Danju mercury power method

Abstract

The present application relates to the field of spacecraft propulsion power technology, in particular to a Danzhu mercury power method, the present application is stored in the storage room Danzhu is transmitted to the combustion chamber, and is ignited in the combustion chamber, so that the cinnabar in the combustion chamber will be converted into mercury under chemical reaction, and then the mercury will be reduced to cinnabar again, the reaction and reduction constitute a closed loop system, a large amount of gas will be generated in the combustion chamber in the whole process, and then the gas is discharged through the tail nozzle, so as to generate the thrust to drive the spacecraft flight, realize the start of the spacecraft flight, because the cinnabar in the combustion chamber will be continuously converted between cinnabar and mercury, so that when the cinnabar is used as power fuel, the power fuel is almost not lost, and then the demand of long-term space exploration of the spacecraft can be met.

Description

Technical Field

[0001] This invention relates to the field of spacecraft propulsion technology, and in particular to a method for using danzhu mercury propulsion. Background Technology

[0002] Humanity's exploration of space is becoming increasingly in-depth. Soaring and conquering space requires spacecraft. With the continuous development of aerospace technology, spacecraft technology has made great breakthroughs. Currently, the propulsion power of spacecraft is a key technology for space exploration.

[0003] Most existing space propulsion technologies employ chemical rockets, solid rockets, solar power, and ion propulsion. However, these technologies have limited power and propulsion speed, which cannot meet the requirements of spacecraft for safe, fast, and efficient flight, and thus cannot meet the needs of spacecraft for long-term space exploration.

[0004] Danzhu mercury propulsion technology is a method of achieving spaceflight using anti-gravity technology. Summary of the Invention

[0005] The purpose of this invention is to provide a mercury-based propulsion method that solves the technical problem that most existing aerospace propulsion technologies use chemical rockets, solid rockets, solar energy, and ion propulsion. These technologies have limited power and propulsion speed, which cannot meet the requirements of safe, fast, and efficient flight of spacecraft, and thus cannot meet the needs of spacecraft for long-term space exploration.

[0006] To achieve the above objectives, the present invention provides a danza mercury kinetic method, comprising the following steps: Operate the control panel inside the cockpit of the spacecraft, and have the control panel transmit control commands to the controller; When the controller receives the control command transmitted from the operation panel, the controller controls the engine to start; At this time, the cinnabar stored in the storage chamber is transferred to the combustion chamber and ignited there; Since the cinnabar in the combustion chamber will be converted into mercury under chemical reaction, and the mercury will be reduced back to cinnabar, new material waves will be generated in the combustion chamber during the entire chemical reaction and reduction process. The matter wave generated in the combustion chamber is discharged through the tail nozzle. The matter wave will disrupt the effect of gravity on the spacecraft, allowing the spacecraft to take off and start its flight.

[0007] The combustion chamber and the tailpipe are connected by a sealing ring to seal the gap between them.

[0008] During the flight of the spacecraft, the flight direction needs to be controlled by a navigation system.

[0009] The navigation system includes a light energy detector, an algorithm processing module, a control module, and an adjustment module.

[0010] The control steps of the navigation system are as follows: During the flight of the spacecraft, it receives light energy from the sun, the earth and the moon through a light energy detector, and transmits the received light energy data to the algorithm processing module for processing; After processing, the algorithm processing module transmits the processed data to the control module, allowing the control module to control the adjustment module. By controlling the adjustment module, the adjustment module can provide a strong force under the action of an electromagnetic field to counteract and overcome gravity, thereby causing the spacecraft to levitate and adjust its direction to move quickly, thus realizing the navigation of the spacecraft.

[0011] The mercury forms a closed-loop system based on a relative circulation path and rotates at high speed, which will generate new matter waves. These matter waves will disrupt the effect of gravity on the spacecraft, allowing the spacecraft to take off.

[0012] The spacecraft uses three engines to achieve power control.

[0013] This invention discloses a method for propelling a spacecraft using cinnabar and mercury. The method involves transferring cinnabar stored in a storage chamber to a combustion chamber, where it is ignited. This causes the cinnabar to be converted into mercury through a chemical reaction, and the mercury is then reduced back to cinnabar. This reaction and reduction form a closed-loop system. During this process, a large amount of gas is generated in the combustion chamber, which is then expelled through a tailpipe, generating thrust to propel the spacecraft and initiate its flight. Because the cinnabar in the combustion chamber continuously transforms between cinnabar and mercury, there is almost no loss of fuel when cinnabar is used as propulsion, thus meeting the needs of long-term space exploration. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0015] Figure 1 This is a flowchart of the danzhu mercury kinetic method according to the first embodiment of the present invention. Detailed Implementation

[0017] The embodiments of the present invention are described in detail below. Examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, but should not be construed as limiting the present invention.

