Single-component thruster for strengthening heat and mass transfer and manufacturing method and application of single-component thruster

Abstract

The invention provides a single-component thruster for strengthening heat and mass transfer and a manufacturing method and application of the single-component thruster. The single-component thruster comprises an evenly-distributed injector assembly, a strengthening type catalyst bed assembly and a spray pipe which are sequentially arranged. The uniform distribution injector assembly comprises an injector, a uniform distribution net and a supporting net; the flow distribution proportion of the injection surface of the injector in the central area is not higher than 45%, and the flow distribution proportion of the injection surface of the injector in the peripheral area is not lower than 55%; the enhanced catalyst bed assembly comprises a shell as well as a sub-bed plate net, a sub-bed plate, a bed stop plate net and a bed stop plate which are sequentially mounted in the shell along the axial direction; through the special structural design of the shell, the separate bed plates and the bed stop plates, the heat and mass transfer of the catalyst bed is enhanced. The method is suitable for a single-component thruster system adopting a green and non-toxic propellant, and the performance index of a spacecraft can be greatly improved.

Description

Technical Field

[0001] The present invention relates to the field of monopropellant propulsion technology, and more particularly to a monopropellant thruster with enhanced heat and mass transfer, a manufacturing method thereof, and applications thereof. Background Art

[0002] Monopropellant engines, due to their simplicity and high reliability, are widely used in satellite and manned spaceflight technology, providing the power needed for attitude control and orbital adjustments. Depending on the application, the starting temperature, ignition conditions, and operating life requirements of monopropellant engines vary. In launch vehicles and spacecraft, monopropellant engines are typically used for attitude control, propellant deposition, and deorbiting. They operate for short periods of time and do not require a long lifespan. The initial start is typically at room temperature (generally defined as 0-35°C) or low-temperature (-30-0°C). Subsequent starts are usually hot starts, with the number of room-temperature starts typically limited to three. Monopropellant propulsion typically uses the low-freezing-point DT-3 propellant. This propellant is highly toxic, flammable, explosive, and highly contaminating, requiring complex ground support and assurance systems, which significantly impacts the vehicle's responsiveness and maneuverability.

[0003] Liquid green propulsion technology, characterized by its non-toxicity, high performance, excellent safety (suitable for air transport), and long-term storage, is the development direction for modern aerospace attitude and orbit control propulsion systems. In recent years, my country's monopropellant green propulsion technology has rapidly developed and has been successfully applied on dozens of satellites. However, progress in launch vehicle and spacecraft propulsion systems has been slower. In this field, high performance is generally required, which necessitates high bed loads in engine design. This presents two technical challenges in specific engineering issues: achieving room temperature or even low-temperature start-up of the lower engine catalyst bed without preheating, and achieving continuous and stable engine operation during orbit control missions. Technically, these challenges require the development of low-freezing-point green propellants and their catalytic combustion technology, and green propulsion monopropellant engine technology. However, in actual engineering practice, the structural design of green propulsion monopropellant engines has consistently adhered to the design methods and concepts of traditional hydrazine engines.

[0004] Among the currently published patents, CN 106134388B, "A Monopropellant Engine with Non-Toxic Unitary Propellants," proposes an engine structure based on a conventional monopropellant hydrazine engine. This design addresses the high difficulty and high combustion temperature of non-toxic propellants by specifying the active components and content of the catalyst, and proposes adding a combustion chamber structure and using refractory metal mesh and porous metal plates. CN 106134393B, "A Small-Thrust Monopropellant Hydrogen Peroxide Rocket Engine," proposes an engine structure based on a conventional monopropellant hydrazine engine with partial improvements to adapt it to a hydrogen peroxide green propellant system. However, these two patents merely propose a single structure, optimizing a conventional monopropellant hydrazine engine to adapt it to a new propellant system. No one has yet proposed a comprehensive technical solution, such as a structural design and manufacturing method for a monopropellant green thruster, that effectively addresses the aforementioned issues, including the mechanism of action and engineering performance of green propellants.

