural part 11, at the level of the nose only, which allows to reduce the mass of the protective cap 2 while applying protection to the hottest areas. In this second embodiment, the structural part 11 is preferably made of a ceramic matrix composite material, which has good thermal protection and thus provides a thermal protection especially for the part or parts not provided with layers 14 and 15. .
    [0016] Thus, in the context of the present invention, an outer layer 14 of finer thermal protection is used so that the structuring material (structural part 11) operates at a higher temperature. There is a slight loss of properties, but this is limited. In return, the inner surface 13 being hotter (several hundred degrees), it is covered with the inner layer 15 of thermal protection to protect the interior 17 and in particular the terminal vehicle 6, radiation and convective effects. The protection cap 2 thus comprises an internal thermal protection preventing a harmful heat transfer for the structures, the on-board equipment and in particular the sensor 8 of the terminal vehicle 6. The present invention can be applied to any type of missile equipped with a protective cap 2. Thus, in particular, it is not limited by the range of the missile and the presence or absence of floors, and it does not depend on the flight altitude.
    权利要求:
    Claims (13)
    [0001]
    REVENDICATIONS1. Structuring missile wall, said wall (10) comprising a structural part (11) provided with an outer face (12) and an inner face (13), characterized in that it comprises, at least at the level of a part (16) of the structural part (11): - on the outer face (12) of the structural part (11), at least one outer layer (14) of thermal protection; and - on the inner face (13) of the structural part (11), at least one inner layer (15) of thermal protection, and in that the inner layer (15) is made of a material having a lower density of a ratio of between 2 and 20 than that of the material of the outer layer (14).
    [0002]
    2. structuring wall according to claim 1, characterized in that the outer layer (14) comprises a silicone-based material or graphite provided with integrated elements.
    [0003]
    3. structuring wall according to one of claims 1 and 2, characterized in that the outer layer (14) is configured to also achieve a mechanical protection.
    [0004]
    4. structuring wall according to any one of the preceding claims, characterized in that the inner layer (15) comprises a fibrous material.
    [0005]
    5. structuring wall according to any one of the preceding claims, characterized in that said structural part (11) is made of one of the following materials: a metal material, a thermostructural composite material, a ceramic material.
    [0006]
    6. structuring wall according to any one of the preceding claims, characterized in that it comprises at least two shells (3, 4) bonded together at the level of connecting zones (18), and in that said layer 302 2 8 Said external surface (12) also covers said connection areas (18) and said inner layer (15) releases said connection areas (18) on said inner face (13).
    [0007]
    7. structuring wall according to any one of the preceding claims, characterized in that it comprises at least one inner part (19) connected by at least one of its ends (19A) to the structural part (11), said inner piece (19) being bonded to the inner face (13) of the structural part (11) via a thermal protection interface element (20) through an opening (21) provided in the inner layer (15).
    [0008]
    8. structuring wall according to claim 7, characterized in that the interface element (20) is made of a material identical to that of the outer layer (14).
    [0009]
    9. Structural wall according to any one of claims 1 to 8, characterized in that said outer and inner layers (14, 15) are arranged on all said structural part (11).
    [0010]
    10. structuring wall according to any one of claims 1 to 8, characterized in that said outer and inner layers (14, 15) are arranged only on part of the structural part (11). 20
    [0011]
    11. structuring wall according to claim 10, characterized in that the structural part (11) is made of one of the following materials: a thermo-structural composite material, a ceramic material.
    [0012]
    12. Structural wall according to any one of the preceding claims, characterized in that it represents the wall (10) of a protective cap (2) which is intended to be mounted at the front of the missile (1). ).
