WO2023116520A1

WO2023116520A1 - Spiral-propulsion-type spacecraft launching method

Info

Publication number: WO2023116520A1
Application number: PCT/CN2022/138889
Authority: WO
Inventors: 陈晓彬
Original assignee: 陈晓彬
Priority date: 2021-12-25
Filing date: 2022-12-14
Publication date: 2023-06-29
Also published as: CN114229035A

Abstract

Disclosed herein is a spiral-propulsion-type spacecraft launching method, which comprises a method for launching a spacecraft from a celestial body in the solar system and a method for launching a spacecraft toward the outside of the solar system. Key operations comprise: first, reducing the initial velocity of a spacecraft that is obtained as same self-rotates or revolves with a celestial body; and then adjusting, to be in the same straight line, the thrust and flight direction of the spacecraft and the gravitational force of an escaped celestial body to which the spacecraft is subjected, and such method is the most ideal method. The present invention is applicable to a spacecraft which has a large mass, which is at a high orbit, or which performs more distant exploration; and is helpful in improving the utilization efficiency of the thrust of a spacecraft.

Description

A method of propulsively launching a spacecraft

technical field

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

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 to the equator, the greater the initial velocity of the spacecraft, so as to save the energy for launch.

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:

Among them, G is the gravitational constant, M is the mass of the celestial body, m is the mass of the spacecraft, v is the linear velocity of the spacecraft, and r is the distance between the spacecraft and the center of mass of the celestial body.

When launching a spacecraft on the earth, there is no clear requirement for the flying direction of the spacecraft except for launching the spacecraft to the east; Altitude, and then adjust for orbital flight.

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.

In order to overcome the above-mentioned defects, the screw propulsion method for launching a spacecraft of the present invention can utilize the thrust of the engine more effectively, thereby reducing the requirements for the power of the launch vehicle, and also reducing the stress of each structure. For large-mass, high-orbit or Spacecraft for longer-distance exploration, providing a better launch method.

Contents of the invention

1. Why are the existing spacecraft launching methods relatively inefficient for thrust utilization?

According to the movement of the spacecraft, whether the spacecraft can launch and leave the celestial body can also be judged according to the following inequality:

where ω represents the angular velocity of the spacecraft.

In order to further explain the situation and express the angular velocity ω, this invention needs to quote a mathematical formula with the patent number 202110273251.7 and the invention name "Electromagnetic Fluid Vortex Power Device":

Among them, v is the velocity, F _x , F _y , F _z , p _x , py _y , p _z are the components of the resultant force F and momentum p on the x, y, and z axes of the particle respectively. Unless otherwise specified, bold symbols represent vectors, the same below.

Then there are:

where ω＝|ω| (5)

When the value of ω is larger, the spacecraft can be separated from the celestial body, and it is easier to launch. It can be seen from formula (4) that when the thrust of the spacecraft has been determined and its momentum direction has been determined, the greater its momentum, the corresponding decrease in angular velocity ω will result. What affects the momentum of the spacecraft is its mass and velocity.

Since the thrust of the spacecraft needs to consume a lot of fuel, its mass cannot be easily reduced in its momentum, so it can only be reduced by reducing the velocity components in each coordinate axis. To launch a spacecraft from a position closer to the equator on the earth, it is usually necessary to launch the spacecraft to a certain height from the ground first. The initial velocity it obtains is greater, but it happens to cause the angular velocity to decrease, that is, the use of thrust Reduced efficiency.

2. What is the principle of spiral propulsion?

In order to better apply the angular velocity of objects to the propulsion principle, it is necessary to compare the propulsion capabilities of some phenomena.

An iron nail, if you want to fasten a wooden board, you usually need to use a hammer to hit it a few more times, but with a screw of the same size as this iron nail, to fasten a same wooden board, you only need to use a screwdriver Turning the screw will drive the screw into the board without applying too much force. This phenomenon in physics can usually be explained by the force helix theory, that is, after a rigid body analyzes the effect of combined forces, it finally obtains a force and a force couple, and both the force and the force couple are not 0, and the direction between them cannot be perpendicular to each other.

There are many natural phenomena that rotate, for example, tornado is one of them. When a candle is burning peacefully, its flame will rise vertically and have a certain height, generally reaching 2-3 cm long. When a tornado is created around the candle, and the candle is in the center of the tornado The direction of the angular velocity of the center and the tornado is also basically the same as that of the flame, so that the height of the flame will usually be stretched to three or four times the usual height.

