CN114229035A - Method for launching a spacecraft with a screw propulsion - Google Patents
Method for launching a spacecraft with a screw propulsion Download PDFInfo
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- CN114229035A CN114229035A CN202111680135.3A CN202111680135A CN114229035A CN 114229035 A CN114229035 A CN 114229035A CN 202111680135 A CN202111680135 A CN 202111680135A CN 114229035 A CN114229035 A CN 114229035A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/409—Unconventional spacecraft propulsion systems
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- Combustion & Propulsion (AREA)
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Abstract
A method of spiral propulsion launching spacecraft is disclosed, including a method of launching a spacecraft celestial in a solar system and a method of launching a spacecraft extrasolar. The key operation is that the initial speed obtained by the rotation or revolution of the spacecraft along with the celestial body is reduced, and then the thrust and the flight direction of the spacecraft are adjusted to be on the same straight line with the gravity of the escaping celestial body, which is the most ideal method. The method is suitable for the spacecraft which has large mass and high orbit or is explored at a longer distance, and is helpful for improving the thrust utilization efficiency of the spacecraft.
Description
Technical Field
The invention relates to a launching method of a spacecraft, in particular to a launching method of a spacecraft with heavy weight and long distance.
Background
In the existing methods for launching spacecraft, the spacecraft is generally launched at a location with a relatively low ground latitude, particularly at a location relatively close to the equator. The method mainly utilizes the relatively large initial velocity generated by the rotation of the earth, and the closer to the equator, the higher the initial velocity of the spacecraft is, so as to save the transmitted energy.
The idea of the method for launching the spacecraft mainly comes from the thought experiment of launching the cannonball on the mountain by Newton, and the cannonball can not fall to the ground as long as enough speed is possessed. The main basis is the following inequality:
wherein G is the universal gravitation 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 centroid of the celestial body.
The spacecraft is launched on the earth, and no clear requirement is made on the flying direction of the spacecraft except for launching the spacecraft to the east; in order to make the spacecraft fly on the sky, the spacecraft is launched to a certain height from the ground, and then the orbit is adjusted to fly.
Such launch methods also often result in easier launch for low mass, low orbit spacecraft; however, for a spacecraft which has a large mass and a high orbit or is used for deep space exploration, a relatively high-power carrier rocket needs to be provided, the requirement on the thrust of an engine of the carrier rocket is relatively high, the force borne by each part of the carrier and the spacecraft is increased along with the increase of the thrust of the rocket, the structural requirement on each part is also improved, and the utilization efficiency of the thrust is difficult to be known at a glance.
In order to overcome the defects, the method for launching the spacecraft in the spiral propulsion mode can more effectively utilize the thrust of the engine, so that the requirement on the power of a carrier rocket is reduced, the stress condition of each structure is also reduced, and a better launching method is provided for the spacecraft which is high in mass and orbit or is explored at a longer distance.
Disclosure of Invention
First, why is the thrust utilization efficiency of the existing spacecraft launch method low?
According to the motion condition of the spacecraft, whether the spacecraft can launch and leave the celestial body can be judged according to the following inequality:
where ω represents the angular velocity of the spacecraft.
To further illustrate the situation and express the angular velocity ω, the present invention needs to refer to patent No. 202110273251.7, which creates a mathematical formula named as electromagnetic fluid vortex power device:
wherein v is velocity, Fx、Fy、Fz，px、py、pzThe resultant force F and the momentum p experienced by the particle are components in the x, y, and z axes, respectively. The bold symbols represent vectors, if not otherwise specified, as follows.
Then there are:
where ω is | ω | (5)
When the value of omega is larger, the spacecraft can be separated from the celestial body more easily to launch. As can be seen from equation (4), when the thrust of the spacecraft is determined and the direction of its momentum is also determined, the greater its momentum is, the corresponding decrease in the angular velocity ω is caused. And the mass and velocity of the spacecraft affect the magnitude of the spacecraft momentum.
Since the thrust of a spacecraft consumes a large amount of fuel, the mass cannot be easily reduced in its momentum, only by reducing the velocity components in the axes. Launching a spacecraft from a position on the earth closer to the equator generally requires that the spacecraft is launched to a certain height away from the ground, the greater the initial velocity obtained by the spacecraft is, but the angular velocity is just reduced, that is, the utilization efficiency of thrust is reduced.
