A system and method for cooling a missile includes an assembly of Peltier tiles configured to be reversibly attached to the skin of the missile with the cold sides of the Peltier tiles against the skin. The Peltier tiles are electrically powered to cool a portion of the missile skin. A thermally conductive paste or sheets of a heat conductive material may be placed between the Peltier tiles and missile skin. When the missile is launched, the assembly of Peltier tiles detach from the missile.

Provided in some embodiments is a method of deploying a payload in a subterranean well. The method including advancing a torpedo in a first portion of a wellbore of a subterranean well (the torpedo including a body, a fiber-optic (FO) umbilical that is physically coupled to a surface component, and adapted to unspool from the torpedo as the torpedo advances in the wellbore, and an engine adapted to generate thrust to propel the torpedo), and activating the engine to generate thrust to propel advancement of the torpedo within a second portion of the wellbore such that the FO umbilical is disposed in the second portion of the wellbore.

Provided in some embodiments is a method of deploying a payload in a subterranean well. The method including advancing a torpedo in a first portion of a wellbore of a subterranean well (the torpedo including a body, a fiber-optic (FO) umbilical that is physically coupled to a surface component, and adapted to unspool from the torpedo as the torpedo advances in the wellbore, and an engine adapted to generate thrust to propel the torpedo), and activating the engine to generate thrust to propel advancement of the torpedo within a second portion of the wellbore such that the FO umbilical is disposed in the second portion of the wellbore.

A launcher for launching a flying vehicle, such as a projectile or missile, includes a cutter for cutting a line, such as an umbilical line, that is coupled to the vehicle prior to launch. An example of a line is a tube for providing cooling for onboard components of the vehicle, such as a seeker of the vehicle. The cutter may be part of a mount of the launcher for mounting the line and other components, such as a compressor. The cutter may be configured so that as the vehicle translates relative to the launcher during the initiation of launch, the line moves against the cutter, severing the line. The cutter may retract after severing the line, for example being pulled away from the vehicle (and into the mount) by a spring mechanism.

A launcher for launching a flying vehicle, such as a projectile or missile, includes a cutter for cutting a line, such as an umbilical line, that is coupled to the vehicle prior to launch. An example of a line is a tube for providing cooling for onboard components of the vehicle, such as a seeker of the vehicle. The cutter may be part of a mount of the launcher for mounting the line and other components, such as a compressor. The cutter may be configured so that as the vehicle translates relative to the launcher during the initiation of launch, the line moves against the cutter, severing the line. The cutter may retract after severing the line, for example being pulled away from the vehicle (and into the mount) by a spring mechanism.

A missile cable cutting system includes a tubular housing opened at one end and allowing a missile to be loaded therein, a cable housing fixed to and installed on one surface of the tubular housing and accommodating an umbilical cable protruding from the inside of the missile, a fixing plate installed in the cable housing and allowing the umbilical cable to be inserted between the fixing plate and the cable housing, and a cable cutter installed to be adjacent to the umbilical cable and cutting one side of the umbilical cable when the missile is fired and moved in a traveling direction.

A missile cable cutting system includes a tubular housing opened at one end and allowing a missile to be loaded therein, a cable housing fixed to and installed on one surface of the tubular housing and accommodating an umbilical cable protruding from the inside of the missile, a fixing plate installed in the cable housing and allowing the umbilical cable to be inserted between the fixing plate and the cable housing, and a cable cutter installed to be adjacent to the umbilical cable and cutting one side of the umbilical cable when the missile is fired and moved in a traveling direction.

A Single Armament Control Unit (SACU) that operates a single missile tube as opposed to multiple tubes. The SACU provides for interlock pin and umbilical depression from the housing on the rotation of a single crankshaft controlled by a single motor where the rotor of the motor and the rotational axis of the crankshaft are generally parallel to the missile tube.

A Single Armament Control Unit (SACU) that operates a single missile tube as opposed to multiple tubes. The SACU provides for interlock pin and umbilical depression from the housing on the rotation of a single crankshaft controlled by a single motor where the rotor of the motor and the rotational axis of the crankshaft are generally parallel to the missile tube.

A guide system for securing a torpedo pre-set power cable to move within a torpedo tube is provided. The guide system includes a longitudinal keeper and a guide assembly. The longitudinal keeper secures the power cable and includes a protrusion. A channel of the guide assembly connects to a Torpedo Mount Dispenser such that the channel receives the protrusion with the keeper sliding within and along a length of the channel. An alternate channel connects to a torpedo tube land and is configured to pivot to a stowed position and a deployed position where the channel is configured to receive the protrusion of the keeper such that the keeper slides within and along a length of the channel. When using each of the channels, the power cable can move within the torpedo tube when the protrusion of the keeper with the secured power cable slides within each channel.