Aerospace vehicle system

An aerospace vehicle system, comprising:

• a rocket having two or more stages;
• each of said two or more stages having a respective rocket engine;
• a satellite detachably fastened to the rocket;
• an electronic device installed inside the satellite;
• a signal line electrically connecting said electronic device located inside the satellite, said signal line extending from inside the satellite to outside of the satellite to the respective rocket engines in each of said stages of said rocket,
• a radio device installed inside the satellite;
• and
• a plurality of sensors, including at least one acceleration sensor installed inside the satellite and pressure and thermo sensors adapted to the rocket engines wherein
• the electronic device is connected to said radio device and said each of said plurality of sensors through the signal line,
• the electronic device controls the rocket to carry the satellite into outer space, said electronic device controlling each respective rocket engine in each of said two or more stages in accordance with signals obtained from said sensors, including from said pressure sensor and said thermo sensor,
• the electronic device controls the satellite in outer space after the satellite is detached from the rocket,
• the signal line is configured to divide into a satellite portion and a rocket portion, and
• prior to detachment of said satellite from said rocket, the electronic device controls the rocket through the signal line in accordance with (1) signals obtained from the plurality of sensors inside said satellite without any signals being obtained from any acceleration sensors within any of the two or more stages of said rocket and (2) commands received from the radio device, wherein said electronic device does not control the satellite based on said at least one acceleration sensor until after detachment of said satellite from said rocket and wherein before said detachment of said satellite from said rocket, said electronic device only controls engines or thrusters that are not controlled by said electronic device after said detachment of said satellite from said rocket,
• wherein the satellite is detachable from said rocket by being mounted within a fairing that is configured to physically separate from the rocket portion, and
• wherein said satellite is contained inside said fairing prior to detachment, whereby the satellite cannot be controlled to impart any vehicle motion prior to detachment.