[0005] Traditional monopropellant thruster design methods focus on the selection of thruster design points, and the design methods generally adopt general design criteria. They have failed to play an effective role in solving the problems of normal or low-temperature startup and continuous orbit control of green propellant high-performance monopropellant thrusters. The gap in design methods has become the key factor in the delay in the engineering application of green high-performance thrusters. Summary of the Invention

[0006] The present invention addresses the technical development bottlenecks of monopropellant propulsion technology, especially green and non-toxic propulsion technology, in achieving high performance, first start-up at room temperature or low temperature, and long-range continuous operation in orbit control working mode. It proposes a monopropellant thruster with enhanced heat and mass transfer, as well as its manufacturing method and application. Through innovation in the thruster structure, the heat and mass transfer in the catalytic combustion process of the monopropellant is enhanced, and a large amount of reaction heat generated by the catalytic combustion is guided to the center of the catalyst bed, so that the catalyst bed temperature rises rapidly to achieve startup ignition. At the same time, a large amount of reaction heat can achieve self-sustaining of the catalytic combustion reaction, so that the engine can work stably, especially when executing long steady-state working conditions, the continuous stability of the engine can be greatly improved; at the same time, a manufacturing method and application of the thruster are proposed; through a large number of experimental verifications, the effectiveness has been fully verified, and it has broad application prospects in the fields of launch vehicles, manned spaceflight, etc.

[0007] The technical means adopted in the present invention are as follows: A monopropellant thruster with enhanced heat and mass transfer, comprising a uniformly distributed injector assembly, an enhanced catalyst bed assembly and a nozzle arranged in sequence; The uniformly distributed injector assembly includes an injector, a uniformly distributed net, and a support net connected in sequence; the injector's injection surface is divided into a central area and a peripheral area, and the areas of the central area and the peripheral area are respectively 50% of the area of ​​the injection surface; the flow distribution ratio of the injector in the central area is not higher than 45%, and the flow distribution ratio in the peripheral area is not lower than 55%; the outlets of the capillaries in the injector are uniformly arranged on the injection surface according to concentric circles of different diameters, and the diameter of the innermost concentric circle is greater than the difference between the diameter of the injection surface and the diameter of the outermost concentric circle; The enhanced catalyst bed assembly includes a shell and a bed partitioning plate net, a bed partitioning plate, a bed stop plate net and a bed stop plate which are sequentially installed axially inside the shell; the shell inlet serves as the inlet of the enhanced catalyst bed assembly and is connected to the outlet of the uniformly distributed injector assembly; the shell outlet serves as the outlet of the enhanced catalyst bed assembly and is connected to the inlet of the nozzle; the internal space of the shell is divided into a front bed catalyst loading space and a rear bed catalyst loading space from the inlet to the outlet, the bed partitioning plate net and the bed partitioning plate are located between the front bed catalyst loading space and the rear bed catalyst loading space, and the bed stop plate net and the bed stop plate are located at the other end of the rear bed catalyst loading space; The structure of the housing adopts one of the following four schemes: a. The inner surface of the shell is conical, the large diameter end is the inlet of the shell, and the small diameter end is the outlet of the shell; b. The inner surface of the shell is cylindrical; c. In the shell, the inner surface of the front bed catalyst filling space is conical, and the large diameter end is the inlet of the shell, and the inner surface of the rear bed catalyst filling space is cylindrical; d. In the shell, the inner surface of the front-bed catalyst loading space is cylindrical, the inner surface of the rear-bed catalyst loading space is conical, and the small-diameter end is the outlet of the shell; When the structure of the shell adopts solution a, the bed partition plate and the bed stop plate are both conical flat plates with a plurality of through holes; When the structure of the shell adopts solution b, the structures of the bed partition board and the bed stop board respectively adopt one of the following two solutions: a cylindrical plate with a conical groove with a large diameter end facing outward on the side facing the shell inlet and a plurality of through holes on the bottom surface, or a cylindrical flat plate with a plurality of through holes; When the structure of the shell adopts solution c: the bed partition plate is a conical flat plate with a plurality of through holes; the bed stop plate is a cylindrical plate with a conical groove with a large diameter end facing outward on the side facing the shell inlet and a plurality of through holes on the bottom surface; When the structure of the shell adopts solution d: the bed partition plate is a cylindrical flat plate with a plurality of through holes; the bed stop plate is a conical flat plate with a plurality of through holes in the center.

[0008] Furthermore, the inner surface of the front bed catalyst filling space is cylindrical, the inner surface of the rear bed catalyst filling space is conical, and the small diameter end is the outlet of the shell; the bed plate is a cylindrical flat plate with several through holes; the bed stop plate is a conical flat plate with several through holes in the center.

