CN114776547B - Fuel-free satellite propulsion device and propulsion method - Google Patents

Abstract

The invention provides a fuel-free satellite propulsion device and a propulsion method. The invention can capture the lean air in the space through the actions of the gas collecting chamber, the ionization chamber and the ion accelerator, provide fuel for the aircraft, ionize the gas in a way of combining heat, electricity and magnetism, ionize the gas by the ionization chamber by utilizing an electric field and a magnetic field generated by cutting a magnetic induction line by a closed coil, prevent negative ions from entering the ion accelerator by Du Bangmo in the ionization chamber, and better achieve the effect of ion separation.

Description

A fuel-free satellite propulsion device and propulsion method

Technical Field

The present invention relates to the field of building technology, and in particular to a fuel-free satellite propulsion device and a propulsion method.

Background technique

When a satellite is in orbit, if it needs to change its orbit, it generally needs to use thrusters to provide power. Existing propulsion methods generally use liquid fuel as power, but this propulsion method requires the storage of liquid fuel, which increases the weight of the satellite.

Summary of the invention

The purpose of the present invention is to provide a fuel-free satellite propulsion device and propulsion method, which is a new type of power device for realizing efficient conversion of satellite ion thrusters.

According to one object of the present invention, the present invention provides a fuel-free satellite propulsion device, including a gas collection chamber, an ionization chamber and an ion accelerator, wherein the gas collection chamber is connected to the ionization chamber, and the ionization chamber is connected to the ion accelerator.

Furthermore, an air collecting fan is provided at the front end of the gas collecting chamber, a heating resistance wire is provided inside the gas collecting chamber, and a solar cell panel is provided outside the gas collecting chamber, and the solar cell panel is connected to the heating resistance wire.

Furthermore, two pairs of N-S electromagnets, a vertical sliding mechanism, an annular metal closed coil and a DuPont membrane are arranged in the ionization chamber, and an external power supply is connected to the ionization chamber.

Furthermore, an S pole of an electromagnet is placed on a side of the ionization chamber connected to the gas collection chamber, an N pole of an electromagnet is placed on a side of the ionization chamber connected to the ion accelerator, and the annular metal closed coil is placed on the vertical sliding mechanism.

Furthermore, the upper and lower ends of the vertical sliding mechanism are respectively connected to horizontal sliding mechanisms, and the horizontal sliding mechanism can adjust the angle θ between the annular metal closed coil and the central axis of the ionization chamber, and the adjustment range of the angle θ is 60° to 90°.

Furthermore, the negative pole of the external power supply is connected to the S pole of the electromagnet, and the positive pole of the external power supply is connected to the N pole of the electromagnet.

Furthermore, the magnitude of the charge generated in the ionization chamber is calculated according to the following formula:

Where Q is the charge, in coulombs; m is the mass of the circular metal closed coil, in g; v is the speed of the circular metal closed coil, in m/s; g is the gravitational acceleration, which is taken as 9.8; d is the diameter of the circular metal closed coil, in m; θ is the angle between the circular metal closed coil and the central axis of the ionization chamber; t is the sliding time of the circular metal closed coil; _R0 is the resistance value of the circular metal closed coil; _R1 is the external resistor.

Furthermore, the DuPont membrane is a cation proton exchange membrane.

Furthermore, the ion accelerator is connected to the ionization chamber through channel 2, and the efficiency of ion collection is calculated by the following formula:

Wherein, m is the correction factor of air temperature and pressure; d is the distance between the electrodes in the ionization chamber, in m; q is the air ionization density per unit time, in esu·cm ^-3 ·s ^-1 ; and V is the plate voltage, in V.

According to another object of the present invention, the present invention provides a propulsion method of a fuel-free satellite propulsion device, comprising the following steps:

S1, the gas enters the gas collection chamber through the gas collecting fan, and the gas temperature is increased by the heating resistance wire;

S2, the heated gas enters the ionization chamber, the annular metal closed coil moves along the vertical sliding mechanism to cut the magnetic flux lines, so that the gas is ionized, the negative ions move toward the S pole of the electromagnet, and the positive ions move toward the N pole of the electromagnet. The positive ions enter the ion accelerator through the DuPont membrane; after the negative ions move to the S pole of the electromagnet, they flow out of the ionization chamber and neutralize with the positive ions.