Second, what is the principle of screw propulsion?
In order to better apply the angular velocity of the object also to the propulsion principle, the propulsion capabilities of some phenomena have to be compared.
An iron nail is required to be tightly nailed with a wood plate, the iron nail is usually required to be knocked for a plurality of times by a hammer, but a screw with the same size as the iron nail is used for tightly nailing a same wood plate, the screw is only required to be rotated by a screwdriver, and the screw can be nailed into the wood plate without exerting too much force. The phenomenon in physics can be generally explained by the force spiral theory, that is, a rigid body is analyzed to synthesize the effect of force, and finally, a force and a couple are obtained, and the force and the couple are not 0, and the directions of the force and the couple cannot be perpendicular to each other.
There are also many natural phenomena of rotation, one of which is for example tornado. When a candle burns quietly, flame of the candle is vertically upward and has a certain height, the height can generally reach 2-3 cm, when tornado is created around the candle, the candle is positioned in the center of the tornado, and the angular velocity direction of the tornado is basically the same as the direction of the flame, so that the height of the flame is usually stretched, and the height of the flame can reach three or four times of the usual height.
If the candle is changed into a large amount of gasoline and the strength of the tornado is increased, the height of the flame can be pulled very high, and the situation that the flame has spiral motion can be obviously seen, and the height of the flame can be pulled to dozens of meters or even dozens of meters, which is mainly determined by the intensity of gasoline combustion and the strength of the tornado.
Some toilet flushing designs also design a vortex. The vortex generating effect can lead the center of the water flow to generate larger drawing force, so as to take away the excrement more easily and also play the water-saving effect to a certain extent. Or a drinking water bottle is filled with water, and a period of time is required for directly pouring all the water in the bottle; however, if the water in the bottle is shaken a few times, a vortex is generated in the bottle, and then the bottle cap is opened to pour out the water completely, the required time is only one third of that of directly pouring the water.
In these phenomena, the motion pattern of the object can be generalized as a screw propulsion. However, flame during combustion, water flow vortex in a toilet, and water in a bottle are not rigid bodies, and therefore, it is difficult to analyze the flame vortex and water flow vortex by using the knowledge of the force spiral. In order to better analyze this phenomenon, these materials are considered as individual particles, and it is difficult to analyze the resultant effect of their forces, but as long as they move, velocity and angular velocity are present. The tensor T needs to be introduced here, representing the push rate, and is defined as:
T＝∑ωivjeiej(wherein i, j ═ 1, 2, 3) (6)
Or may be expressed in the form of a matrix:
the physical meaning represented by T is: in the same system, when i equals j, the corresponding TijAbsolute value, i.e. | Tij| represents along eiEase of advancement in direction. When | TijThe larger the value of | is, the easier it is to advance in that direction. The dimensions of the components of T are the same as the acceleration and it is a three-dimensional second-order tensor. Since the ability of substances to propel in different media also varies greatly, it is necessary to define them with the same system, otherwise such a comparison would be difficult; the same system refers to that various physical quantities and elements in a substance are basically the same, and the difference between the speed and the angular speed is allowed, or the third physical quantity related to the two physical quantities is different, so that the comparison is convenient.
Thirdly why is the efficiency of thrust utilization by the method of spiral propulsion launch spacecraft higher?
According to the inequality in equation (2), the spacecraft launches more easily off the celestial body when the angular velocity is larger. In order to obtain the maximum value of the angular velocity, it is necessary to rewrite the expression (4) into an in-line form, that is:
order to
Thus, 1/p is not the reciprocal of p, but a new vector, and this form is used for convenience of representation. Then, the equation (8) can be rewritten as the following cross product relationship:
therefore, when both the magnitude of the resultant force and the magnitude of the momentum are determined, F and 1/p are perpendicular to each other in order to maximize the angular velocity, and there are:
thus, a unique solution cannot be obtained, but the relationship between the force and the momentum can be further clarified, and the method can be roughly divided into two cases, wherein one of the polynomials is a positive number, and the other two polynomials are negative numbers; the second is where the two terms are positive and the remaining one is negative. In the second case, the last term left must be negative and must be relatively large in order for equation (11) to be true, but the force is not minimal, meaning that the efficiency of the force utilization is reduced in this case.