[0009] Furthermore, the inner surface of the front bed catalyst filling space is conical, and the large diameter end is the inlet of the shell, and the inner surface of the rear bed catalyst filling space is cylindrical; the bed plate is a conical flat plate with a plurality of through holes; the bed stop plate is a cylindrical plate with a conical groove with the large diameter end facing outward on the side facing the shell inlet and a plurality of through holes on the bottom surface.

[0010] Furthermore, the opening area on the divided bed plate is not less than 60%.

[0011] Furthermore, the opening area on the bed stop is not less than 25%.

[0012] The present invention also provides a method for manufacturing the monopropellant thruster with enhanced heat and mass transfer, wherein the catalyst is loaded into the enhanced catalyst bed assembly in any of the following ways: (1) After the nozzle and the shell are fixedly connected to form an integrated structure, the catalyst is loaded from the inlet of the enhanced catalyst bed assembly, and then the uniform injector assembly is connected to the enhanced catalyst bed assembly; (2) After the uniform injector assembly and the shell are fixedly connected to form an integrated structure, the catalyst is loaded from the outlet of the enhanced catalyst bed assembly, and then the nozzle is connected to the enhanced catalyst bed assembly.

[0013] Furthermore, when the catalyst is loaded using method (1), the following steps are specifically included: a) Weld the nozzle and shell together into an integrated structure; spot weld the bed stop plate mesh to the bed stop plate, and install it from the inlet end of the shell onto the bed stop plate mounting platform at the bottom of the shell, with the bed stop plate mesh facing the shell inlet; b) loading the rear bed catalyst into the rear bed catalyst loading space of the shell and compacting it; c) Install the bed plate in the shell, fill the through holes on the bed plate with the rear bed catalyst and compact it; d) Spot weld the bed plate mesh to the bed plate and the inner wall of the shell; e) loading the front-bed catalyst into the front-bed catalyst loading space of the shell and compacting it; f) Bolt or weld the uniform injector assembly to the inlet end of the shell.

[0014] Furthermore, when the catalyst is loaded using method (2), the following steps are specifically included: a) Welding the uniform injector assembly and the shell into an integrated structure; loading the front-bed catalyst into the front-bed catalyst loading space of the shell from the outlet end and compacting it; b) After spot welding the bed separation plate mesh to the bed separation plate, place the bed separation plate mesh facing the front bed catalyst and install the bed separation plate mesh and bed separation plate together into the shell; c) filling the rear bed catalyst into the rear bed catalyst filling space of the shell and compacting it; d) After spot welding the bed stopper mesh to the bed stopper plate, place the bed stopper mesh facing the rear bed catalyst and install the bed stopper mesh and bed stopper plate together into the housing; e) Bolt or weld the nozzle to the outlet end of the shell.

[0015] The present invention also provides an application of a monocomponent thruster with enhanced heat and mass transfer. The catalyst used in the enhanced catalyst bed assembly is a non-iridium spontaneous catalyst, and the active component is a single metal ruthenium or bimetallic ruthenium-based catalyst. The normal temperature start-up temperature range of the thruster is 0°C to 35°C; the low temperature start-up temperature range of the thruster is -20°C to 0°C; the continuous opening time of the thruster does not exceed 1800s; the thrust provided by the thruster ranges from 5N to 500N, and the bed load range is (1.5 to 6) g / cm 2 •s.

[0016] Compared with the prior art, the present invention has the following advantages: The monopropellant thruster with enhanced heat and mass transfer provided by the present invention, as well as its manufacturing method and application, enhances the heat and mass transfer in the catalytic combustion process of the propellant by improving the structure of the uniformly distributed injector and the catalyst bed, guides a large amount of reaction heat generated by the catalytic combustion to the center of the catalyst bed, rapidly increases the temperature of the catalyst bed and realizes fast startup. At the same time, a large amount of reaction heat can realize the self-sustaining of the catalytic combustion reaction, so that the engine can operate stably, especially when executing long steady-state operating conditions, which can greatly increase the continuous stable working time of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0018] Figure 1 It is a schematic diagram of the thruster structure of embodiment 1 of the present invention.

[0019] Figure 2 It is a schematic structural diagram of the uniformly distributed injector assembly of Example 1 of the present invention.

[0020] Figure 3 It is a schematic structural diagram of the enhanced catalyst bed assembly of Example 1 of the present invention.

[0021] Figure 4 This is a data curve of chamber pressure and temperature during cold start of the thruster at room temperature according to Example 1 of the present invention.

