Abstract: The deployment device may include a support piece, the deployable element, in particular a handle, may be rotatably mounted on said support piece and being connected by means of an elastic element to the support piece. The deployable element may include at least one pin capable of being moved along a curved guide of the support piece and adopting one or both of the two stable positions, respectively, in two housings provided in the support piece. The stable positions may respectively correspond to a stowed position and a deployed position of the deployable element. The guide and the elastic element may be configured to generate an automatic deployment of the deployable element to the deployed position as soon as the deployable element is subjected by an operator to a rotation having an angle greater than or equal to an unlocking angle.

Abstract: A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

Abstract: The deployment device may include a support piece, the deployable element, in particular a handle, may be rotatably mounted on said support piece and being connected by means of an elastic element to the support piece. The deployable element may include at least one pin capable of being moved along a curved guide of the support piece and adopting one or both of the two stable positions, respectively, in two housings provided in the support piece. The stable positions may respectively correspond to a stowed position and a deployed position of the deployable element. The guide and the elastic element may be configured to generate an automatic deployment of the deployable element to the deployed position as soon as the deployable element is subjected by an operator to a rotation having an angle greater than or equal to an unlocking angle.

Abstract: A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

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.