An adjustable pitch air-breathing dual-stage ion engine

Abstract

The present invention provides an adjustable-distance air-breathing dual-stage ion engine, which relates to the technical field of ion engines, and includes a first-stage Feld-Brown effect ion thruster and a final-stage Feld-Brown effect ion thruster, wherein a screw hole is provided through the side surface of the first-stage Feld-Brown effect ion thruster. The present invention, by providing a first-stage Feld-Brown effect ion thruster, a final-stage Feld-Brown effect ion thruster, a bolt and an elongated waist hole, can achieve the spacing adjustment and fixing function between the first-stage Feld-Brown effect ion thruster and the final-stage Feld-Brown effect ion thruster through the structural combination of the bolt and the elongated waist hole, thereby reducing the electric field strength between the collector at the end of the first-stage thruster and the emitter at the front end of the final-stage thruster, suppressing the ion backflow in the dual-stage ion engine, and adjusting the first-stage Feld-Brown effect ion thruster and the final-stage Feld-Brown effect ion thruster to the most reasonable spacing.

Description

Technical Field

[0001] The invention relates to the technical field of ion engines, and in particular to an adjustable-pitch air-breathing double-stage ion engine. Background Art

[0002] There are many forms of ion thrusters based on the Befeld-Brown effect, such as the simple levitation machine and the ion-propelled aircraft of MIT. Their common feature is that their most basic thruster modules are asymmetric capacitors based on the Befeld-Brown effect, which rely on this structure to ionize and accelerate ambient gases or particles to generate thrust. The common advantages of these propulsion methods are: they do not require the consumption of traditional chemical propellants, and as long as there is electricity (from solar energy or nuclear power), thrust can be generated permanently, that is, the endurance time is long, but their disadvantages are: due to their small thrust and low efficiency, they are not suitable for large-scale engineering applications. When the single stage is changed to a When two-stage or even multi-stage propulsion is changed, the thrust output can be increased in theory. However, ion backflow is easily generated in the transition part between the two poles, making the series connection invalid. Since the ions at the end of the first-stage thruster of the engine cannot be completely neutralized by the collector plate, a part of the charged particles are pulled back in the opposite direction by the collector, resulting in a decrease in the thrust increase efficiency after the two-stage series connection. Increasing the distance between the two-stage thrusters, thereby reducing the electric field strength between the collector at the end of the first-stage thruster and the emitter at the front end of the final-stage thruster, is an effective measure to suppress ion backflow in a two-stage ion engine. However, the most reasonable distance between the two-stage thrusters of the engine is often not accurately determined. Summary of the invention

[0003] The purpose of the present invention is to solve the shortcomings of the prior art and to propose an adjustable pitch air-breathing dual-stage ion engine.

[0004] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an adjustable pitch air-breathing two-stage ion engine, comprising a first-stage Feldbrown effect ion thruster and a final-stage Feldbrown effect ion thruster, wherein a screw hole is penetrated through the side surface of the first-stage Feldbrown effect ion thruster, and a bolt is threadedly connected to the inner side of the screw hole, and an elongated waist hole is penetrated through the side surface of the final-stage Feldbrown effect ion thruster, wherein the elongated waist hole and the screw hole are located on the same horizontal line, and the elongated waist hole is sleeved on the outer surface of the bolt.

[0005] In order to realize the connection function between the first-level Field-Brown effect ion thruster and the collection encryption inlet, the improvement of the present invention is that a trumpet-shaped air intake collection encryption inlet is provided at the front end of the first-level Field-Brown effect ion thruster, and the first-level Field-Brown effect ion thruster is fixedly connected to the trumpet-shaped air intake collection encryption inlet by screws.

[0006] In order to limit the composition of the Laval tail nozzle, the improvement of the present invention is that the rear end of the final-stage Field-Brown effect ion thruster is equipped with a Laval tail nozzle, and the Laval tail nozzle is composed of a middle convergent throat and a tail divergent nozzle.

[0007] In order to more effectively convert the internal pressure of the tail supersonic airflow into the engine thrust output, the present invention has the following improvements: the intermediate convergent throat and the tail divergent nozzle are fixedly connected, and the intermediate convergent throat is located at the front end of the tail divergent nozzle.

[0008] In order to provide the prerequisite for the limiting work, the present invention has the following improvements: the inner front end of the last-stage Feld-Brown effect ion thruster is provided with a limiting boss, and the rear end of the first-stage Feld-Brown effect ion thruster is provided with a terminal.

