The invention discloses an integrated
heat exchanger which is applied to a launching device, the launching device comprises a launching cylinder, the
heat exchanger comprises a plurality of heat exchange pipes, and the heat exchange pipes are distributed in the cylinder wall of the launching cylinder in the circumferential direction; the heat exchange tube comprises a condensation section, a heat insulation section and an
evaporation section which are sequentially connected to form a
closed tube cavity, and the
tube diameter of the
closed tube cavity is gradually reduced in the direction from the condensation section to the
evaporation section; a liquid absorbing core is arranged on the inner wall of the closed
pipe cavity, a working medium capable of conducting
phase change between the gas state and the
liquid state is contained in the closed
pipe cavity, and the liquid absorbing core can absorb the liquid working medium and guide the liquid working medium to flow from the condensation section to the
evaporation section. The heat generated by the unmanned aerial vehicle at the front part of the transmitting tube due to friction can be collected and used for heating the cavity at the
tail part of the transmitting tube, so that
carbon dioxide is prevented from desublimating into a
solid, the temperature of the transmitting tube is balanced, and the
structural integrity of the transmitting tube is ensured. The invention further provides a parameter determination method, a starting transmitting device,
electronic equipment and a computer readable storage medium.