If this candle is replaced with a large amount of gasoline, and the intensity of the tornado is increased, the height of the flame can be pulled very high, and it can be clearly seen that the flame is in a spiral motion, and the height of the flame can be stretched Reaching more than ten meters or even tens of meters mainly depends on the intensity of gasoline burning and the intensity of the tornado.

Some toilets have flush designs that also feature whirlpools. The effect of generating a vortex can make the center of the water flow generate a greater pumping force, and it is easier to take away the excrement, which also has the effect of saving water to a certain extent. Or fill a drinking water bottle with water, and it will take a while to pour all the water in the bottle directly; but if you shake the water in the bottle a few more times to create a vortex inside, then open the bottle cap and pour all the water The time required to pour out is generally only one-third of that of direct pouring.

In these phenomena, the motion of objects can be summarized as spiral propulsion. But the burning flame, the water vortex in the toilet, and the water in the bottle are not rigid bodies, so it is difficult to use the knowledge of the force spiral to analyze. In order to better analyze this phenomenon, these substances are regarded as individual particles. Of course, it is very difficult to analyze the combined effect of their forces, but as long as they move, there will be speed and angular velocity. . Here we need to introduce tensor T, which represents the propulsion rate, and define it as:

T=∑ω ⁱ v ^j e _i e _j (where i, j=1, 2, 3) (6)

Or it can be expressed in matrix form:

The physical meaning represented by T is: in the same system, when i=j, the corresponding absolute value of T _ij , that is, |T _ij | indicates the difficulty of advancing along the e _i direction. When the value of |T _ij | is larger, it means that it is easier to advance in this direction. The dimensions of each component of T are the same as the acceleration, and it is a three-dimensional second-order tensor. Since the propelling ability of matter in different media is also very different, it must be defined by the same system, otherwise the comparison will be very difficult; and the same system means that the various physical quantities and elements in the matter are basically the same, and the allowable speed It is convenient to compare if there is a difference with the angular velocity, or the third physical quantity related to these two physical quantities is different.

3. Why is the propulsion method of launching a spacecraft more efficient in terms of thrust?

According to the inequality in (2), when the angular velocity is greater, the spacecraft is easier to launch away from the celestial body. In order to find the maximum value of angular velocity, formula (4) needs to be rewritten into the form of determinant, that is:

make

Therefore, 1/p does not represent the reciprocal of p, but a new vector, which is used for convenience. Then formula (8) can be rewritten as the following relational formula of cross product:

Therefore, in the case where the resultant force and momentum have been determined, in order to maximize the angular velocity, F and 1/p are perpendicular to each other, as follows:

In this way, a unique solution cannot be obtained, but the relationship between force and momentum can be further clarified, which can be roughly divided into two situations, one is that one of the fractions is positive, and the other two are negative; the second One is that two of the fractions are positive and the remaining one is negative. In the second case, the remaining last item must be a negative number and must be relatively large to make equation (11) valid, but the force at this time is not the smallest, which means that in this scheme, the force utilization efficiency is also decreasing.

So there is only one solution, that is, one of the fractions is positive, and the other two are negative, that is, the directions of the force and momentum of the other two are opposite. According to the change rate of momentum to time is equal to the external force it receives, When the force and momentum are in opposite directions, the momentum will gradually decrease.

Therefore, in order to satisfy formula (11), the final evolution result of force and momentum is that their directions are the same. Considering that this is the physical quantity of the same research object, this relationship is that the direction of motion of the object advances along the direction of force; In the other two directions in the coordinate system, the force and momentum of the object will tend to 0. Substituting this relationship into equation (4), the obtained angular velocity tends to infinity.

When the angular velocity is infinite, it means that the research object can escape from any object, including celestial bodies with very large masses, but the premise is that the research object must first overcome the gravitational force of this celestial body. Such a result is consistent with the result obtained by the compositional analysis of force in classical physics. It is worth noting that the r on the left side of the inequality (2) no longer represents the distance between the centers of mass of two objects, but is perpendicular to the direction of motion of the research object, so there is no definite direction, of course its value will also tend to infinity.

Since the celestial body will produce rotation, when the spacecraft is launched on its surface, it will inevitably be driven by its rotation, and the spacecraft will also produce an initial velocity. The direction of this initial velocity is the same as the surface of the celestial body where the spacecraft is located The position is tangent and perpendicular to the rotation axis of the celestial body. The spacecraft needs to go to the sky. The first task is to stay away from the surface of the celestial body and reach a certain height. This direction is just perpendicular to the direction of the initial velocity. In order to improve the utilization efficiency of the thrust, the initial velocity of the spacecraft needs to be reduced.