[0009] In order to realize the limiting function between the first-level Feld-Brown effect ion thruster and the last-level Feld-Brown effect ion thruster, the improvement of the present invention is that the end is located between the limiting bosses, and the limiting bosses are in contact with the end.

[0010] In order to further supplement the available working fluid of the final-stage ion thruster, the present invention has the following improvements: a side suction air inlet is provided between the first-stage Feld-Brown effect ion thruster and the final-stage Feld-Brown effect ion thruster, and the side suction air inlet is composed of a front end shell and a recess.

[0011] In order to construct an air intake structure for a side-suction air intake duct, the improvements of the present invention are that the front end shell is installed at the front end of the final-stage Field-Brown effect ion thruster, the recess is opened on the upper surface of the end, the shape of the front end shell is a hollow trapezoid, and the front end shell is sleeved on the outer surface of the end.

[0012] In order to realize the control function of the first-level Field-Brown effect ion thruster and the final-level Field-Brown effect ion thruster, the improvements of the present invention are that the outer surface of the first-level Field-Brown effect ion thruster is equipped with a first-level control handle and a first-level control panel, and the outer surface of the final-level Field-Brown effect ion thruster is equipped with a final-level control handle and a final-level control panel.

[0013] Compared with the prior art, the advantages and positive effects of the present invention are:

[0014] 1. The present invention, by providing a first-stage Field Brown effect ion thruster, a final-stage Field Brown effect ion thruster, bolts and an elongated waist hole, can achieve the spacing adjustment and fixing function between the first-stage Field Brown effect ion thruster and the final-stage Field Brown effect ion thruster through the structural combination of the bolts and the elongated waist hole, thereby reducing the electric field strength between the collector at the end of the first-stage thruster and the emitter at the front end of the final-stage thruster, inhibiting ion backflow in the dual-stage ion engine, and adjusting the first-stage Field Brown effect ion thruster and the final-stage Field Brown effect ion thruster to the most reasonable spacing.

[0015] 2. The present invention, by providing a trumpet-shaped air intake collection and encryption inlet, a side suction air intake duct, a front end shell, a recess, a Laval tail nozzle, an intermediate contraction throat, and a tail expansion nozzle, can realize the function of high-density air intake under high-speed conditions through the trumpet-shaped air intake collection and encryption inlet, so that the air-breathing ion engine obtains more available working medium, and further supplements the available working medium of the final stage ion thruster through the structural combination of the side suction air intake duct, the front end shell, the recess, and the Laval tail nozzle, and finally improves the overall working medium flow rate and thrust output of the engine, and the internal pressure of the tail supersonic airflow is more effectively converted into the engine thrust output through the structural combination of the Laval tail nozzle, the intermediate contraction throat, and the tail expansion nozzle. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A schematic diagram of the overall components of an adjustable pitch air-breathing dual-stage ion engine proposed by the present invention;

[0017] Figure 2 The present invention provides a schematic diagram of the structure of the first-stage Field-Brown effect ion thruster of an adjustable-pitch air-breathing dual-stage ion engine;

[0018] Figure 3 The present invention provides a partial structural diagram of the final-stage Field-Brown effect ion thruster of an adjustable-pitch air-breathing dual-stage ion engine;

[0019] Figure 4 The present invention provides a side-view cross-sectional schematic diagram of an adjustable-pitch air-breathing dual-stage ion engine.

[0020] Legend:

[0021] 1. First-stage Feld-Brown effect ion thruster; 2. Last-stage Feld-Brown effect ion thruster; 3. Laval tail nozzle; 4. Trumpet-shaped air intake collection and encryption inlet; 5. Long waist hole; 6. Bolt; 7. Notch; 8. Limiting boss; 9. End; 10. Side suction air intake duct; 11. Front end shell; 12. Middle contraction throat; 13. Tail expansion nozzle. DETAILED DESCRIPTION

[0022] In order to more clearly understand the above-mentioned purpose, features and advantages of the present invention, the present invention is further described below in conjunction with the accompanying drawings and embodiments. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict.

[0023] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways than those described herein. Therefore, the present invention is not limited to the specific embodiments of the following disclosure.