So there is only one scheme where one of the terms is positive and the other two terms are negative, i.e. the other two terms have opposite directions of force and momentum, and the momentum will gradually decrease when the direction of force and momentum is opposite, according to the time-varying rate of momentum being equal to the external force to which it is subjected.
Therefore, in order to satisfy equation (11), the direction of the force and the momentum finally evolve as a result that they are the same, considering that this is a physical quantity of the same study object, the relationship is that the direction of the object motion advances along the direction of the force; in the other two directions in the coordinate system, the force and momentum of the object tend to be 0, and the angular velocity obtained by substituting the relation into the expression (4) tends to be infinite.
When the angular velocity is infinite, this means that the subject can escape from any object, including, of course, a celestial body of very large mass, but provided that the subject first overcomes the gravitational force of the celestial body. Such results are consistent with those obtained from a synthetic analysis of forces in classical physics. It is worth noting that (2) the left r in the inequality is no longer the distance representing the centroid between two objects, but is perpendicular to the direction of motion of the object under study, so there is no definite direction, and its value will tend to be infinite.
The celestial body can rotate, so when the spacecraft is launched on the surface of the celestial body, the spacecraft can be inevitably driven by the rotation of the celestial body, and the spacecraft can also generate an initial speed, wherein the direction of the initial speed is tangential to the surface position of the celestial body where the spacecraft is located, and is vertical to the rotation axis of the celestial body. The spacecraft needs to be on the day, the first task is to be away from the surface of the celestial body and reach a certain height, the direction is just vertical to the direction of the initial speed, and in order to improve the utilization efficiency of the thrust, the initial speed of the spacecraft needs to be reduced.
There are two methods, the first is to select a higher latitude position as the transmitting location, especially the position of two poles is the best. The method is characterized in that the method can be divided into three regions of low latitude, middle latitude and high latitude on the earth according to the latitude, wherein the latitude of 0-30 degrees is the low latitude region, the latitude of 30-60 degrees is the middle latitude region, and the latitude of 60-90 degrees is the high latitude region; another method is to reduce the initial velocity caused by the rotation of the celestial body by using the thrust during the launching of the spacecraft, so that the thrust opposite to the initial velocity of the spacecraft can occur.
When the initial speed of the spacecraft, which is caused by the rotation of the celestial body, is reduced to 0, the flying attitude of the spacecraft can be further adjusted. Because of the existence of the universal gravitation, the spacecraft needs to overcome the force in the launching and launching process, and according to the above discussed results, the thrust borne by the spacecraft, the flying speed of the spacecraft and the gravitation borne by the spacecraft are all concentrated on a straight line, and the directions of the thrust and the speed are the same and are all directed to the spacecraft from the center of mass of the celestial body, so that the utilization efficiency of the thrust can be maximized.
If the spacecraft is launched at the pole of the celestial body, the spacecraft does not need to consider reducing the initial speed during launching and launching, and the thrust direction and the flight direction of the spacecraft are outward along the rotation axis of the celestial body. There is a natural phenomenon in the universe called "black hole jet", and a large number of energetic particles are ejected along the direction of the rotation axis of the black hole and towards the outer sides of the two poles.
And fourthly, the optimal direction of the spiral propulsion type launching spacecraft can be better explained by utilizing the spherical coordinates and the cylindrical coordinates.
Since the formula (4) uses a cartesian coordinate system, the positions of the coordinate axes are equal, and if it is not described in connection with the rotation direction of the celestial body, it is difficult to know which is the optimal emission direction, so the description will be further made in connection with the spherical coordinates and the cylindrical coordinates. This requires two equations from the paper "a simple derivation of velocity and acceleration expressions in cylindrical and spherical coordinates", written by Duming casting, the university of Heyu:
the expression (12) is an expression of an arbitrary speed in a spherical coordinate system, and the expression (13) is an expression of an arbitrary speed in a cylindrical coordinate system, and the vertex of a certain variable is provided with ". multidot..
