CN117985248A

CN117985248A - Propellant storage heating equipment

Info

Publication number: CN117985248A
Application number: CN202211378613.XA
Authority: CN
Inventors: 张振华; 张兴华; 蔡建; 贾少霞; 李龙; 金婷; 刘芳芳; 杨景华
Original assignee: Institute of Microelectronics of CAS
Current assignee: Institute of Microelectronics of CAS
Priority date: 2022-11-04
Filing date: 2022-11-04
Publication date: 2024-05-07

Abstract

The invention discloses propellant storage heating equipment, relates to the technical field of aerospace propellants, and is used for improving the sublimation efficiency of iodine working media and avoiding the phenomenon of pressure response lag in system flow control. The propellant storage heating apparatus comprises a storage tank having a receiving chamber for carrying a propellant to be sublimated, the receiving chamber having an outlet end, a heater and a heat conductor. The heater is arranged on the storage box and is used for heating the storage box so that the temperature of the storage box is increased. The heat conduction piece is located in the accommodating cavity, and the heat conduction piece is in contact connection with the inner wall of the storage box and is used for being in contact with the propellant to be sublimated.

Description

Propellant storage heating equipment

Technical Field

The invention relates to the technical field of aerospace propellants, in particular to a propellant storage heating device.

Background

Under the traction of increasing space task demands, various novel electric propulsion at home and abroad continuously emerge, and the proposal and realization of novel space tasks which are difficult or impossible to complete by traditional chemical propulsion are promoted. Compared with chemical propulsion, the electric propulsion has the advantages of high specific impulse, long service life, simple structure, high reliability and the like. The spacecraft based on electric propulsion can save a large amount of propellant compared with chemical propulsion, can obviously reduce the launching weight of the spacecraft or send more effective load to a detection target place, and effectively reduce the dependence on the launching window and the total weight.

At present, under the conditions of no reduction of specific impulse, high-density propellant storage, low system cost and low dry weight, solid iodine working medium is generally adopted at home and abroad to realize electric propulsion.

In practice, iodine working fluid is typically stored in a storage tank, and then iodine vapor is generated by external heating or radiant heating and delivered to a downstream pusher. With the increasing of the solid iodine working media, the problem of slow heat transfer often exists when the iodine working media are heated, the sublimation efficiency of the iodine working media is lower, and the pressure response is lagged when the flow of the system is controlled.

Disclosure of Invention

The invention aims to provide propellant storage heating equipment which is used for improving the sublimation efficiency of iodine working media and avoiding the phenomenon of pressure response lag in system flow control.

In order to achieve the above object, the present invention provides a propellant storage heating apparatus comprising:

A storage tank having a receiving cavity for carrying a propellant to be sublimated; the accommodating cavity is provided with an outlet end;

the heater is arranged on the storage box and used for heating the storage box;

A heat conduction member located in the accommodation chamber; the heat conducting piece is in contact connection with the inner wall of the storage tank and is used for being in contact with the propellant to be sublimated.

By adopting the technical scheme, the propellant storage heating equipment provided by the invention comprises the storage box and the heater, wherein the storage box is provided with the containing cavity for bearing the propellant to be sublimated, and the propellant to be sublimated is contained in the storage box. The heater is used for heating the storage box, when the temperature of the storage box is increased, the temperature of the propellant to be sublimated contained in the containing cavity of the storage box is increased, the propellant sublimates, and the sublimated propellant is output from the outlet end. Moreover, the propellant storage heating equipment provided by the invention further comprises the heat conduction piece which is positioned in the accommodating cavity and is in contact connection with the inner wall of the storage box, so that the heat conduction piece can receive the heat of the inner wall of the storage box under the heat conduction effect, and the temperature of the heat conduction piece is increased. Further, the temperature of the propellant to be sublimated in contact with the heat conducting member is increased, and the speed of sublimation of the propellant away from the inner wall of the storage tank is accelerated, so that the efficiency of sublimation of the propellant is improved. When the propellant is iodine working medium, the sublimation efficiency of the iodine working medium can be improved, and the phenomenon of pressure response lag during system flow control is avoided.