There are two methods. The first is to choose a location with a higher latitude as the launch location, especially the location at the poles is the best. According to the latitude on the earth, it can be divided into three types: low, middle and high latitude regions. The latitude of 0°～30° is the low latitude region, 30°～60° is the middle latitude region, and 60°～90° is the high latitude region. Restricted by objective conditions, it is impossible to completely select the launch site of the spacecraft at the poles, but the preferred choice is still in the high latitude area. When the spacecraft is launched on other celestial bodies, the high latitude area is also divided according to this method; in addition One method is to use the thrust to reduce the initial velocity caused by the rotation of the celestial body during the launch of the spacecraft, so that the thrust opposite to the initial velocity of the spacecraft can appear.

When the initial velocity of the spacecraft due to the rotation of the celestial body decreases to 0, the flight attitude of the spacecraft can be further adjusted. Due to the existence of gravitation, the spacecraft needs to overcome this force during launch. According to the results discussed above, the thrust received by the spacecraft, the flying speed of the spacecraft, and the gravitational force of the spacecraft received by the celestial body are all Concentrate on a straight line, and the thrust and speed are in the same direction, all pointing from the center of mass of the celestial body to the spacecraft, so that the utilization efficiency of the thrust can be maximized.

If the spacecraft is launched at the pole of the celestial body, then there is no need to consider reducing its initial velocity during launch, and its thrust direction and flight direction are all along the rotation axis of the celestial body. There is a natural phenomenon called "black hole jet" in the universe. A large number of high-energy particles are ejected toward the outside of the two poles along the direction of the black hole's rotation axis.

4. Utilizing spherical coordinates and cylindrical coordinates, it can better explain the best direction of the helical propulsion launching spacecraft.

Since the formula (4) adopts the Cartesian coordinate system, the position of each coordinate axis is equal, if it is not explained in conjunction with the rotation direction of the celestial body, it is difficult to figure out which one is the best launch direction, so now It is necessary to further combine spherical coordinates and cylindrical coordinates to illustrate the situation. This requires quoting two formulas from the paper "A Simple Derivation of Velocity and Acceleration Expressions in Cylindrical Coordinate System and Spherical Coordinate System" published by Du Mingzhu of Hetao University:

Among them, Equation (12) is the expression of arbitrary velocity in the spherical coordinate system, and Equation (13) is the expression of arbitrary velocity in the cylindrical coordinate system. A variable with a “.” guide.

First find the spherical coordinate system

have:

Then the corresponding angular velocity is:

Then its propulsion rate tensor T is:

Obviously, in the system of the spherical coordinate system, the difficulty of pushing the object along the e _r direction is

The difficulty of pushing the object in the direction of e _θ and e _φ is equal to

when

The larger the value, the easier it is for the object to propel in the e _r direction. According to the meanings represented by these variables, when the angle of θ is 0 or π, it is the best propulsion direction.

Then find the cylindrical coordinate system

have:

Then the corresponding angular velocity is:

Then its propulsion rate tensor T is:

Obviously, in the system of the cylindrical coordinate system, the degree of difficulty for the object to advance along the z-axis is

The difficulty of advancing along the e _r and e _φ directions is 0, which does not mean that it cannot be advanced in these two directions, but compared with other directions of the system, it is more difficult to advance.

From the analysis results of the spherical coordinate system and the cylindrical coordinate system, combined with the situation of the rotation of the celestial body, when the spacecraft is going to be far away from the celestial body, the best direction is to advance along the direction of the rotation axis of the celestial body. This result is consistent with that in Descartes The analysis in the child coordinate system is consistent. To set the center of mass where the celestial body is located as the origin, the direction of the celestial body's rotation axis is the θ=0 axis, and the launch site of the spacecraft is on the φ=0 plane, and the spherical coordinate system, the Cartesian coordinate system and the cylindrical coordinate system are also set according to this Relationship conversion.

When a spacecraft is launched outside the solar system, since it is launched on the earth, the revolution of the earth will also generate an initial velocity for the spacecraft, which will reduce the efficiency of thrust utilization. Therefore, launching a spacecraft in this case has little to do with the rotation axis of the sun. The center of mass of the sun is set as the origin, and the plane where the earth revolves around the sun is set as the θ=π/2 plane, which is the same as the ecliptic plane. Coincidence, the position of the earth is set on the φ=0 plane, and the spherical coordinate system is set.