By first determining a spherical coordinate system
Comprises the following steps:
the corresponding angular velocities are:
its push rate tensor T is:
it is clear that in a system with a spherical coordinate system, the object is along erThe difficulty of the propulsion in the direction is
And the object is at eθAnd eφThe difficulty of pushing in the direction is
When in use
The larger the time, the object is at erThe easier the direction is to advance, the more preferable the direction is to advance when the angle of θ is 0 or π, depending on the meaning of these variables.
Then solving for a cylindrical coordinate system
Comprises the following steps:
the corresponding angular velocities are:
its push rate tensor T is:
it is obvious thatIn the system of the cylindrical coordinate system, the difficulty degree of the object to advance along the z-axis direction is
And edge erAnd eφThe ease of propulsion in both directions is 0, which is not to say that propulsion in both directions is not possible, but is more difficult than in the other directions of the system.
From the analysis results of the spherical coordinate system and the cylindrical coordinate system, and the combination of the autorotation condition of the celestial body, when the spacecraft is far away from the celestial body, the optimal direction is still pushed along the direction of the autorotation axis of the celestial body, and the result is consistent with the analysis in the Cartesian coordinate system. A spherical coordinate system is set on a spacecraft launching site on a phi 0 plane, and a Cartesian coordinate system and a cylindrical coordinate system are converted according to the relation by setting the centroid of the celestial body as the origin, the pointing direction of the rotation axis of the celestial body as the theta 0 axis and the phi 0 plane.
When the spacecraft is launched out of the solar system, the spacecraft is launched on the earth, and the revolution of the earth generates an initial speed to the spacecraft, so that the utilization efficiency of the thrust is reduced. Therefore, in this case, the spacecraft is launched, the center of mass of the sun is set as the origin, the plane where the earth revolves around the sun is set as the plane θ ═ pi/2, that is, the spacecraft is located on the ecliptic plane, and the spherical coordinate system is set on the plane Φ ═ 0, without much relation with the rotation axis of the sun.
Because there are many other celestial bodies on the ecliptic surface, when the spacecraft passes near these celestial bodies, the spacecraft will be disturbed by the gravity of these celestial bodies, and will change the direction of motion, which will prolong the time of launching the spacecraft outside the solar system, so it will launch better along the vertical direction of the ecliptic surface, which means that the ecliptic surface of the solar system should be detached first, and the initial velocity of the spacecraft caused by the revolution of the earth should be reduced.
However, because the gravitational force of the sun is relatively large, when the gravitational force exerted by the sun on the spacecraft is not in the same straight line with the thrust and the flight direction of the spacecraft, the utilization efficiency of the thrust is reduced, so that the two factors must be combined to find a relatively proper included angle between the spacecraft and the ecliptic plane, that is, the flight direction of the spacecraft is intersected with the ecliptic plane. It is of course not necessary that the spacecraft be launched on earth, so celestial bodies are used in the claims instead.
It is worth noting that the gravitational slingshot effect can no longer be utilized by launching the spacecraft out of the solar system by the method, so that the engine of the spacecraft can preferably always provide thrust to overcome the gravitational force exerted by the sun, and the thrust of the engine does not need to be particularly large, but can be used for a long time.
The invention has the advantages that: for the spacecraft which has large mass and high orbit or is explored in a longer distance, a better launching method is provided, and particularly the thrust utilization efficiency of an engine is improved.
Detailed Description
The present invention will be further described with reference to the following examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.
In this embodiment, it is suitable for spacecraft that are to launch large mass, high orbit, or explore at greater distances. Taking the launching on the earth as an example, a launching place is selected first, if other factors such as weather and the like do not need to be considered, a high-latitude area is taken as a first choice, but the launching place is also selected according to the actual situation; after the spacecraft launches to lift off, the thrust direction of the spacecraft or a carrier is regulated, westward thrust can be generated, and the initial speed caused by the rotation of the earth is reduced; when the initial speed is reduced to 0, the thrust direction of the spacecraft or the vehicle is adjusted to make the thrust of the spacecraft, the flight direction of the spacecraft and the gravity of the earth to the spacecraft in the same direction, and the spacecraft is sent to a preset height in such a way; the preset height can exceed the orbit height, then the thrust direction of the spacecraft is adjusted, and the spacecraft is sent into the preset orbit by utilizing the gravity of the earth; if the spacecraft needs to fly to other planets in the solar system, a proper position is found to accelerate the spacecraft to fly away from the earth.