[0018] First embodiment: Please see Figure 1 ,in Figure 1 This is a flowchart illustrating the tanzanol mercury kinetic method according to the first embodiment of the present invention. The present invention provides a tanzanol mercury kinetic method, comprising the following steps: S101. Operate the control panel in the cockpit of the spacecraft, and transmit control commands to the controller. S102. When the controller receives the control command transmitted from the operation panel, the controller controls the engine to start. S103. At this time, the cinnabar stored in the storage chamber is transferred to the combustion chamber and ignited in the combustion chamber. S104. Since the cinnabar in the combustion chamber will be converted into mercury under chemical reaction, and the mercury will be reduced back to cinnabar, new material waves will be generated in the combustion chamber during the entire chemical reaction and reduction process. S105. The matter wave generated in the combustion chamber is discharged through the tail nozzle. The matter wave will disrupt the effect of gravity on the spacecraft, allowing the spacecraft to take off and start its flight.

[0019] In this embodiment, the present invention transfers the cinnabar stored in the storage chamber to the combustion chamber and ignites it there. This causes the cinnabar in the combustion chamber to be converted into mercury through a chemical reaction, and then the mercury is reduced back to cinnabar. This reaction and reduction form a closed-loop system. Throughout the process, a large amount of gas is generated in the combustion chamber, which is then discharged through the tail nozzle, thereby generating thrust to propel the spacecraft and initiate its flight. Because the cinnabar in the combustion chamber continuously transforms between cinnabar and mercury, there is almost no loss of fuel when cinnabar is used as propulsion, thus meeting the needs of long-term space exploration.

[0020] The storage chamber includes a storage tank and a flow control pump. The storage tank is used to store the cinnabar. The flow control pump is connected to the storage tank and is used to output the cinnabar and control the flow rate of the cinnabar.

[0021] Secondly, the combustion chamber and the tail nozzle are connected by a sealing ring to seal the gap between the combustion chamber and the tail nozzle. Both the combustion chamber and the tail nozzle are made of metal materials with good thermal conductivity.

[0022] Furthermore, during the flight of the spacecraft, the flight direction of the spacecraft needs to be controlled by a navigation system, which includes a light energy detector, an algorithm processing module, a control module, and an adjustment module.

[0023] Meanwhile, the control steps of the navigation system are as follows: During the flight of the spacecraft, the solar energy detector receives light energy from the sun, earth, and moon, and transmits the received light energy data to the algorithm processing module for processing; after processing, the algorithm processing module transmits the processed data to the control module, allowing the control module to control the adjustment module; by controlling the adjustment module, the adjustment module provides a strong force under the action of the electromagnetic field to counteract and overcome gravity, thereby causing the spacecraft to levitate and adjust its direction for rapid movement, thus achieving the navigation of the spacecraft. After the solar energy detector receives light energy from the sun, earth, and moon, it transmits the received light energy data to the algorithm processing module, where it performs algorithmic processing using the Di Yao algorithm to determine the rocket's specific position in the three coordinate systems of the sun, earth, and moon. The algorithm processing module then transmits the processed data to the control module, allowing the control module to control the adjustment module based on the processed data. This causes the adjustment module to provide a strong force under the action of the electromagnetic field to counteract and overcome gravity, thereby causing the spacecraft to levitate and adjust its direction for rapid movement, thus achieving the navigation of the spacecraft.

[0024] In addition, the mercury forms a closed-loop system according to the relative circulation path and rotates at high speed, which will cause new matter waves. These matter waves will disrupt the effect of gravity on the spacecraft, allowing the spacecraft to take off.

[0025] Finally, the spacecraft uses three engines to achieve power control, one engine for launch (by changing the electrodes for descent), one engine for atmospheric flight, and one engine for spaceflight.