Since there are many other celestial bodies on the ecliptic plane, if the spacecraft passes near these celestial bodies, it will be more or less disturbed by the gravitational force of these celestial bodies, thus changing the direction of motion, which will prolong the time for the spacecraft to launch outside the solar system , so it is better to launch along the vertical direction of the ecliptic plane, which also means to leave the ecliptic plane of the solar system first, and to reduce the initial velocity brought by the earth's revolution to the spacecraft.

However, due to the relatively strong gravitational force of the sun, when the gravitational force exerted by the sun on the spacecraft is not on the same line as the thrust and flight direction of the spacecraft, the utilization efficiency of the thrust will be reduced. Therefore, it is necessary to combine these two factors to find The spacecraft and the ecliptic plane form a relatively suitable angle, that is, the flight direction of the spacecraft intersects the ecliptic plane. Of course, the spacecraft is not necessarily launched on the earth, so it is replaced by a celestial body in the claims.

It is worth noting that the gravitational slingshot effect can no longer be used to launch a spacecraft outside the solar system using the method described above, so it is best for the engine of the spacecraft to provide thrust all the time to overcome the gravitational force exerted by the sun. The thrust of this engine does not need Very large, but can be used for a long time.

The invention has the advantages of providing a more optimal launch method for spacecraft with large mass, high orbit or longer-distance exploration, especially improving the thrust utilization efficiency of the engine.

Detailed ways

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.

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 earth on it are all in the same direction, and the spacecraft is sent to a predetermined height in this way; this predetermined height can exceed the orbital height, and then adjust the thrust direction of the spacecraft, And make good use of the gravity of the earth to send the spacecraft into the predetermined orbit; if the spacecraft wants to fly to other planets in the solar system, then find a suitable position to accelerate away from the earth.

When it is necessary to launch a spacecraft outside the solar system, it is better to choose a high-latitude region to launch, which is more conducive to the spacecraft’s departure from the ecliptic plane; The direction of revolution is opposite to achieve the purpose of reducing the initial velocity brought by the earth's revolution; then adjust the thrust direction of the spacecraft so that the spacecraft flies away from the ecliptic plane of the solar system and reach a predetermined distance; finally adjust the thrust direction of the spacecraft , so that the thrust of the spacecraft, the flight direction of the spacecraft and the gravitational force of the sun on it are all in the same direction, and then the spacecraft is accelerated to the escape velocity to the sun. As long as there is enough time, it can basically fly out of the solar system.

In other specific embodiments of the method for propulsively launching a spacecraft of the present invention, in order to be able to adapt to different usage requirements, the launch site can be changed accordingly, or it can be launched on other celestial bodies, and it can also be used for the predetermined height. different presets. When launching a spacecraft outside the solar system, the flight direction of the spacecraft away from the sun is more flexible.

The above is only a preferred embodiment of the present invention, it should be pointed out that for those of ordinary skill in the art, without departing from the technical principles of the present invention, some improvements and replacements can also be made, and these improvements and replacements are also possible. It should be regarded as the protection scope of the present invention.

Claims

A method for propulsively launching a spacecraft, including a method for launching a spacecraft from a celestial body in the solar system and a method for launching a spacecraft outside the solar system, characterized in that: when launching a spacecraft from a celestial body in the solar system, the The initial velocity generated by the spacecraft with the rotation of the celestial body; when the spacecraft is launched outside the solar system, the initial velocity generated by the spacecraft's revolution with the celestial body can be reduced.
The launch method according to claim 1, characterized in that: the spacecraft can provide a thrust in the opposite direction to the initial velocity generated by the rotation of the celestial body in the ecliptic plane of the solar system, and the high latitude position of the celestial body can also be selected to The purpose of launching a spacecraft is to reduce the initial velocity of the spacecraft as the celestial body rotates.
The launch method according to claim 1, characterized in that: when the spacecraft is launched outside the solar system, the spacecraft can break away from the ecliptic plane, and can provide a thrust opposite to the direction of the initial velocity generated by the revolution of the celestial body, so as to reduce the The initial velocity produced by the orbiting spacecraft with the celestial body.
The launching method according to claim 1 or 3, characterized in that: when the spacecraft is launched outside the solar system, the flight direction of the spacecraft can intersect with the ecliptic plane of the solar system.