Improved scheme for thrust device of space rocket

Abstract

The invention relates to an improved scheme for a thrust device of a space rocket. The improved scheme is that groups of eruption tubes E are additionally installed on the exterior walls of a carrier rocket and a spaceship A of a spacecraft for adjusting the deviation degree of the flying path of the spacecraft at any time. On the one hand, energy consumption required to adjust the course after launch of the spacecraft can be saved and on the other hand, the flying state of the spaceship A being separated from the carrier rocket C can be controlled.

Description

technical field [0001] The invention discloses an improvement plan of a space rocket propulsion device, which relates to a space rocket launching method and a control method when flying in the air and in space. Background technique [0002] At present, the methods used by major countries in the world to develop and launch space rockets are all to use a single method of axial propulsion and force to control the direction of flight, so that the flying object is lifted into the air, and in the air or in space. mid flight. To put this phenomenon in a more vivid way, it is as if people are using a chopstick to hold the bottom end of a pencil and push it up in a juggling manner. When a flying object is flying in the air or within the reach of the earth's gravitational force at high altitudes, some unstable factors will often appear, (such as encountering strong winds, or encountering rising air currents, or encountering Changes in the gravitational field caused by the inhomogene...

AI Technical Summary

Problems solved by technology

(Scientists from various countries in the world may have realized this recently and made a "slight improvement"—that is, moving the four launch tubes radially outwards—"binding" on the outer skin of the flying object) In this way, neither Accurate and reliable, low efficiency, but also a lot of fuel wasted; and due to the addition of these numerous precision control equipment, the take-off weight of the flying object is also greatly increased, thereby reducing the loading rate of the internal space of the flying object

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