[0022] Figure 5 This is the chamber pressure and temperature data curve of the thruster in the long steady state of 1800s in Example 1 of the present invention.

[0023] Figure 6 It is a schematic structural diagram of the enhanced catalyst bed assembly of Example 2 of the present invention.

[0024] Figure 7 This is a schematic diagram of the bed plate structure of Example 2 of the present invention.

[0025] Figure 8 It is a schematic diagram of the bed stop plate structure of embodiment 2 of the present invention.

[0026] Figure 9 This is a curve of chamber pressure and temperature data during normal temperature startup of a thruster according to Example 2 of the present invention.

[0027] Figure 10 This is a curve of chamber pressure and temperature data of the thruster in the long steady state of 300 seconds according to Example 2 of the present invention.

[0028] Figure 11 It is a schematic structural diagram of the enhanced catalyst bed assembly of Example 3 of the present invention.

[0029] Figure 12 This is a schematic diagram of the bed plate structure of Example 3 of the present invention.

[0030] Figure 13 It is a schematic diagram of the bed stop plate structure of embodiment 3 of the present invention.

[0031] Figure 14 It is a schematic structural diagram of the enhanced catalyst bed assembly of Example 4 of the present invention.

[0032] Figure 15 This is a data curve of the thruster chamber pressure and temperature during cold start at room temperature according to Example 4 of the present invention.

[0033] Figure 16 This is a data curve of chamber pressure and temperature of the thruster in the long steady state of 200 seconds according to Example 4 of the present invention.

[0034] Figure 17 It is a schematic structural diagram of the enhanced catalyst bed assembly of Example 5 of the present invention.

[0035] Figure 18 This is a curve of the thruster low-temperature starting chamber pressure and temperature data of Example 5 of the present invention.

[0036] Figure 19 This is a curve of chamber pressure and temperature data of a thruster in a long steady state of 100 seconds according to Example 5 of the present invention.

[0037] Figure 20 Schematic diagram of the thruster structure of comparative example 1 of the present invention.

[0038] Figure 21 This is the data curve of the thruster chamber pressure and temperature during cold start at room temperature of Comparative Example 1 of the present invention.

[0039] Figure 22 This is the chamber pressure and temperature data curve of the thruster in the comparative example 1 of the present invention in the long steady state of 100s.

[0040] Figure 23 The thruster long steady state 100s chamber pressure and temperature data curve of comparative example 2 of the present invention.

[0041] In the figure: 1. Uniformly distributed injector assembly; 2. Enhanced catalyst bed assembly; 3. Nozzle; 4. Injector; 5. Uniformly distributed net; 6. Support net; 7. Shell; 8. Front bed catalyst; 9. Partitioning bed plate net; 10. Partitioning bed plate; 11. Rear bed catalyst; 12. Bed stop plate net; 13. Bed stop plate. DETAILED DESCRIPTION

[0042] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0043] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings 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. The following description of at least one exemplary embodiment is actually only illustrative and is in no way intended to limit the present invention and its application or use. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0044] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they indicate the presence of features, steps, operations, devices, components and / or combinations thereof.

[0045] Unless otherwise specified, the relative arrangement of the parts and steps, numerical expressions and numerical values ​​set forth in these embodiments do not limit the scope of the present invention. At the same time, it should be clear that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to actual proportional relationships. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of the exemplary embodiments can have different values. It should be noted that similar numbers and letters represent similar items in the following drawings, and therefore, once an item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0046] In the description of the present invention, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "horizontal, vertical, vertical, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present invention: the directional words "inside and outside" refer to the inside and outside relative to the outline of each component itself.

[0047] For ease of description, spatially relative terms such as "above," "above," "on the upper surface of," and "above" may be used herein to describe the spatial positional relationship of a device or feature to other devices or features as shown in the figures. It should be understood that spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is inverted, a device described as "above" or "on top of" another device or structure would then be positioned as "below" or "below" the other device or structure. Thus, the exemplary term "above" may include both the orientations of "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used herein should be interpreted accordingly.