In one possible implementation, the heat transfer element is a heat transfer plate, which is parallel to the axis of the storage tank.

In one possible implementation, the number of heat transfer plates is plural, and the plural heat transfer plates are arranged in parallel at intervals.

In one possible implementation, the cross section of the heat transfer plate is wave-shaped or zigzag-shaped; adjacent two heat-conducting plates are connected in contact.

In one possible implementation, the heat conductor is a mesh heat conductor.

In one possible implementation, the mesh-like heat transfer element is arranged perpendicular to the axis of the storage tank; the mesh-shaped heat conduction pieces are multiple in number and are sequentially arranged in parallel along the axis extending direction of the storage box.

In one possible implementation, the material of the storage tank and the heat conduction member is 316L stainless steel or nichrome.

In one possible implementation, the propellant storage heating apparatus further comprises a filter screen disposed at the outlet end.

In one possible implementation, the filter mesh is made of 316L stainless steel or nichrome.

In one possible implementation, the propellant storage heating apparatus further comprises a control valve disposed at the outlet end.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:

FIG. 1 is a schematic diagram of a propellant storage heating apparatus according to an embodiment of the present invention;

Fig. 2 is a schematic cross-sectional view provided in an embodiment of the present invention.

Reference numerals:

1-storage box, 2-heat conducting piece, 3-filter screen, 4-control valve, 5-flange cover and 6-pipeline.

Detailed Description

In order to make the technical problems, technical schemes and beneficial effects to be solved more clear, the invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.

It will be understood that when an element is referred to as being "mounted" or "disposed" on another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise. The meaning of "a number" is one or more than one unless specifically defined otherwise.

In the description of the present invention, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", etc., are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.

In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

For space mission requirements, increasing demands are being placed on the maneuverability, payload capacity, mission coverage capacity and lifetime of the spacecraft. The necessity and importance of applying electric propulsion is becoming more and more pronounced for modern spacecraft, with which costs can be reduced and life can be prolonged. Currently, electric propulsion technology is internationally entered into a stage of full-scale application. Under the traction of increasing space task demands, various novel electric propulsion at home and abroad continuously emerge, and the proposal and realization of novel space tasks which are difficult or impossible to complete by traditional chemical propulsion are promoted. The international proposal of a new electric propulsion technical system is that under the condition of not reducing specific impulse, a solid iodine working medium route is adopted, and the system has the advantages of high-density propellant storage, low system cost and low dry weight. At present, solid iodine working medium electric propulsion technology research has been competitively developed at home and abroad.

In practical application, the iodine working medium is generally stored in a storage box, and then the iodine working medium is heated by external heating or radiation to generate iodine steam and is conveyed to a downstream thruster. With the increasing of the solid iodine working media, the problem of slow heat transfer often exists when the iodine working media are heated, the sublimation efficiency of the iodine working media is lower, and the pressure response is lagged when the flow of the system is controlled.

In order to solve the above-described problems of the prior art, as shown in fig. 1 and 2, an embodiment of the present invention provides a propellant storage heating apparatus comprising a storage case 1, a heater and a heat conductor 2, the storage case 1 having a receiving chamber for carrying a propellant to be sublimated, the receiving chamber having an outlet end. A heater is provided to the storage tank 1, and the heater is used to heat the storage tank 1 so that the temperature of the storage tank 1 increases. The heat conducting piece 2 is located in the accommodating cavity, the heat conducting piece 2 is in contact connection with the inner wall of the storage box 1, and the heat conducting piece 2 is used for being in contact with the propellant to be sublimated.