When the spacecraft needs to be launched out of the solar system, the spacecraft can be launched better in a high-latitude area, and the spacecraft can be separated from the ecliptic surface more conveniently; after the spacecraft flies away from the earth for a certain distance, the thrust direction of the spacecraft is adjusted to be opposite to the revolution running direction of the earth, so that the purpose of reducing the initial speed caused by the revolution of the earth is achieved; then adjusting the thrust direction of the spacecraft to enable the spacecraft to fly away from the solar ecliptic plane and reach a preset distance; finally, the thrust direction of the spacecraft is adjusted, so that the thrust of the spacecraft, the flight direction of the spacecraft and the attraction of the sun to the spacecraft are in the same direction, then the spacecraft is accelerated to reach the escape speed of the sun, and the spacecraft can fly out of the solar system basically as long as sufficient time is available.
In other embodiments of the method for launching a spacecraft in a screw propulsion mode, the launch location can be changed accordingly, launch on other celestial bodies can be selected, and different presets can be adopted for the preset height. When the spacecraft is launched out of the solar system, the flying direction of the spacecraft far away from the sun is more flexibly selected.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and substitutions can be made without departing from the technical principle of the present invention, and these modifications and substitutions should also be regarded as the protection scope of the present invention.
Claims (4)
1. A method of propelling a spacecraft spirally, comprising launching the spacecraft into a celestial body in a solar system and launching the spacecraft out of the solar system, characterized in that: when the spacecraft is launched by the celestial body in the solar system, the initial speed of the spacecraft generated along with the rotation of the celestial body can be reduced; when the spacecraft is launched out of the solar system, the initial speed of the spacecraft generated along with the revolution of the celestial body can be reduced.
2. The transmission method according to claim 1, characterized in that: the spacecraft can provide thrust opposite to the initial speed direction 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 be selected to launch the spacecraft, so that the initial speed generated by the rotation of the spacecraft along with the celestial body is reduced.
3. The transmission method according to claim 1, characterized in that: when the spacecraft is launched out of the solar system, the spacecraft can be separated from the ecliptic plane and can provide thrust opposite to the initial speed direction generated by revolution of the celestial body, so that the initial speed generated by the spacecraft along with the revolution of the celestial body is reduced.
4. A transmission method according to claim 1 or 3, characterized in that: when the spacecraft is launched out of the solar system, the flight direction of the spacecraft can intersect the ecliptic plane of the solar system.
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| CN202111680135.3A CN114229035A (en) | 2021-12-25 | 2021-12-25 | Method for launching a spacecraft with a screw propulsion |
| PCT/CN2022/138889 WO2023116520A1 (en) | 2021-12-25 | 2022-12-14 | Spiral-propulsion-type spacecraft launching method |
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| CN202111680135.3A CN114229035A (en) | 2021-12-25 | 2021-12-25 | Method for launching a spacecraft with a screw propulsion |
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| WO2023116520A1 (en) * | 2021-12-25 | 2023-06-29 | 陈晓彬 | Spiral-propulsion-type spacecraft launching method |
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| CN201165915Y (en) * | 2007-03-31 | 2008-12-17 | 陈久斌 | Flywheel engine |
| US10720986B2 (en) * | 2012-12-05 | 2020-07-21 | Ses S.A. | Apparatuses, systems and methods for obtaining information about electromagnetic energy emitted from the earth, such as for locating an interference source on earth |
| CN104139872A (en) * | 2014-08-01 | 2014-11-12 | 姚黎明 | Operating method and structure of unpowered spacecraft capable of hovering in any space |
| CN104309822B (en) * | 2014-11-04 | 2016-04-27 | 哈尔滨工业大学 | A kind of spacecraft single impulse water-drop-shaped based on parameter optimization is diversion track Hovering control method |
| CN113775496A (en) * | 2021-03-01 | 2021-12-10 | 陈晓彬 | Electromagnetic fluid vortex power device |
| CN114229035A (en) * | 2021-12-25 | 2022-03-25 | 陈晓彬 | Method for launching a spacecraft with a screw propulsion |
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| WO2023116520A1 (en) * | 2021-12-25 | 2023-06-29 | 陈晓彬 | Spiral-propulsion-type spacecraft launching method |
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