    [0013]
    13. Missile, characterized in that it comprises a structuring wall such as that specified in any one of claims 1 to 12.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2960619B1|2016-10-19|Structural wall of a missile, particularly for a thermal protective cap
    EP3325819B1|2019-08-28|Assembly via mechanical linkage comprising at least one part made of a composite material
    EP2146898B1|2010-12-08|Rear lower aerodynamic fairing for the attachment device of an aircraft engine
    EP0567417B1|1996-07-03|Thermal protection device for an object and structure, particularly a thermal shield, so obtained
    EP1412693A1|2004-04-28|Multilayer composite armour
    EP2190739A1|2010-06-02|Lower rear aerodynamic fairing for an aircraft engine attachment device
    CA2915109A1|2014-12-24|Assembly having a temperature-dependent self-tightening connection
    EP3274565B1|2021-09-22|Turbine ring assembly with specific holding device for ceramic matrix composite ring segments
    EP2753810B1|2018-11-07|Improved flame resistant shield
    FR2771331A1|1999-05-28|Aircraft panel
    FR2779222A1|1999-12-03|DEVICE FOR PROVISIONAL CONNECTION AND PYROTECHNICAL SEPARATION OF TWO NON-METAL ASSEMBLIES
    EP2861833B1|2016-09-28|Turbomachine shroud wall provided with an abradable layer
    EP3396300A1|2018-10-31|Actuating device for ejecting at least one removable part of a missile, in particular a fairing
    WO1983003895A1|1983-11-10|Armouring plate, particularly for lightened armouring
    EP2527781A1|2012-11-28|Joining element for a body made of a composite material of a military penetrating projectile
    EP0440544B1|1994-03-09|Thermal protection system, especially for spacecraft
    EP2701977B1|2015-09-09|Method for temporarily connecting two parts together, such as two stages of a space launcher, and assembly including two temporarily connected parts
    EP3271243B1|2021-07-14|Method and device for fireproofing a composite material part
    WO2021048489A1|2021-03-18|Structural and/or acoustic panel comprising a u-shaped sealing flange directed toward the inside of the panel, and method for manufacturing such a panel
    EP1389815A1|2004-02-18|Supporting apparatus also protecting at least one linear device against aerothermal stress
    FR3074480A1|2019-06-07|SEPARATION IN TWO TIMES OF VIROLES BELONGING TO A LAUNCHER
    EP0441704B1|1993-12-15|Rigid and pressure permeable thermal protection device
    FR2595131A1|1987-09-04|Thermal protection partition
    WO2017182565A1|2017-10-26|Thrust reverser door for a jet engine nacelle
    FR3067650A1|2018-12-21|MONOLITHIC COMPOSITE STRUCTURE FOR EXTENDED RANGE OF TEMPERATURES AND METHOD OF MANUFACTURING THE SAME
    同族专利:
    公开号 | 公开日
    US9891031B2|2018-02-13|
    PL2960619T3|2017-06-30|
    JP6573637B2|2019-09-11|
    WO2015197923A1|2015-12-30|
    ES2610752T3|2017-05-03|
    US20170167838A1|2017-06-15|
    IL249641A|2020-06-30|
    FR3022885B1|2016-10-21|
    EP2960619B1|2016-10-19|
    IL249641D0|2017-02-28|
    EP2960619A1|2015-12-30|
    JP2017519180A|2017-07-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5413859A|1992-10-28|1995-05-09|Lockhead Corporation|Sublimitable carbon-carbon structure for nose tip for re-entry space vehicle|
    US5979826A|1995-06-07|1999-11-09|Raytheon Company|Hybrid composite article and missile components and their fabrication|
    US6091375A|1996-06-25|2000-07-18|Sumitomo Electric Industries, Ltd.|Radome|
    US6558785B1|1998-08-07|2003-05-06|Lockheed Martin Corporation|Insulated reentry heat shield|
    US6592981B1|1998-08-07|2003-07-15|Lockheed Martin Corporation|Oxidation resistant insulating sandwich tiles|
    US4428998A|1979-12-21|1984-01-31|Rockwell International Corporation|Laminated shield for missile structures and substructures|
    US4892783A|1988-11-10|1990-01-09|General Electric Company|Tri-element carbon based heat shield|
    GB2228142B|1988-12-07|1993-01-06|Telefunken Systemtechnik|Radome|