[0048] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0049] like Figures 1 to 3 As shown, the present invention provides a monopropellant thruster with enhanced heat and mass transfer, comprising a uniformly distributed injector assembly 1, an enhanced catalyst bed assembly 2 and a nozzle 3 arranged in sequence; The uniformly distributed injector assembly 1 includes an injector 4, a uniformly distributed net 5, and a support net 6 connected in sequence; the injection surface of the injector 4 is divided into a central area and a peripheral area excluding the central area, and the areas of the central area and the peripheral area are respectively 50% of the area of ​​the injection surface; the flow distribution ratio of the injector 4 in the central area is not higher than 45%, and the flow distribution ratio in the peripheral area is not lower than 55%; the outlets of the capillaries in the injector 4 are uniformly arranged on the injection surface according to concentric circles of different diameters, and the diameter of the innermost concentric circle is greater than the difference between the diameter of the injection surface and the diameter of the outermost concentric circle; The enhanced catalyst bed assembly 2 includes a shell 7 and a bed partitioning plate net 9, a bed partitioning plate 10, a bed stop plate net 12 and a bed stop plate 13 installed in sequence along the axial direction inside the shell 7; the inlet of the shell 7 serves as the inlet of the enhanced catalyst bed assembly 2 and is connected to the outlet of the uniformly distributed injector assembly 1; the outlet of the shell 7 serves as the outlet of the enhanced catalyst bed assembly 2 and is connected to the inlet of the nozzle 3; the internal space of the shell 7 is divided into a front bed catalyst loading space and a rear bed catalyst loading space from the inlet to the outlet, the bed partitioning plate net 9 and the bed partitioning plate 10 are located between the front bed catalyst loading space and the rear bed catalyst loading space, and the bed stop plate net 12 and the bed stop plate 13 are located at the other end of the rear bed catalyst loading space; The present invention enhances the heat and mass transfer of the catalyst bed through the special structural design of the shell 7, the bed plate 10 and the bed stop plate 13: The structure of the housing 7 adopts one of the following four schemes: a. The inner surface of the shell 7 is conical, the large diameter end is the inlet of the shell 7, and the small diameter end is the outlet of the shell 7; b. The inner surface of the housing 7 is cylindrical; c. In the shell 7, the inner surface of the front bed catalyst filling space is conical, and the large diameter end is the inlet of the shell 7, and the inner surface of the rear bed catalyst filling space is cylindrical; d. In the shell 7, the inner surface of the front bed catalyst filling space is cylindrical, the inner surface of the rear bed catalyst filling space is conical, and the small diameter end is the outlet of the shell 7; When the structure of the housing 7 adopts solution a, the bed partition plate 10 and the bed stop plate 13 are both conical flat plates with a plurality of through holes; When the structure of the shell 7 adopts solution b, the structures of the bed partition board 10 and the bed stop board 13 respectively adopt one of the following two solutions: a cylindrical plate with a conical groove with a large diameter end facing outward on the side facing the inlet of the shell 7 and a plurality of through holes on the bottom surface, or a cylindrical flat plate with a plurality of through holes; When the structure of the shell 7 adopts solution c: the bed partition plate 10 is a conical flat plate with a plurality of through holes; the bed stop plate 13 is a cylindrical plate with a conical groove with a large diameter end facing outward on the side facing the entrance of the shell 7 and a plurality of through holes on the bottom surface; When the structure of the shell 7 adopts solution d: the bed partition board 10 is a cylindrical flat plate with a plurality of through holes; the bed stop board 13 is a conical flat plate with a plurality of through holes in the center.

[0050] Preferably, when the bed stop plate 13 is a conical flat plate or a cylindrical flat plate, the through hole is opened in the center.

[0051] Preferably, the inner surface of the front bed catalyst filling space is cylindrical, the inner surface of the rear bed catalyst filling space is conical, and the small diameter end is the outlet of the shell 7; the bed plate 10 is a cylindrical flat plate with a plurality of through holes; the bed stop plate 13 is a conical flat plate with a plurality of through holes in the center.

[0052] Preferably, the inner surface of the front bed catalyst filling space is conical, and the large diameter end is the inlet of the shell 7, and the inner surface of the rear bed catalyst filling space is cylindrical; the bed plate 10 is a conical flat plate with a plurality of through holes; the bed stop plate 13 is a cylindrical plate with a conical groove with the large diameter end facing outward on the side facing the inlet of the shell 7 and a plurality of through holes on the bottom surface.

[0053] Furthermore, the opening area on the bed partition board 10 is not less than 60%.

[0054] Furthermore, the opening area of ​​the bed stop plate 13 is not less than 25%.