The technical solution of the present invention can capture the rarefied air in space and provide fuel for the aircraft through the functions of the gas collection chamber, the ionization chamber and the ion accelerator, and ionize the gas by combining heat, electricity and magnetism. The ionization chamber uses the electric field and magnetic field generated by the closed coil cutting the magnetic flux lines to ionize the gas, and the DuPont membrane in the ionization chamber prevents negative ions from entering the ion accelerator, thereby better achieving the effect of ion separation.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

FIG1 is a schematic structural diagram of an embodiment of the present invention;

In the figure, 1. gas collecting chamber; 2. gas collecting chamber; 3. gas collecting chamber; 4. channel one; 5. channel two; 6. gas collecting fan; 7. heating resistor wire; 8. solar cell panel; 9. electromagnet S pole; 10. electromagnet N pole; 11. annular metal closed coil; 12. vertical sliding mechanism; 13. horizontal sliding mechanism; 14. external power supply; 15. DuPont film; 16. discharge channel.

Detailed ways

The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as limiting the present invention.

In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined. In addition, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

Example 1

As shown in Figure 1, a fuel-free satellite propulsion device includes a gas collection chamber 1, an ionization chamber 2 and an ion accelerator 3. The gas collection chamber 1 is connected to the ionization chamber 2 through a channel 1 4, and the ionization chamber 2 is connected to the ion accelerator 3 through a channel 2 5.

An air collecting fan 6 is provided at the front end of the gas collecting chamber 1 , a heating resistor 7 is provided inside the gas collecting chamber 1 , and a solar cell panel 8 is provided outside the gas collecting chamber 1 , and the solar cell panel 8 is connected to the heating resistor 7 .

A DuPont membrane 15 is provided at one end of the ion chamber near the ion accelerator 3. The DuPont membrane 15 is a cation proton exchange membrane. The DuPont membrane 15 is a proton exchange membrane, namely a "cation proton exchange membrane"; the model of the DuPont membrane is NAFION-117.

The end of the ionization chamber near the ionization chamber 2 is used for the discharge channel 16 for the discharge of negative ions. The side of the ionization chamber 2 connected to the gas collection chamber 1 is placed with the electromagnet S pole 9, the side of the ionization chamber 2 connected to the ion accelerator 3 is placed with the electromagnet N pole 10, and the annular metal closed coil 11 is placed on the vertical sliding mechanism 12. The upper and lower ends of the vertical sliding mechanism 12 are respectively connected to the horizontal sliding mechanism 13, and the horizontal sliding mechanism 13 can adjust the angle θ between the annular metal closed coil 11 and the central axis of the ionization chamber 2, and the adjustment range of the angle θ is 60° to 90°.

The ionization chamber 2 is externally connected to an external power supply 14 , the negative pole of the external power supply 14 is connected to the S pole 9 of the electromagnet, and the positive pole of the external power supply 14 is connected to the N pole 10 of the electromagnet.

The magnitude of the charge generated in the ionization chamber 2 is calculated according to the following formula:

Where Q is the charge, in coulombs; I is the current, in A; m is the mass of the circular metal closed coil, in g; v is the speed of the circular metal closed coil, in m/s; g is the gravitational acceleration, which is 9.8; d is the diameter of the circular metal closed coil, in m; θ is the angle between the circular metal closed coil and the central axis of the ionization chamber; t is the sliding time of the circular metal closed coil; _R0 is the resistance value of the circular metal closed coil; _R1 is the external resistor.

The ion accelerator 3 is connected to the ionization chamber 2 through the channel 5. The efficiency of ion collection is calculated by the following formula:

Wherein, m is the correction factor of air temperature and pressure; d is the distance between the electrodes in the ionization chamber, in m; q is the air ionization density per unit time, in esu·cm ^-3 ·s ^-1 ; and V is the plate voltage, in V.

