A zero-energy aerospace propellant management and emission reduction device

Abstract

The present invention discloses a zero-energy aerospace propellant management and emission reduction device, which is characterized by comprising a tank, an inner blade separation system, a screen channel separation system and a collection control device including a pressure control valve; the tank is placed in the outermost layer and is in a shell shape as a whole; the inner blade separation system is connected and communicated with the collection control device; the screen channel separation system is connected and communicated with the collection control device; the flow rate can be adjusted and the liquid can be output through the collection control device. The zero-energy aerospace propellant management and emission reduction device of the present invention can be applied to complex gas-liquid boundary conditions, can achieve liquid extraction without entrainment of gas, and liquid discharge without fuel consumption, while the gas-liquid separation efficiency is high, the utilization rate of liquid propellant is high, and the energy consumption is low.

Description

Technical Field

[0001] The present invention relates to the field of aerospace propulsion, and in particular to a zero-energy consumption aerospace propellant management and emission reduction device. Background Art

[0002] Under microgravity conditions, the traditional method of obtaining liquid propellant is to use forward thrust or centrifugal action to separate gas and liquid, which has the disadvantage of requiring additional fuel consumption; and the traditional method of controlling pressure is to directly discharge the gas-liquid mixture, which will cause a large amount of fuel waste. Therefore, technicians in this field are committed to developing an aerospace propellant management and emission reduction device for complex gas-liquid boundary conditions, which can achieve the acquisition and discharge of liquid fuel, and at the same time has high efficiency of gas-liquid separation, high utilization rate of liquid propellant, and low energy consumption. Summary of the invention

[0003] In view of the above-mentioned defects of the prior art, the technical problems to be solved by the present invention are: how to achieve the acquisition and discharge of liquid fuel with low energy consumption, how to improve the efficiency of gas-liquid separation, and how to improve the utilization rate of liquid propellant.

[0004] To achieve the above objectives, the present invention provides a zero-energy aerospace propellant management and emission reduction device, which is characterized in that it includes a tank, an inner blade separation system, a screen channel separation system and a collection control device; the tank is placed in the outermost layer and is shell-shaped as a whole; the inner blade separation system is connected and communicated with the collection control device; the screen channel separation system is connected and communicated with the collection control device; and the liquid is output through the collection control device.

[0005] Furthermore, the interior of the tank is a curved path structure, which is in the form of a combination of a spherical cap and a cylinder.

[0006] Furthermore, the inner blade separation system includes 12 short blades, and the short blades are perpendicular to the inner wall of the storage tank; the bottom end of the inner blade separation system is connected and communicated with the collection control device through a pressure control valve.

[0007] Furthermore, the 12 short blades are evenly arranged and the angle between two adjacent short blades is 30°.

[0008] Furthermore, the short blades are made of a material with good lyophilicity and low density.

[0009] Furthermore, the screen channel separation system includes a plurality of hollow pipes, each of which has a porous pipe wall. The hollow pipes are distributed in the inner wall of the storage tank, and the bottom ends converge to the collection control device and are connected thereto.

[0010] Furthermore, four hollow pipes are arranged in the tank, which are symmetrically distributed and basically pass through the PMD device and the entire aerospace propellant management and emission reduction device. The bottom end of the hollow pipe is connected and communicated with the collection control device.

[0011] Furthermore, the screen channel separation system selects the Dutch Twill weaving method 325×2300 type, where 325×2300 represents 325 warp threads and 2300 weft threads per square inch, which can reflect the screen weaving density.

[0012] Furthermore, the collection control device includes a liquid storage chamber and a pressure control valve; the aerospace propellant management and emission reduction device outputs the liquid through the liquid storage chamber.

[0013] Furthermore, the liquid storage chamber and the pressure control valve are placed at the bottom of the aerospace propellant management and emission reduction device, and the pressure control valve is a passive control switch, which is a switch for controlling the liquid storage chamber to output liquid outward.

[0014] Compared with the traditional method and device, the present invention has the following beneficial effects:

[0015] The zero-energy aerospace propellant management and emission reduction device of the present invention can be applied to complex gas-liquid boundary conditions, and can realize the acquisition and emission of liquid fuel. At the same time, the gas-liquid separation efficiency is high, the utilization rate of liquid propellant is high, and the energy consumption is low.

[0016] The concept, specific structure and technical effects of the present invention will be further described below in conjunction with the accompanying drawings to fully understand the purpose, characteristics and effects of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall effect of a preferred embodiment of the present invention;

[0018] Figure 2 It is a schematic diagram of the overall structure of a preferred embodiment of the present invention;

[0019] Figure 3 A schematic diagram of a curved path tank according to a preferred embodiment of the present invention;

[0020] Figure 4 It is a schematic overall cross-sectional view of a preferred embodiment of the present invention;

[0021] Figure 5 A schematic diagram of the structure of a collection control device according to a preferred embodiment of the present invention;

[0022] Figure 6 The figure is a schematic diagram of the structure of a pressure control valve according to a preferred embodiment of the present invention.

[0023] Among them, 1-collection control device, 11-liquid storage chamber, 12-pressure control valve, 2-storage tank, 3-hollow pipe, 4-blade. DETAILED DESCRIPTION

[0024] The following describes several preferred embodiments of the present invention with reference to the drawings in the specification, so that the technical content is clearer and easier to understand. The present invention can be embodied in many different forms of embodiments, and the protection scope of the present invention is not limited to the embodiments mentioned in the text.

[0025] In the drawings, components with the same structure are indicated by the same numerical reference numerals, and components with similar structures or functions are indicated by similar numerical reference numerals. The size and thickness of each component shown in the drawings are arbitrarily shown, and the present invention does not limit the size and thickness of each component. In order to make the illustration clearer, the thickness of the components is appropriately exaggerated in some places in the drawings.