[0024] Embodiment 1

[0025] See also Figure 1-4The present invention provides a technical solution: an adjustable pitch air-breathing two-stage ion engine, comprising a first-stage Feld-Brown effect ion thruster 1 and a final-stage Feld-Brown effect ion thruster 2, wherein the outer surface of the first-stage Feld-Brown effect ion thruster 1 is provided with a first-stage control handle and a first-stage control panel, and the outer surface of the final-stage Feld-Brown effect ion thruster 2 is provided with a final-stage control handle and a final-stage control panel. The purpose of this design is to realize the control function of the first-stage Feld-Brown effect ion thruster 1 and the final-stage Feld-Brown effect ion thruster 2, and the final-stage control handle and the final-stage control panel are provided. The inner front end of the first-stage Field Brown effect ion thruster 2 is provided with a limiting boss 8, and the rear end of the first-stage Field Brown effect ion thruster 1 is provided with a terminal 9, which is located between the limiting bosses 8, and the limiting boss 8 fits with the terminal 9. This design is to limit the activity trajectory of the first-stage Field Brown effect ion thruster 1 and the final-stage Field Brown effect ion thruster 2, and limit the degrees of freedom between the two-stage thrusters of the engine, except that the first-stage Field Brown effect ion thruster 1 and the final-stage Field Brown effect ion thruster 2 can only move. In addition to performing axial sliding forward and backward pitch adjustment movement to achieve the pitch adjustment function, this design method can also prevent the unstable connection between the first-level Field Brown effect ion thruster 1 and the final-level Field Brown effect ion thruster 2. The side surface of the first-level Field Brown effect ion thruster 1 is penetrated with a screw hole, and the inner side of the screw hole is threadedly connected with a bolt 6. This design is to achieve the function of adjusting the driving depth of the bolt 6. The side surface of the final-level Field Brown effect ion thruster 2 is penetrated with an elongated waist hole 5, and the elongated waist hole 5 and the screw hole are located at the same level. The flat line and the long waist hole 5 are sleeved on the outer surface of the bolt 6. By sliding the bolt 6 on the inner side of the long waist hole 5, the spacing adjustment function of the first-stage Field Brown effect ion thruster 1 and the final-stage Field Brown effect ion thruster 2 can be realized, and the fixation is completed by further driving the bolt 6, so as to reduce the electric field strength between the collector at the end 9 of the first-stage thruster and the emitter at the front end of the final thruster, suppress the ion backflow in the dual-stage ion engine, and adjust the first-stage Field Brown effect ion thruster 1 and the final-stage Field Brown effect ion thruster 2 to the most reasonable spacing.

[0026] Embodiment 2

[0027] See also Figure 2-4The front end of the first-level Feld-Brown effect ion thruster 1 is provided with a trumpet-shaped air intake collection and encryption inlet 4, and the first-level Feld-Brown effect ion thruster 1 is fixedly connected to the trumpet-shaped air intake collection and encryption inlet 4 by screws. Through the trumpet-shaped air intake collection and encryption inlet 4, the function of high-density air intake under high-speed state is realized, so that the air-breathing ion engine obtains more available working medium. The rear end of the last-level Feld-Brown effect ion thruster 2 is equipped with a Laval tail nozzle 3, and the Laval tail nozzle 3 is composed of an intermediate contraction throat 12 and a tail expansion nozzle 13. The intermediate contraction throat 12 and the tail expansion nozzle 13 are fixedly connected, and the intermediate contraction throat 12 is located at the front end of the tail expansion nozzle 13. Through the Laval tail nozzle 3 and the intermediate contraction throat 12 The structural combination of the rear expansion nozzle 13 can more effectively convert the internal pressure of the tail supersonic airflow into the engine thrust output. A side suction air inlet 10 is arranged between the first-stage Feld-Brown effect ion thruster 1 and the last-stage Feld-Brown effect ion thruster 2. The side suction air inlet 10 is composed of a front end shell 11 and a recess 7. The front end shell 11 is installed at the front end of the last-stage Feld-Brown effect ion thruster 2. The recess 7 is opened on the upper surface of the end 9. The shape of the front end shell 11 is a hollow trapezoid. The front end shell 11 is sleeved on the outer surface of the end 9. This design is to construct the air intake structure of the side suction air inlet 10, further supplement the available working fluid of the last-stage ion thruster, and finally improve the overall working fluid flow rate and thrust output of the engine.