A propulsion method for a fuel-free satellite propulsion device comprises the following steps:

S1, the gas enters the gas collecting chamber 1 through the gas collecting fan 6, and the gas temperature is increased by the heating resistor 7 to improve the ionization efficiency of the gas;

S2, the heated gas enters the ionization chamber 2, the annular metal closed wire 11 moves along the vertical sliding mechanism 12 to cut the magnetic flux lines, so that the gas is ionized, the negative ions move toward the S pole of the electromagnet 9, and the positive ions move toward the N pole of the electromagnet 10. The positive ions enter the ion accelerator through the DuPont membrane; after the negative ions move to the S pole of the electromagnet, they flow out of the ionization chamber through the discharge channel 16 and neutralize with the positive ions.

The technical solution of the present invention can capture the rarefied air in space and provide fuel for the aircraft through the functions of the gas collection chamber 1, the ionization chamber 2 and the ion accelerator 3, ionize the gas by combining heat, electricity and magnetism, ionize the gas by using the electric field and magnetic field generated by cutting the magnetic flux lines by the annular metal closed coil 11, and prevent negative ions from entering the ion accelerator by using the DuPont film 15, so as to better achieve the effect of ion separation.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents. However, these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims (7)

1. A fuel-free satellite propulsion device, comprising a gas collection chamber, an ionization chamber and an ion accelerator, wherein the gas collection chamber is communicated with the ionization chamber, and the ionization chamber is communicated with the ion accelerator; two pairs of N-S electromagnets, a vertical sliding mechanism, an annular metal closing coil and Du Bangmo are arranged in the ionization chamber, and an external power supply is externally connected to the ionization chamber;

An electromagnet S pole is arranged on one side of the ionization chamber, which is communicated with the gas collection chamber, an electromagnet N pole is arranged on one side of the ionization chamber, which is communicated with the ion accelerator, and the annular metal closing coil is arranged on the vertical sliding mechanism; the upper end and the lower end of the vertical sliding mechanism are respectively connected with a horizontal sliding mechanism, the horizontal sliding mechanism can adjust an included angle theta between the annular metal closing coil and the central axis of the ionization chamber, and the adjusting range of the included angle theta is 60-90 degrees.

2. The fuel-free satellite propulsion device of claim 1, wherein a gas collecting fan is arranged at the front end of the gas collecting chamber, a heating resistance wire is arranged inside the gas collecting chamber, a solar panel is arranged outside the gas collecting chamber, and the solar panel is connected with the heating resistance wire.

3. The fuel-free satellite propulsion device of claim 1, wherein a negative pole of the external power source is connected to the electromagnet S pole and a positive pole of the external power source is connected to the electromagnet N pole.

4. The fuel-free satellite propulsion device of claim 1, wherein the magnitude of the charge generated in the ionization chamber is calculated according to the formula:

Wherein Q is charge, unit coulomb; i is current, and the unit is A; m is the mass of the annular metal closed coil, and the unit g; v is the speed of movement of the annular metal closing coil in m/s; g is gravity acceleration, 9.8 is taken; d is the diameter of the annular metal closed coil, and the unit is m; θ is the included angle between the annular metal closed coil and the central axis of the ionization chamber; t is the sliding time of the annular metal closed coil; r ₀ is the resistance value of the annular metal closed coil; r ₁ is an external resistor.

5. The fuelled satellite propulsion plant according to claim 1 wherein Du Bangmo is a cationic proton exchange membrane.

6. The fuel-free satellite propulsion device of claim 1, wherein the ion accelerator is in communication with the ionization chamber via a channel, and the efficiency of ion collection is calculated by the following equation:

Wherein m is an air temperature and air pressure correction factor; d is the electrode spacing of the ionization chamber, and the unit is m; q is the ionization density of air in unit time, esu cm ^－3·s^－1; v is the plate voltage, and the unit is V.

7. The propulsion method of a fuel-free satellite propulsion apparatus of claim 1, comprising the steps of:

s1, enabling gas to enter a gas collection chamber through a gas collection fan, and enabling the temperature of the gas to rise through a heating resistance wire;

s2, the heated gas enters an ionization chamber, an annular metal closing coil moves along a vertical sliding mechanism to cut a magnetic induction line, so that the gas is ionized, negative ions move towards the S pole of an electromagnet, positive ions move towards the N pole of the electromagnet, and positive ions enter an ion accelerator through Du Bangmo; the negative ions flow out of the ionization chamber to neutralize with the positive ions after moving to the S pole of the electromagnet.