Screw propulsion type spacecraft launching method
A technology for helical propulsion and spacecraft, applied in the field of spacecraft launch, can solve the problems that the thrust utilization efficiency is difficult to understand at a glance, and the thrust requirements are high, and achieve the effect of improving the thrust utilization efficiency.
Pending Publication Date: 2022-03-25
陈晓彬
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Problems solved by technology
[0007] Such a launch method often also makes it easier to launch small-mass, low-orbit spacecraft; but for large-mass, high-orbit or deep space exploration spacecraft, it is necessary to provide a relatively high-power launch vehicle, which is for The requirements for the thrust of the launch vehicle engine are relatively high, and with the increase of the thrust of the rocket, the force on the various components of the vehicle and the spacecraft will also increase. Difficult to understand at a glance
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[0073] The present invention will be further described below in conjunction with embodiment. The following examples are used to illustrate the present invention, but are not intended to limit the protection scope of the present invention.
[0074] In this embodiment, it is more suitable for launching large-mass, high-orbit or long-distance exploration spacecraft. Take the launch on the earth as an example. First, select the launch location. If you don’t need to consider other factors such as weather, high-latitude areas are the first choice, but you should also choose according to the actual situation; Or the thrust direction of the vehicle, there can be a westward thrust to reduce the initial velocity brought by the earth's rotation; when the initial velocity is basically reduced to 0, then adjust the thrust direction of the spacecraft or the vehicle to make the spacecraft The thrust of the spacecraft, the flight direction of the spacecraft and the gravitational force of the...
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The invention discloses a method for launching a spacecraft in a screw propulsion mode. The method comprises a method for launching the spacecraft in a celestial body in a solar system and a method for launching the spacecraft out of the solar system. The key operation is that the initial speed obtained by rotation or revolution of the spacecraft along with the celestial body is reduced, then the thrust of the spacecraft is adjusted, and the flight direction and the gravity of the spacecraft suffered from the escaping celestial body are on the same straight line, which is the most ideal method. The method is suitable for large-mass, high-orbit or longer-distance exploration spacecrafts, and is helpful for improving the thrust utilization efficiency of the spacecrafts.
Description
technical field [0001] The invention relates to a method for launching a spacecraft, in particular to a method for launching a spacecraft with a large weight and a long distance. Background technique [0002] In the existing methods for launching a spacecraft, the spacecraft is usually launched at a position with a relatively low latitude on the ground, especially a position relatively close to the equator. The main thing is to use the relatively large initial velocity generated by the rotation of the earth. The closer the position is to the equator, the greater the initial velocity of the spacecraft, so as to save launch energy. [0003] The idea of this method of launching a spacecraft is mainly derived from Newton’s thought experiment of launching a cannonball on a high mountain. As long as it has enough speed, the cannonball will not fall to the ground. The main basis is the following inequality: [0004] [0005] Among them, G is the gravitational constant, M is ...
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Login to View More IPC IPC(8): B64G1/00B64G1/40
CPCB64G1/002B64G1/409
Inventor 陈晓彬
Owner 陈晓彬