[0028] Working principle: During the assembly process, the activity trajectories of the first-level Field Brown effect ion thruster 1 and the final-level Field Brown effect ion thruster 2 are first limited by the limiting boss 8 and the end 9, thereby limiting the degrees of freedom between the two-stage thrusters of the engine. In addition to allowing the first-level Field Brown effect ion thruster 1 and the final-level Field Brown effect ion thruster 2 to only perform axial sliding forward and backward pitch adjustment movements to achieve the pitch adjustment function, this design method can also prevent the unstable connection between the first-level Field Brown effect ion thruster 1 and the final-level Field Brown effect ion thruster 2. Then, by sliding the bolt 6 on the inner side of the elongated waist hole 5, the spacing adjustment function between the first-level Field Brown effect ion thruster 1 and the final-level Field Brown effect ion thruster 2 can be achieved, and the fixation is completed by further driving the bolt 6. The electric field strength between the collector at the end 9 of the first-stage thruster and the emitter at the front end of the final-stage thruster is reduced, the ion backflow in the dual-stage ion engine is suppressed, and the first-stage Feld-Brown effect ion thruster 1 and the final-stage Feld-Brown effect ion thruster 2 are adjusted to the most reasonable spacing. During operation, the trumpet-shaped air intake collection and encryption entrance 4 is used to realize the function of high-density air intake at high speed, so that the air-breathing ion engine obtains more available working medium. The structural combination of the side suction air intake duct 10, the front end shell 11, the recess 7, and the Laval tail nozzle 3 further supplements the available working medium of the final-stage ion thruster, and finally improves the overall working medium flow rate and thrust output of the engine. The internal pressure of the tail supersonic airflow is more effectively converted into engine thrust output through the structural combination of the Laval tail nozzle 3, the middle contraction throat 12, and the tail expansion nozzle 13.

[0029] The above description is only a preferred embodiment of the present invention and does not limit the present invention in other forms. Any technician familiar with the profession may use the technical content disclosed above to change or modify it into an equivalent embodiment with equivalent changes and apply it to other fields. However, any simple modification, equivalent change and modification made to the above embodiment based on the technical essence of the present invention without departing from the content of the technical solution of the present invention still falls within the protection scope of the technical solution of the present invention.

Claims

1. An adjustable pitch air-breathing two-stage ion engine, comprising a first-stage Feld-Brown effect ion thruster (1) and a final-stage Feld-Brown effect ion thruster (2), characterized in that: The side surface of the first-level Feldbron effect ion thruster (1) is penetrated with a screw hole, and the inner side of the screw hole is threadedly connected with a bolt (6); the side surface of the final-level Feldbron effect ion thruster (2) is penetrated with an elongated waist hole (5), and the elongated waist hole (5) is located on the same horizontal line as the screw hole, and the elongated waist hole (5) is sleeved on the outer surface of the bolt (6); the front end of the first-level Feldbron effect ion thruster (1) is provided with a trumpet-shaped air intake collection and encryption inlet (4); the first-level Feldbron effect ion thruster (2) is provided with a trumpet-shaped air intake collection and encryption inlet (4); The thruster (1) is fixedly connected to a trumpet-shaped air intake collection and encryption inlet (4) by screws; a Laval tail nozzle (3) is installed at the rear end of the final-stage Feld-Brown effect ion thruster (2); the Laval tail nozzle (3) is composed of a middle contraction throat (12) and a tail expansion nozzle (13); a side suction air intake duct (10) is arranged between the first-stage Feld-Brown effect ion thruster (1) and the final-stage Feld-Brown effect ion thruster (2); the side suction air intake duct (10) is composed of a front end shell (11) and a recess (7).

2. According to the adjustable pitch air-breathing two-stage ion engine of claim 1, the middle contracting throat (12) and the tail diverging nozzle (13) are fixedly connected, and the middle contracting throat (12) is located at the front end of the tail diverging nozzle (13).

3. The adjustable pitch air-breathing dual-stage ion engine according to claim 1, characterized in that: The inner front end of the final-stage Feld-Brown effect ion thruster (2) is provided with a limiting boss (8), and the rear end of the first-stage Feld-Brown effect ion thruster (1) is provided with a terminal (9).

4. The adjustable pitch air-breathing dual-stage ion engine according to claim 3, characterized in that: The end (9) is located between the limiting bosses (8), and the limiting bosses (8) are in close contact with the end (9).

5. The adjustable pitch air-breathing dual-stage ion engine according to claim 1, characterized in that: The front end housing (11) is mounted on the front end of the final-stage Field-Brown effect ion thruster (2). The opening (7) is opened on the upper surface of the end (9), and the front end housing (11) is in the shape of a hollow trapezoid. The front end housing (11) is sleeved on the outer surface of the end (9).

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