Abstract: An actuation device for ejecting a removable part of a missile includes a pyrotechnic actuator having a pyrotechnic charge configured to generate an overpressure and a piston configured to act on the removable part of the missile, at least one retaining rod, and at least one thermal insulation element configured to thermally insulate at least the pyrotechnic charge. The pyrotechnic actuator is configured to break the retaining rod.

Abstract: A missile includes a separable nose cone having an ejectable shell cooperating with a support element. The missile has a body with a main longitudinal axis and a nose cone having a shell connected by a rear end thereof to a support element of the missile and defined around a secondary longitudinal axis. The support element has a housing, and the rear end of the shell has a thickness adapted to be received in the housing in a contacting manner. The housing is configured to allow the shell to pivot and to maintain contact while the orientation of the shell is such that the secondary longitudinal axis is at an angle smaller than an ejection angle in relation to said main longitudinal axis, and to end the contact when the secondary longitudinal axis is at an angle higher than or equal to the ejection angle in such a way as to eject the shell from the missile.

Abstract: An actuation device for ejecting a removable part of a missile includes a pyrotechnic actuator having a pyrotechnic charge configured to generate an overpressure and a piston configured to act on the removable part of the missile, at least one retaining rod, and at least one thermal insulation element configured to thermally insulate at least the pyrotechnic charge. The pyrotechnic actuator is configured to break the retaining rod.

Abstract: A missile includes a separable nose cone having an ejectable shell cooperating with a support element. The missile has a body with a main longitudinal axis and a nose cone having a shell connected by a rear end thereof to a support element of the missile and defined around a secondary longitudinal axis. The support element has a housing, and the rear end of the shell has a thickness adapted to be received in the housing in a contacting manner. The housing is configured to allow the shell to pivot and to maintain contact while the orientation of the shell is such that the secondary longitudinal axis is at an angle smaller than an ejection angle in relation to said main longitudinal axis, and to end the contact when the secondary longitudinal axis is at an angle higher than or equal to the ejection angle in such a way as to eject the shell from the missile.

Abstract: The missile comprises at least one separable propulsion stage and a terminal vehicle arranged to the front of the separable propulsion stage, said missile being provided at the front with a separable protective fairing comprising at least two individual shells and with a connecting part connected to the missile towards the rear beyond the position of the rear end of the terminal vehicle. The protective fairing is configured such that, when mounted on the missile, it surrounds all of the terminal vehicle and it is connected at the rear end to the connecting part by means of articulated connecting elements.

Abstract: The invention relates to a missile structural wall, in particular for a thermal protection fairing. The structural wall of a missile, in particular of a protective fairing of the missile, comprises a structural part provided with an outer surface and an inner surface, as well as comprising, at least at a front end of the structural part, an outer thermal protection layer on the outer surface and an inner thermal protection layer on the inner surface, the inner layer being made from a material having a density that is between 2 and 20 times lower than that of the material of the outer layer.

Abstract: The invention relates to a missile structural wall, in particular for a thermal protection fairing. The structural wall of a missile, in particular of a protective fairing of the missile, comprises a structural part provided with an outer surface and an inner surface, as well as comprising, at least at a front end of the structural part, an outer thermal protection layer on the outer surface and an inner thermal protection layer on the inner surface, the inner layer being made from a material having a density that is between 2 and 20 times lower than that of the material of the outer layer.

Abstract: The missile comprises at least one separable propulsion stage and a terminal vehicle arranged to the front of the separable propulsion stage, said missile being provided at the front with a separable protective fairing comprising at least two individual shells and with a connecting part connected to the missile towards the rear beyond the position of the rear end of the terminal vehicle. The protective fairing is configured such that, when mounted on the missile, it surrounds all of the terminal vehicle and it is connected at the rear end to the connecting part by means of articulated connecting elements.