The present invention relates a safety ignition device for a high altitude dual pulse motor according to the present invention, and can prevent accidental ignition of an ignition device or a propulsion engine while efficiently using a space by installing the safety ignition device in front of a combustion pipe, increase the reliability of ignition, and maintain the air tightness of the inside of the propulsion engine and the ignition device even in a high altitude environment.

The present invention relates a safety ignition device for a high altitude dual pulse motor according to the present invention, and can prevent accidental ignition of an ignition device or a propulsion engine while efficiently using a space by installing the safety ignition device in front of a combustion pipe, increase the reliability of ignition, and maintain the air tightness of the inside of the propulsion engine and the ignition device even in a high altitude environment.

A solid rocket motor propellant grain arrangement may comprise a case, a propellant grain disposed within the case, and an integrated rocket motor aging sensor disposed outward from the propellant grain, wherein the integrated rocket motor aging sensor is configured to measure data corresponding to a plurality of distinct locations of the propellant grain. The integrated rocket motor aging sensor may comprise a resistive screen matrix (RSM).

The present invention relates a safety ignition device for a high altitude dual pulse motor according to the present invention, and can prevent accidental ignition of an ignition device or a propulsion engine while efficiently using a space by installing the safety ignition device in front of a combustion pipe, increase the reliability of ignition, and maintain the air tightness of the inside of the propulsion engine and the ignition device even in a high altitude environment.

The present invention relates a safety ignition device for a high altitude dual pulse motor according to the present invention, and can prevent accidental ignition of an ignition device or a propulsion engine while efficiently using a space by installing the safety ignition device in front of a combustion pipe, increase the reliability of ignition, and maintain the air tightness of the inside of the propulsion engine and the ignition device even in a high altitude environment.

A compact safety ignition device for a dual pulse motor capable of preventing accidental ignition of an ignition device includes a housing which forms an accommodation space and coupled to a front port of a combustion tube. Primary and secondary circuit portions mounted inside the housing for generating ignition signals for a primary and secondary propellant, respectively. A primary ignition device mounted at one end of the housing and electrically connected to the primary circuit portion and accommodated in the combustion tube. A secondary bulkhead initiator mounted inside the housing and electrically connected to the secondary circuit portion. The primary ignition device includes a primary detonation portion electrically connected to the primary ignition device and includes a primary bulkhead initiator electrically connected to the primary detonation portion at a protrusion protruding from an end of the primary detonation portion.

A compact safety ignition device for a dual pulse motor capable of preventing accidental ignition of an ignition device includes a housing which forms an accommodation space and coupled to a front port of a combustion tube. Primary and secondary circuit portions mounted inside the housing for generating ignition signals for a primary and secondary propellant, respectively. A primary ignition device mounted at one end of the housing and electrically connected to the primary circuit portion and accommodated in the combustion tube. A secondary bulkhead initiator mounted inside the housing and electrically connected to the secondary circuit portion. The primary ignition device includes a primary detonation portion electrically connected to the primary ignition device and includes a primary bulkhead initiator electrically connected to the primary detonation portion at a protrusion protruding from an end of the primary detonation portion.

A multipulse rocket motor includes a secondary pulse, fired after a primary pulse of the motor, that includes a thermal insulator having channels therein, around a propellant grain of the secondary pulse. The channels provide a way to equalize pressure on the propellant grain of the secondary pulse, to reduce stresses on the propellant grain as the primary pulse is operating. The channels may extend along most or substantially all of a length of the secondary pulse. The channels may be defined by material strips of thermal insulator material evenly circumferentially spaced around the secondary pulse.

A multi-pulse propulsion system includes at least one pulse chamber containing at least one propellant for igniting during at least one pulse of the multi-pulse propulsion system, at least one additional pulse chamber containing at least one additional propellant for igniting during at least one additional pulse of the multi-pulse propulsion system, and at least one passive fuzing system configured to initiate the at least one additional pulse. The at least one passive fuzing system includes a sensor and an igniter. The sensor is configured to sense an environmental condition and/or a ballistic condition. The igniter is configured to provide a stimulus that causes ignition of the at least one additional propellant in response to the sensor sensing that the environmental condition and/or the ballistic condition has reached or exceeded one or more threshold values.

A multi-pulse propulsion system includes at least one pulse chamber containing at least one propellant for igniting during at least one pulse of the multi-pulse propulsion system, at least one additional pulse chamber containing at least one additional propellant for igniting during at least one additional pulse of the multi-pulse propulsion system, and at least one passive fuzing system configured to initiate the at least one additional pulse. The at least one passive fuzing system includes a sensor and an igniter. The sensor is configured to sense an environmental condition and/or a ballistic condition. The igniter is configured to provide a stimulus that causes ignition of the at least one additional propellant in response to the sensor sensing that the environmental condition and/or the ballistic condition has reached or exceeded one or more threshold values.