With the adoption of the technical scheme, the propellant storage heating device provided by the embodiment of the invention comprises the storage box 1 and the heater, wherein the storage box 1 is provided with the containing cavity for bearing the propellant to be sublimated, and the propellant to be sublimated is contained in the storage box 1. The heater is used for heating the storage tank 1, when the temperature of the storage tank 1 is increased, the temperature of the propellant to be sublimated contained in the containing cavity of the storage tank 1 is increased, the propellant sublimates, and the sublimated propellant is output from the outlet end and is conveyed to the downstream propeller. Furthermore, the propellant storage heating device provided by the embodiment of the invention further comprises the heat conduction piece 2, wherein the heat conduction piece 2 is positioned in the accommodating cavity, and the heat conduction piece 2 is in contact connection with the inner wall of the storage box 1, so that the heat conduction piece 2 can receive heat of the inner wall of the storage box 1 under the effect of heat conduction, and the temperature of the heat conduction piece 2 is increased. Further, the temperature of the propellant to be sublimated in contact with the heat conductive member 2 is increased to accelerate the sublimation speed of the propellant far from the inner wall of the storage box 1, thereby improving the sublimation efficiency of the propellant and greatly shortening the time required for heating and power supply. When the propellant is iodine working medium, the sublimation efficiency of the iodine working medium can be improved, and the phenomenon of pressure response lag during system flow control is avoided.

In practice, the storage tank is used as a propellant storage tank, and the storage tank can be in a cuboid, a cylinder or other structures, and is not particularly limited herein, and is arranged according to practical situations. The heat transfer member may be welded in the storage box, and an inner wall of the storage box includes a side wall and a bottom wall of the receiving chamber. The heat conductive members are in contact with the propellant to be sublimated, not only can sublimation efficiency of the propellant to be sublimated in contact with the heat conductive members be improved, but also when the number of the heat conductive members is plural, accordingly, the area of the heat conductive members is increased, and thus, the number of the propellant to be sublimated in contact with the heat conductive members is increased, thereby indicating that uniformity of sublimation of the propellant contained in the containing chamber can be improved.

As a possible implementation, the heat-conducting element 2 is a heat-conducting plate, which is parallel to the axis of the storage tank 1. When the heat conduction member 2 is a heat conduction plate, the contact area between the heat conduction member 2 and the propellant to be sublimated can be increased, the quantity of the propellant to be sublimated in contact with the heat conduction member 2 is increased, the sublimation speed of the propellant to be sublimated is increased, and the sublimation uniformity of the propellant contained in the containing cavity can be improved.

In some embodiments, the number of heat transfer plates is a plurality, the plurality of heat transfer plates being arranged in parallel and spaced apart relation. The contact area of the heat conduction member 2 and the propellant to be sublimated can be increased, the quantity of the propellant to be sublimated in contact with the heat conduction member 2 is increased, the sublimation speed of the propellant to be sublimated is increased, and the uniformity of the sublimation of the propellant contained in the containing cavity can be improved. In addition, the plurality of heat conduction plates are arranged in parallel at intervals, so that the packing density of the propellant in the accommodating cavity can be improved.

In one example, as shown in fig. 2, the cross section of the heat conduction plate is in a wave shape or a zigzag shape, and two adjacent heat conduction plates are in contact connection, and the wave shape can be a positive-brown wave shape or a wavy shape. In a plane perpendicular to the axis of the storage tank 1, the crest points and the trough points of two adjacent waveforms or saw-tooth shapes are in contact, so that contact connection of a plurality of heat conduction plates is realized, and the plurality of heat conduction plates can be in contact with each other and conduct heat so as to promote the uniformity of propellant sublimation.

In one possible implementation, the heat conducting member 2 is a mesh-shaped heat conducting member, so that the variety of the heat conducting member 2 is enriched, and the selection is facilitated according to practical situations. The mesh of the net-shaped heat conduction member can contain the propellant to be sublimated, so that not only is the space occupied by the heat conduction member 2 reduced and the storage amount of the propellant to be sublimated correspondingly increased, but also the amount of the propellant in contact with the heat conduction member 2 is increased and the sublimation rate of the propellant is accelerated.