[0055] Furthermore, the front bed catalyst filling space is filled with a front bed catalyst 8, and the rear bed catalyst filling space is filled with a rear bed catalyst 11. Both the front bed catalyst 8 and the rear bed catalyst 11 are non-iridium spontaneous catalysts, and the active component is a single metal ruthenium or a bimetallic ruthenium-based catalyst.

[0056] The present invention also provides a method for manufacturing a monopropellant thruster with enhanced heat and mass transfer, wherein the catalyst is loaded into the enhanced catalyst bed assembly 2 in any of the following ways: (1) After the nozzle 3 and the housing 7 are fixedly connected to form an integral structure, the catalyst is loaded from the inlet of the enhanced catalyst bed assembly 2, and then the uniform injector assembly 1 is connected to the enhanced catalyst bed assembly 2; (2) After the uniform injector assembly 1 and the shell 7 are fixedly connected to form an integrated structure, the catalyst is loaded from the outlet of the enhanced catalyst bed assembly 2, and then the nozzle 3 is connected to the enhanced catalyst bed assembly 2.

[0057] Furthermore, when the structure of the shell 7 adopts scheme a, c, or d, the catalyst needs to be loaded in method (1); when the structure of the shell 7 adopts scheme b, the catalyst can be loaded in method (1) or (2).

[0058] Furthermore, when the catalyst is loaded using method (1), the following steps are specifically included: a) Weld the nozzle 3 and the housing 7 together into an integrated structure; spot weld the bed stopper mesh 12 to the bed stopper plate 13, and install it from the inlet end of the housing 7 onto the bed stopper plate mounting platform at the bottom of the housing 7, with the bed stopper mesh 12 facing the inlet of the housing 7; b) loading the rear bed catalyst 11 into the rear bed catalyst loading space of the housing 7 and compacting it; c) Installing the bed plate 10 in the housing 7, filling the through holes of the bed plate 10 with the rear bed catalyst 11 and compacting the filler; d) Spot weld the bed partition plate mesh 9 to the bed partition plate 10 and the inner wall of the shell 7; e) loading the front-bed catalyst 8 into the front-bed catalyst loading space of the housing 7 and compacting it; f) Connect the uniform injector assembly 1 to the inlet end of the housing 7 by bolting or welding.

[0059] Furthermore, when the catalyst is loaded using method (2), the following steps are specifically included: a) Welding the uniform injector assembly 1 and the housing 7 into an integrated structure; loading the front-bed catalyst 8 into the front-bed catalyst loading space of the housing 7 from the outlet end of the housing 7 and compacting it; b) After spot welding the bed separation plate mesh 9 to the bed separation plate 10, place the bed separation plate mesh 9 facing the front bed catalyst 8, and install the bed separation plate mesh 9 and the bed separation plate 10 together into the housing 7; c) loading the rear bed catalyst 11 into the rear bed catalyst loading space of the housing 7 and compacting it; d) After spot welding the bed stopper mesh 12 to the bed stopper plate 13, place the bed stopper mesh 12 facing the rear catalyst bed 11 and install the bed stopper mesh 12 and the bed stopper plate 13 together into the housing 7; e) Connect the nozzle 3 to the outlet end of the housing 7 by bolting or welding.

[0060] The present invention also provides an application of a monopropellant thruster with enhanced heat and mass transfer, which is applied to a monopropellant thruster system, and is particularly suitable for a green and non-toxic propellant system. The heat and mass transfer in the catalytic combustion process of the monopropellant is enhanced by the uniformly distributed injector assembly 1 and the enhanced catalyst bed assembly 2 structure, so as to achieve fast start-up of the thruster under normal temperature and low temperature start-up temperature conditions and high-temperature continuous working stability, thereby greatly improving the technical and tactical performance indicators of high-performance power equipment such as launch vehicles and manned spaceflight, and having broad application prospects; the catalyst used in the enhanced catalyst bed assembly 2 is a non-iridium spontaneous catalyst, and the active component is a monometallic ruthenium-based catalyst or a bimetallic ruthenium-based catalyst; the normal temperature start-up temperature range of the thruster is 0°C~35°C; the low temperature start-up temperature range of the thruster is -20°C~0°C; the continuous opening time of the thruster does not exceed 1800s; the thrust provided by the thruster ranges from 5N to 500N, and the bed load range is (1.5~6) g / cm 2 •s.