[0026] When using the cinnabar-mercury propulsion method of this embodiment, the control panel in the cockpit of the spacecraft is operated to transmit control commands to the controller. Upon receiving the control commands from the control panel, the controller starts the engine. At this time, cinnabar stored in the storage tank is output to the combustion chamber via the flow control pump. Simultaneously, the combustion chamber can control the flow rate of the output cinnabar. After the cinnabar is transmitted to the combustion chamber, it is ignited. Since the cinnabar in the combustion chamber is converted to mercury through a chemical reaction, and the mercury is gradually reduced back to cinnabar, a new matter wave is generated in the combustion chamber during the entire chemical reaction and reduction process. This matter wave is then dissipated through the tail nozzle, and the matter wave disrupts the gravitational effect on the spacecraft. The spacecraft is launched and put into flight using three engines: one for launch (by changing electrodes for descent), one for atmospheric flight, and one for spaceflight. During flight, the spacecraft receives solar energy from the sun, earth, and moon via a light energy detector and transmits the data to an algorithm processing module. The processed data is then transmitted to a control module, which controls an adjustment module. This adjustment module, under the influence of an electromagnetic field, provides a strong force to counteract gravity, levitating the spacecraft and allowing it to adjust its direction for rapid movement, thus achieving navigation control.

[0027] In summary, this invention transfers cinnabar stored in the storage chamber to the combustion chamber and ignites it there. This causes the cinnabar in the combustion chamber to be converted into mercury through a chemical reaction, and then the mercury is reduced back to cinnabar. This reaction and reduction form a closed-loop system. During this process, a large amount of gas is generated in the combustion chamber, which is then expelled through the exhaust nozzle, generating thrust to propel the spacecraft and initiate its flight. Because the cinnabar in the combustion chamber continuously transforms between cinnabar and mercury, there is almost no loss of fuel when cinnabar is used as propulsion. This satisfies the needs of long-term space exploration and solves the technical problem that existing aerospace propulsion technologies, such as chemical rockets, solid rocket propulsion, solar power, and ion propulsion, have limited power and propulsion speed, failing to meet the safety, speed, and efficiency requirements of spacecraft during flight and thus hindering long-term space exploration.

[0028] The above-disclosed embodiments are merely one or more preferred embodiments of this application and should not be construed as limiting the scope of this application. Those skilled in the art can understand that all or part of the processes for implementing the above embodiments and equivalent changes made in accordance with the claims of this application still fall within the scope of this application.

Claims

1. A mercury-based method for cinnabar mining, characterized in that, Includes the following steps: Operate the control panel inside the cockpit of the spacecraft, and have the control panel transmit control commands to the controller; When the controller receives the control command transmitted from the operation panel, the controller controls the engine to start; At this time, the cinnabar stored in the storage chamber is transferred to the combustion chamber and ignited there; Since the cinnabar in the combustion chamber will be converted into mercury under chemical reaction, and the mercury will be reduced back to cinnabar, new material waves will be generated in the combustion chamber during the entire chemical reaction and reduction process. The matter wave generated in the combustion chamber is discharged through the tail nozzle. The matter wave will disrupt the effect of gravity on the spacecraft, allowing the spacecraft to take off and start its flight.

2. The danzhu mercury-powered method as described in claim 1, characterized in that, The combustion chamber and the tailpipe are connected by a sealing ring to seal the gap between them.

3. The danzhu mercury-powered method as described in claim 1, characterized in that, During the flight of the spacecraft, the flight direction needs to be controlled by a navigation system.

4. The danzhu mercury-powered method as described in claim 3, characterized in that, The navigation system includes a light energy detector, an algorithm processing module, a control module, and an adjustment module.

5. The danza-mercury dynamic method as described in claim 4, characterized in that, The control steps of the navigation system are as follows: During the flight of the spacecraft, it receives light energy from the sun, the earth and the moon through a light energy detector, and transmits the received light energy data to the algorithm processing module for processing; After processing, the algorithm processing module transmits the processed data to the control module, allowing the control module to control the adjustment module. By controlling the adjustment module, the adjustment module can provide a strong force under the action of an electromagnetic field to counteract and overcome gravity, thereby causing the spacecraft to levitate and adjust its direction to move quickly, thus realizing the navigation of the spacecraft.

6. The danzhu mercury-powered method as described in claim 1, characterized in that, The mercury forms a closed-loop system according to a relative circulation path and rotates at high speed, which will cause new matter waves. These matter waves will disrupt the effect of gravity on the spacecraft, allowing the spacecraft to take off.

7. The danzhu mercury-powered method as described in claim 1, characterized in that, The spacecraft uses three engines to achieve power control.

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