    US5691736A|1995-03-28|1997-11-25|Loral Vought Systems Corporation|Radome with secondary heat shield|
    US5626951A|1995-04-03|1997-05-06|Rockwell International Corporation|Thermal insulation system and method of forming thereof|
    JP3195266B2|1997-02-12|2001-08-06|三菱重工業株式会社|Multi-layer heat insulating material and its manufacturing method|
    DE10318514B3|2003-04-24|2004-09-16|Dornier Gmbh|Multiple layer ceramic composite material used as a heat-resistant electromagnetic window comprises an oxidic carbon-free fiber-reinforced ceramic layer, and a layer made from a thermal insulating layer consisting of a pure oxidic foam|
    US7082878B2|2003-07-01|2006-08-01|Raytheon Company|Missile with multiple nosecones|
    US7710347B2|2007-03-13|2010-05-04|Raytheon Company|Methods and apparatus for high performance structures|
    US8789390B2|2010-04-15|2014-07-29|Corning Incorporated|Near net fused silica articles and method of making|
    DE202014003131U1|2014-04-11|2014-07-02|Bundesrepublik Deutschland, vertreten durch das Bundesministerium der Verteidigung, vertreten durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr|Missile with protective device against beam weapons|FR3022995B1|2014-06-25|2017-06-09|Mbda France|MISSILE PROVIDED WITH A SEPARABLE PROTECTIVE VEST|
    FR3065521B1|2017-04-21|2019-06-28|Mbda France|MISSILE PROVIDED WITH A SEPARABLE HEADBOARD COMPRISING AT LEAST ONE EJECTABLE SHELL COOPERATING WITH A SUPPORTING ELEMENT|
    FR3065798A1|2017-04-28|2018-11-02|Mbda France|ACTUATING DEVICE FOR EJECTING AT LEAST ONE REMOVABLE PORTION OF MISSILE, ESPECIALLY A HEAD|
    KR102116059B1|2018-11-13|2020-05-27|국방과학연구소|The driving part air frame of the guided missile including the dissimilar materials|
    US11260976B2|2019-11-15|2022-03-01|General Electric Company|System for reducing thermal stresses in a leading edge of a high speed vehicle|
    US11267551B2|2019-11-15|2022-03-08|General Electric Company|System and method for cooling a leading edge of a high speed vehicle|
    US11260953B2|2019-11-15|2022-03-01|General Electric Company|System and method for cooling a leading edge of a high speed vehicle|
    WO2021194718A1|2020-03-27|2021-09-30|Northrop Grumman Systems Corporation|Aerial vehicle having antenna assemblies, antenna assemblies, and related methods and components|
    法律状态:
    2015-06-30| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-01| PLSC| Search report ready|Effective date: 20160101 |
    2016-07-08| PLFP| Fee payment|Year of fee payment: 3 |
    2017-06-30| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-27| PLFP| Fee payment|Year of fee payment: 5 |
    2019-06-28| PLFP| Fee payment|Year of fee payment: 6 |
    2020-06-30| PLFP| Fee payment|Year of fee payment: 7 |
    2021-06-30| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1401422A|FR3022885B1|2014-06-25|2014-06-25|STRUCTURING WALL OF MISSILE, ESPECIALLY FOR THERMAL PROTECTION COFFEE|FR1401422A| FR3022885B1|2014-06-25|2014-06-25|STRUCTURING WALL OF MISSILE, ESPECIALLY FOR THERMAL PROTECTION COFFEE|
    PL15290153T| PL2960619T3|2014-06-25|2015-06-10|Structural wall of a missile, particularly for a thermal protective cap|
    JP2016574358A| JP6573637B2|2014-06-25|2015-06-10|Missile structure wall especially for thermal protection fairing|
    PCT/FR2015/000115| WO2015197923A1|2014-06-25|2015-06-10|Missile structural wall, in particular for a thermal protection fairing|
    US15/320,064| US9891031B2|2014-06-25|2015-06-10|Missile structural wall for thermal protection fairing|
    ES15290153.4T| ES2610752T3|2014-06-25|2015-06-10|Structural wall of a missile, in particular for a thermal protection shield|
    EP15290153.4A| EP2960619B1|2014-06-25|2015-06-10|Structural wall of a missile, particularly for a thermal protective cap|
    IL249641A| IL249641A|2014-06-25|2016-12-19|Missile structural wall, in particular for a thermal protection fairing|
    [返回顶部]