[0061] The monopropellant thruster with enhanced heat and mass transfer provided by the present invention, as well as its manufacturing method and application, enhances the heat and mass transfer in the catalytic combustion process of the propellant through the structural design of the uniformly distributed injector and the catalyst bed, guides the large amount of reaction heat generated by the catalytic combustion to the center of the catalyst bed, rapidly increases the temperature of the catalyst bed, and realizes fast startup. At the same time, the large amount of reaction heat can realize the self-sustaining of the catalytic combustion reaction, so that the engine can operate stably, especially when executing long steady-state operating conditions, it can greatly improve the continuous stable working time of the engine, and has broad application prospects in the fields of launch vehicles, manned spaceflight, etc.

[0062] Example 1 Based on the above technical solutions, Figure 1-3 As shown, in the thruster provided in this embodiment, the flow distribution ratio of the injector 4 in the central area is not higher than 40%, and the flow distribution ratio in the peripheral area is not lower than 60%; The structure of the enhanced catalyst bed assembly 2 is as follows Figure 3 As shown: the inner surface of the shell 7 is conical, the large diameter end is the inlet of the shell 7, and the small diameter end is the outlet of the shell 7; the bed partition board 10 and the bed stop board 13 are both conical flat plates with a plurality of through holes; The opening area on the bed partition plate 10 is 75%.

[0063] The opening area of ​​the bed stop plate 13 is 30%.

[0064] The manufacturing method of the thruster described in this embodiment adopts method (1) of loading the catalyst, that is, after the nozzle 3 and the shell 7 are fixedly connected to form an integrated structure, the catalyst is loaded from the inlet of the enhanced catalyst bed assembly 2, and then the uniform injector assembly 1 is connected to the enhanced catalyst bed assembly 2.

[0065] The thruster of this embodiment is applied to a monopropellant thruster system using green and non-toxic propellants. The front bed catalyst 8 and the rear bed catalyst 11 are both non-iridium spontaneous catalysts, and the active component is a single metal ruthenium catalyst. The ground test start temperature of the thruster is room temperature, and the ignition curve is as follows: Figure 4 As shown; the thruster ground test continuous working condition is the continuous opening time 100s, the ignition curve is as follows Figure 5 As shown; the thrust range of the thruster is 50N, and the bed load range is 3g / cm 2 •s, successfully passed the 1800s long steady-state test.

[0066] Example 2 The difference from the thruster in Example 1 is that: The flow distribution ratio of the injector 4 in the central area is 45%, and the flow distribution ratio in the peripheral area is 55%; The outlet of the injector 4 is spot welded to the uniform mesh 5, and the aperture specification of the uniform mesh 5 is 250 mesh; the outer side of the uniform mesh 5 is spot welded to the support mesh 6, and the aperture specification of the support mesh 6 is 40 mesh; The structure of the enhanced catalyst bed assembly 2 is as follows Figure 6 As shown: the inner surface of the shell 7 is cylindrical, and the structure of the bed plate 10 and the bed stop plate 13 is as shown. Figure 7 、 Figure 8 As shown, they are all cylindrical plates with a conical groove with a large diameter end facing outward on the side facing the inlet of the housing 7 and a plurality of through holes on the bottom surface; The opening area on the bed partition board 10 is 60%; The opening area on the bed stop plate 13 is 25%.

[0067] The manufacturing method of the thruster described in this embodiment adopts method (2) to load the catalyst, that is, after the uniform injector assembly 1 and the shell 7 are fixedly connected to form an integrated structure, the catalyst is loaded from the outlet of the enhanced catalyst bed assembly 2, and then the nozzle 3 is connected to the enhanced catalyst bed assembly 2.

[0068] The thruster of this embodiment is applied to a monopropellant thruster system using green and non-toxic propellants. The front bed catalyst 8 and the rear bed catalyst 11 are both non-iridium spontaneous catalysts, and the active component is a ruthenium-based alloy catalyst. The thruster ground test is started at room temperature at 0°C, and the ignition curve is as follows: Figure 9 As shown; the thruster ground test continuous working condition is the continuous opening time of 300s, the ignition curve is as follows Figure 10 As shown; the thrust range of the thruster is 60N, and the bed load range is 4g / cm 2 •s.

[0069] Example 3 The thruster of this embodiment differs from that of embodiment 2 only in that: The structure of the enhanced catalyst bed assembly 2 is as follows Figure 11 As shown: the inner surface of the shell 7 is cylindrical, and the structure of the bed plate 10 and the bed stop plate 13 is as shown. Figure 12 、 Figure 13 As shown, the bed partition plate 10 is a cylindrical flat plate with a plurality of through holes, and the bed stop plate 13 is a cylindrical flat plate with a plurality of through holes in the center; and the flow distribution ratio of the injector 4 and the opening area on the bed partition plate 10 and the bed stop plate 13 in this embodiment are the same as those in Example 2.