Specifically, the mesh-shaped heat conduction pieces are arranged perpendicular to the axis of the storage box 1, the mesh-shaped heat conduction pieces are multiple in number, and the mesh-shaped heat conduction pieces are sequentially arranged in parallel along the extending direction of the axis of the storage box 1, so that the sublimation rate of the propellant can be accelerated, and the sublimation uniformity of the propellant contained in the containing cavity can be improved.

In practice, the material of the storage tank 1, in particular, the material of the inner wall of the receiving chamber of the storage tank 1 for direct contact with the propellant is required to be a material that does not react electrochemically with the propellant, and in the embodiment provided in the present invention, as an alternative, the material of the storage tank 1 may be 316L stainless steel or nichrome, which is of course only illustrative and not particularly limited. Similarly, the material of the heat conducting member 2 is required to be a material that does not react electrochemically with the propellant, and the material of the heat conducting member 2 is exemplified by 316L stainless steel or nichrome, and is specifically selected according to the actual situation. It should be noted that, the heat conduction member 2 has a certain elasticity, and is suitable for accommodating cavities with different structures, so that the application range of the heat conduction member 2 is enlarged. The propellant storage heating equipment provided by the embodiment of the invention utilizes the characteristics of good softness and heat conduction performance of the heat conduction piece 2, performs solid propellant filling operation on the filling position formed between the heat conduction piece 2 and the accommodating cavity, greatly shortens the heating time, has great significance on a solid propellant electric propulsion system with large working mass and time requirements, is convenient for rapid heating, has a compact structure and provides conditions for rapid operation of a satellite platform. In addition, due to the compressible type of the heat conductive member 2, the heat conductive member 2 may closely contact the inner wall of the storage box 1, increasing a heat conductive area, enabling the heat conductive member 2 to rapidly conduct heat and spread the heat.

It should be noted that, when the cross section of the heat conduction plate is a schematic top view of a waveform as shown in fig. 2, fig. 1 is a schematic front view of fig. 2, that is, a plurality of waveform heat conduction plates are sequentially arranged at intervals along an axis parallel to the storage box 1, and the peak points and the trough points of two adjacent waveform heat conduction plates are in contact. It should be understood that, when the heat conductive member 2 is a mesh heat conductive member, a plurality of mesh heat conductive members are disposed in parallel in order along the extending direction of the axis of the storage box 1, fig. 2 may be a schematic plan view of one layer of mesh heat conductive members.

In specific implementation, the propellant storage heating device provided by the embodiment of the invention further comprises a flange cover 5, wherein the flange cover 5 is arranged at the outlet end of the storage box 1, and the flange cover 5 is arranged at the outlet end of the storage box 1 in a covering manner. The flange cover 5 is matched with the storage box 1, the flange cover 5 is used as a communicating part of the storage box 1 and an external pipeline 6 for conveying sublimated propellant, one end of the flange cover 5 can be connected to the storage box 1 through bolt fastening, and the other end of the flange cover 5 and the pipeline 6 can be fixedly connected through a welding connection mode. The flange cover 5 may be made of 316L stainless steel, nichrome, or the like, which does not react with the propellant.

In a possible implementation manner, referring to fig. 1, the propellant storage heating apparatus provided in the embodiment of the present invention further includes a filter screen 3 disposed at the outlet end. Specifically, the output end of the flange cover 5 is provided with a boss circumferentially arranged along the inner wall of the output end of the flange cover 5, and the filter screen 3 can be fixedly arranged on the boss in a welding manner. The purpose of setting the filter screen 3 is that on the one hand, other solid impurities flowing along with the gaseous propellant are intercepted, and on the other hand, the filter screen 3 can avoid the solid propellant to travel into the pipeline 6 and block the pipeline 6 under the condition of weightlessness. The aperture of the filter screen 3 is required to ensure that no solid propellant passes through, so that the gaseous propellant can smoothly flow through and does not react with the filter screen 3. The material of the filter screen 3 may be 316L stainless steel or nichrome, etc. that does not react with the propellant. The filter screen 3 can pass through 5-10 mu m particles, and can be welded in a boss in the flange cover 5 after being arranged in a certain rule by adopting a plurality of layers of metal filter screens 3.

