An erection device and method for the marine hot launch of a rocket are provided. The erection device includes a launch vessel, a launch pad, an erection assembly, a guide member, a driving cylinder, a sliding member, and a connecting member. The sliding member cooperates with the guide member and is driven by the driving cylinder to move linearly. The connecting member has one end hinged to the erection assembly at a certain angle and the other end connected to the sliding member and is configured to move with the sliding member to drive the erection assembly to be erected on the launch pad. The erection device and method can achieve an effective erection of the rocket for marine hot launch with a desired erection effect and high stability.

An erection device and method for the marine hot launch of a rocket are provided. The erection device includes a launch vessel, a launch pad, an erection assembly, a guide member, a driving cylinder, a sliding member, and a connecting member. The sliding member cooperates with the guide member and is driven by the driving cylinder to move linearly. The connecting member has one end hinged to the erection assembly at a certain angle and the other end connected to the sliding member and is configured to move with the sliding member to drive the erection assembly to be erected on the launch pad. The erection device and method can achieve an effective erection of the rocket for marine hot launch with a desired erection effect and high stability.

Methods and apparatus for a brace for attachment to a launch rail for a projectile for distributing loading of the projectile when supported by the launch rail. A height of the brace can be adjusted to distribute loading. In embodiments, a release mechanism can allow movement of a wear plate during launch of the projectile.

A pneumatic actuator for imparting velocity to a resting object, comprising a fixed member and a ram, the ram having two or more generally elongated ram members,

wherein the fixed member is formed with a base plate having an inlet hole therethrough,

the ram members are formed and disposed concentrically about the center axis so as to lie one within another and to move in a telescopic arrangement,

the innermost one of the ram members is configured to enable it to be driven by any pressurized gas fed through the inlet hole and to drive the object, and each of the other ram members is configured to move only behind the innermost ram member;

the actuator being operative to move the innermost ram member along its entire range of motion and thereby impart velocity to the object.

The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, the control circuitry is configured to activate one or more thrusters that cause the projectile to turn at a certain rate and a certain azimuth.

The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, the control circuitry is configured to activate one or more thrusters that cause the projectile to turn at a certain rate and a certain azimuth.

An effector launch system includes a stowable effector launcher housing having a housing panel configured for coupling with a vehicle, and one or more receptacle brackets movably coupled with the housing panel. The one or more receptacle brackets include one or more effector launcher sockets. The launch system further includes one or more effector launchers. Each effector launcher includes an effector received within an adapter housing. The stowable effector launcher housing is movable between deployed and stowed configurations. In the deployed configuration the one or more receptacle brackets extend from the housing panel and the one or more effector launchers are received within the one or more effector launcher sockets. In the stowed configuration the one or more effector launchers are removed from the one or more effector launcher sockets and the one or more receptacle brackets are stowed along the housing panel.

An effector launch system includes a stowable effector launcher housing having a housing panel configured for coupling with a vehicle, and one or more receptacle brackets movably coupled with the housing panel. The one or more receptacle brackets include one or more effector launcher sockets. The launch system further includes one or more effector launchers. Each effector launcher includes an effector received within an adapter housing. The stowable effector launcher housing is movable between deployed and stowed configurations. In the deployed configuration the one or more receptacle brackets extend from the housing panel and the one or more effector launchers are received within the one or more effector launcher sockets. In the stowed configuration the one or more effector launchers are removed from the one or more effector launcher sockets and the one or more receptacle brackets are stowed along the housing panel.

The invention relates to a ramp of a catapult and to a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) is supported on a ramp (1). The ramp is formed of one or more ramp elements (1a-1m). The ramp element comprises four frame plates, namely two parallel side plates (20a, 20b), a top plate (21) and a bottom plate (22). The frame plates are separate pieces which are connected at fastening points (25) to each other by means of mechanical fastening elements (26).

The invention relates to a launching cylinder of a catapult and to a catapult. The launching cylinder comprises a frame inside which are a pneumatic pressure space for launching purpose and a hydraulic pressure space for returning purpose. The pressure spaces are separated from each other by means of a piston assembly.