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only 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.

[0027] like Figure 1 , Figure 2 and Figure 4 As shown, a zero-energy aerospace propellant management and emission reduction device includes a tank 2, an inner blade separation system, a screen channel separation system and a collection control device. Among them, the inner blade separation system is composed of 12 short blades 4 with an angle of 30° between each other, and the blade structure performs tension adsorption and positioning on the liquid; the screen channel separation system is composed of 4 hollow pipes 3, and when the liquid is discharged, it passes through the hollow pipe 3, and at the same time, the remaining liquid in the tank 2 enters the hollow pipe 3 through the porous mesh screen, and the gas is prevented from entering the hollow pipe 3 due to capillary action, thereby achieving gas-liquid phase separation; the collection control device 1 includes a liquid storage chamber 11 and a pressure control valve 12, and the liquid storage chamber 11 can receive the liquid transported by the screen channel and the blades 4 and transport it to the outside of the aerospace propellant management and emission reduction device (PMD), and can also be used to supplement and update the liquid in the device when the fuel in the device is exhausted. The pressure control valve 12 is a passive control switch that can control the switch of the transport channel between the blade separation system and the liquid storage chamber. When the flow rate is small, that is, the pressure difference on both sides of the device is small, it will be closed, and the aerospace propellant management and reduction device (PMD) will only work by the curtain channel separation system; and when the flow rate exceeds the critical pressure, that is, the pressure difference on both sides is large, the pressure control valve 12 will be opened.

[0028] The gas-liquid management process of this device mainly consists of three links. The propellant flows into the device and is diverted through the baffle, which has the effect of slowing down the flow rate and pre-separation; the separation process is carried out simultaneously by the inner blades and the screen channel. After pre-separation, the liquid propellant close to the tank wall enters the screen channel and flows to the liquid storage chamber, while the gas is blocked outside the screen channel; the liquid propellant close to the central axis will flow to the liquid storage chamber along the wall angle; under the regulation of the pressure control valve, the liquids in the two sets of separation systems will eventually converge in the liquid storage chamber, and pure liquid propellant will be obtained through the liquid outlet. Compared with other common propellant management devices, this device is based on the surface tension of the liquid when performing propellant management, and does not consume any energy in the entire gas-liquid separation process, achieving the effect of energy saving and emission reduction to the greatest extent; and the design of the inner blade and outer screen improves the utilization rate of the device for the near-axial liquid and the efficiency of gas-liquid separation; the passive pressure control valve can be adjusted autonomously according to different flow conditions, increasing the fault tolerance of the container. In addition, the zero-energy aerospace propellant management and emission reduction device including the present invention can be applied to complex gas-liquid boundary conditions, and can realize the acquisition and discharge of liquid fuel. At the same time, the gas-liquid separation efficiency is high, the utilization rate of liquid propellant is high, and the energy consumption is low.

[0029] The device can realize the acquisition and discharge of liquid fuel, has high efficiency of gas-liquid separation, and has no additional energy consumption.

[0030] The preferred specific embodiments of the present invention are described in detail above. It should be understood that a person skilled in the art can make many modifications and changes based on the concept of the present invention without creative work. Therefore, any technical solution that can be obtained by a person skilled in the art through logical analysis, reasoning or limited experiments based on the concept of the present invention on the basis of the prior art should be within the scope of protection determined by the claims.

Claims

1. A zero-energy aerospace propellant management and emission reduction device, characterized in that: It includes a tank, an inner blade separation system, a screen channel separation system and a collection control device; the tank is placed in the outermost layer and is in a shell shape as a whole; the inner blade separation system is connected and communicated with the collection control device; the screen channel separation system is connected and communicated with the collection control device, and the liquid is output through the collection control device; the interior of the tank is a curved path structure, which adopts the form of a combination of a spherical cap and a cylinder; the inner blade separation system includes 12 short blades, and the short blades are perpendicular to the inner wall of the tank; the screen channel separation system includes a plurality of hollow pipes, each of which has a porous pipe wall, and the hollow pipes are distributed in the inner wall of the tank, and the bottom ends converge to the collection control device and are connected to it; the collection control device includes a liquid storage chamber and a pressure control valve, and the aerospace propellant management and emission reduction device outputs the liquid through the liquid storage chamber.

2. The zero-energy aerospace propellant management and emission reduction device according to claim 1, characterized in that: The bottom end of the inner blade separation system is connected and communicated with the collection control device through a pressure control valve.

3. The zero-energy aerospace propellant management and emission reduction device as claimed in claim 2, characterized in that: The 12 short blades are evenly arranged and the angle between two adjacent short blades is 30°.

4. The zero-energy aerospace propellant management and emission reduction device as claimed in claim 2, characterized in that: The short blades are made of a material with good liquid affinity and low density.

5. The zero-energy aerospace propellant management and emission reduction device according to claim 1, characterized in that: A total of four hollow pipes are arranged in the tank, which are symmetrically distributed and basically run through the entire aerospace propellant management and emission reduction device. The bottom ends of the hollow pipes are connected and communicated with the collection control device.

6. The zero-energy aerospace propellant management and emission reduction device according to claim 1, characterized in that: The screen channel separation system selects the Dutch Twill weaving method 325×2300 type.

7. The zero-energy aerospace propellant management and emission reduction device according to claim 1, characterized in that: The liquid storage chamber and the pressure control valve are placed at the bottom of the aerospace propellant management and emission reduction device. The pressure control valve is a passive control switch, which is a switch that controls the liquid storage chamber to output liquid outward.

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