As a possible implementation manner, the propellant storage heating apparatus provided in the embodiment of the present invention further includes a control valve 4, as shown in fig. 1, where the control valve 4 is disposed at the outlet end. The control valve 4 is used as an on-off gas path valve, and the control valve 4 is made of corrosion-resistant stainless steel series and the like. When the line 6 is inflated, the control valve 4 is in an open state, and gaseous propellant can flow along the line 6 into the receiving chamber. When the propellant is stored for a long period of time, the entry of external gases, in particular water vapor, into the line 6 and into the receiving chamber is prevented.

It should be noted that, in the embodiment provided by the present invention, the solid propellant may be an iodine working medium. The particle size and the processing method of the iodine working medium can be processed according to different requirements. Specifically, a grinding mode can be adopted to obtain the solid iodine working medium with the density of about 2.7-2.8g/cm < 3 >. When the conditions of equal safety and equal quality requirements are ensured, a liquefying and resolidifying mode is adopted, and the solid iodine working medium with the density of about 4.8g/cm < 3 > can be obtained.

When the solid propellant is iodine working medium, the solid iodine particles of raw materials are changed into solid iodine powder in a rolling way, so that on one hand, the filling density of the solid iodine working medium can be improved, on the other hand, the contact area with the heat conduction piece is increased, and the sublimation time of the solid iodine working medium is shortened. In a dry environment, the prepared solid iodine working medium is filled into the storage box, and in the filling process, the storage box needs to be rocked back and forth in order to fill as much solid iodine working medium as possible, so that the whole storage box is filled with the solid iodine working medium. After filling, the flange cover and the storage box are mechanically assembled, so that the sealing performance of the storage box is ensured. The control valve in the pipeline is in a closed state, so that the solid iodine working medium is prevented from being in contact with a wet environment to generate electrochemical reaction. When the iodine working medium is in contact with the heat conduction piece in a liquid state, the temperature in the accommodating cavity is ensured not to cause the liquid iodine working medium to be condensed to block the channel, and the liquid iodine working medium has strong toxicity and needs to be operated in a safe and advanced mode. The mode maximizes the density of the iodine working medium, maximizes the contact area of the iodine working medium and the heat conduction piece, has high filling density, further shortens the heating time, and is beneficial to the rapid long-life operation of the electric propulsion system.

In the description of the above embodiments, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.

The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A propellant storage heating apparatus, comprising:

a storage tank having a receiving cavity for carrying a propellant to be sublimated; the receiving chamber has an outlet end;

The heater is arranged on the storage box and used for heating the storage box;

2. A propellant storage heating apparatus according to claim 1, wherein the heat conducting member is a heat conducting plate, the heat conducting plate being parallel to the axis of the storage case.

3. A propellant storage heating apparatus according to claim 2, wherein the number of heat transfer plates is plural, a plurality of the heat transfer plates being arranged in parallel and spaced apart relation.

4. A propellant storage heating apparatus according to claim 3, wherein the heat transfer plate is corrugated or saw-tooth in cross-section; adjacent two of the heat conduction plates are connected in contact.

5. A propellant storage heating apparatus according to claim 1, wherein the heat conductor is a mesh heat conductor.

6. A propellant storage heating apparatus according to claim 5, wherein the mesh heat transfer element is disposed perpendicular to the axis of the storage case; the number of the net-shaped heat conduction pieces is multiple, and the net-shaped heat conduction pieces are sequentially arranged in parallel along the extending direction of the axis of the storage box.

7. A propellant storage heating apparatus according to claim 1, wherein the material of the storage tank, the heat transfer element is 316L stainless steel or nichrome.

8. A propellant storage heating apparatus according to claim 1, further comprising a filter screen disposed at the outlet end.

9. The propellant storage heating apparatus of claim 8, wherein the filter is 316L stainless steel or nichrome.

10. The propellant storage heating apparatus of claim 1, further comprising a control valve disposed at the outlet end.