Reduction of rocket jet stream dispersion

A system for reducing dispersion in a launched rocket cause by jet-stream misalignment, the system comprising:

• a processing unit and a rocket spinning mechanism, the processing unit comprising a computer processor and computer memory and being configured to control operation of the rocket spinning mechanism, the rocket spinning mechanism being configured, responsive to instructions received from the processing unit, to spin the rocket around a longitudinal axis of the rocket;
• the processing unit is configured for reducing jet-stream misalignment, to:
• obtain information indicative of a division of total operation time of the rocket engine into a first time period and a second time period wherein an impulse that is generated during the first time period is at least approximately the same as an impulse generated during the second time period;
• measure a period of time that is approximately equal to the first time period starting from time of activation of the rocket engine;
• and
• upon termination of the period of time, generate instructions for the rocket spinning mechanism to rotate the rocket around a longitudinal axis thereof, wherein the rocket spinning mechanism rotates the rocket according to the instructions received;
• measure an angle of rotation;
• and
• generate additional instructions for the rocket spinning mechanism to stop rotation of the rocket once approximately 180° rotation is completed, wherein the rocket spinning mechanism stops rotation of the rocket according to the additional instructions received.

A non-transitory program storage device readable by a computer processor, tangibly embodying a program of instructions executable by the computer processor to perform a method of reducing dispersion of a launched rocket caused by jet-stream misalignment, the method comprising:

• obtaining information indicative of a division of total operation time of a rocket engine of the rocket into a first time period and a second time period, wherein an impulse that is generated during the first time period is at least approximately the same as an impulse generated during the second time period;
• measuring a period of time that is approximately equal to the first time period starting from time of activation of the rocket engine;
• upon termination of the period of time, generating instructions for causing the rocket to rotate around a longitudinal axis of the rocket;
• measuring an angle of rotation;
• and
• once approximately 180° rotation of the rocket is completed, generating additional instructions for causing the rocket to stop rotating.

A rocket with reduced dispersion from an intended flight path caused by jet-stream misalignment, the rocket comprising a subsystem for reducing jet-stream misalignment in the rocket after launch, the subsystem comprising:

• a processing unit and a rocket spinning mechanism, the processing unit comprising a computer processor and computer memory and configured to control the rocket spinning mechanism;
• the rocket spinning mechanism is configured, responsive to instructions received from the processing unit, to spin the rocket around a longitudinal axis of the rocket;
• the processing unit is configured for reducing jet-stream misalignment, to:
• obtain information indicative of a division of total operation time of the rocket engine into a first time period and a second time period, wherein an impulse that is generated during the first time period is at least approximately the same as an impulse generated during the second time period;
• measure a period of time in accordance with the first time period starting from time of activation of the rocket engine;
• and
• upon termination of the period of time, generate instructions to the rocket spinning mechanism to rotate the rocket around a longitudinal axis thereof, wherein the rocket spinning mechanism rotates the rocket according to the instructions received;
• measure an angle of rotation;
• and
• generate additional instructions to the rocket spinning mechanism to stop rotation of the rocket once approximately 180° rotation is completed, wherein the rocket spinning mechanism stops rotation of the rocket according to the additional instructions received.