[0070] The manufacturing method of the thruster described in this embodiment is the same as that of Example 2.

[0071] The thruster described in this embodiment is applied to a monopropellant thruster system using green and non-toxic propellants. The catalyst used is the same as that in Example 2. The thruster can achieve room temperature or low temperature startup, can pass a 100 s long steady-state test, and can provide a thrust range of 5N to 500N and a bed load range of (1.5 to 6) g / cm 2 •s.

[0072] Example 4 The thruster of this embodiment differs from that of embodiment 1 only in that: The structure of the enhanced catalyst bed assembly 2 is as follows Figure 14 As shown: in the shell 7, the inner surface of the front bed catalyst filling space is cylindrical, the inner surface of the rear bed catalyst filling space is conical, and the small diameter end is the outlet of the shell 7; the bed plate 10 is a cylindrical flat plate with a plurality of through holes, and the bed stop plate 13 is a conical flat plate with a plurality of through holes in the center; and the flow distribution ratio of the injector 4 and the opening area on the bed plate 10 and the bed stop plate 13 in this embodiment are the same as those in Example 1.

[0073] The manufacturing method of the thruster described in this embodiment is the same as that of Example 1.

[0074] The thruster described in this embodiment is applied to a monopropellant thruster system using green non-toxic propellant, and the catalyst used is the same as that in Example 1; the thruster ground test is started at room temperature at 0°C, and the ignition curve is as follows: Figure 15As shown; the thruster ground test continuous working condition is the continuous opening time 200s, the ignition curve is as follows Figure 16 As shown; the rated thrust of the thruster is 150N and the bed load is 4g / cm 2 •s; The 150N thruster provided in this embodiment successfully achieved room temperature start-up and stably completed 200s ignition.

[0075] Example 5 The thruster of this embodiment differs from that of embodiment 4 only in that: The structure of the enhanced catalyst bed assembly 2 is as follows Figure 17 As shown: in the shell 7, the inner surface of the front bed catalyst filling space is conical, and the large diameter end is the inlet of the shell 7, and the inner surface of the rear bed catalyst filling space is cylindrical; the bed plate 10 is a conical flat plate with a plurality of through holes; the bed stop plate 13 is a cylindrical plate with a conical groove with the large diameter end facing outward on the side facing the inlet of the shell 7 and a plurality of through holes on the bottom surface; and the flow distribution ratio of the injector 4 and the opening area on the bed plate 10 and the bed stop plate 13 in this embodiment are the same as those in Example 1.

[0076] The manufacturing method of the thruster described in this embodiment is the same as that of Example 1.

[0077] The thruster described in this embodiment is applied to a monopropellant thruster system using green non-toxic propellant, and the catalyst used is the same as that in Example 1; the thruster ground test is started at room temperature at 0°C, and the ignition curve is as follows: Figure 18 As shown; the thruster ground test continuous working condition is the continuous opening time 100s, the ignition curve is as follows Figure 19 As shown; the rated thrust of the thruster is 300N, and the bed load is 2g / cm 2 •s; The 300N thruster provided in this embodiment successfully achieved room temperature start-up and stably completed 100s ignition.

[0078] Comparative Example 1 The thruster of Comparative Example 1 is as follows Figure 20 The difference between the conventional monopropellant thruster structure shown in the figure and the thrusters of Examples 2 and 3 is that the inner shell surface of the catalyst bed assembly of Comparative Example 1 is cylindrical, and the bed plate 7' and the bed stop plate 13' do not use the structure of enhancing heat and mass transfer proposed by the present invention, but are as follows Figure 20 The cylindrical thin plate with a certain opening rate is shown, but the opening area of ​​the bed plate is less than 60%, and the opening area of ​​the bed stop plate is less than 25%; when this thruster is used to conduct a green propellant hot test, the catalyst used is the same as that in Example 2. Under normal temperature or low temperature conditions, successful startup cannot be achieved, and the chamber pressure disappears, as shown in FIG. Figure 21As shown; and when the orbit control ignites for 100s continuously, there are faults such as chamber pressure drop and flameout, and the stable work cannot be completed, such as Figure 22 shown.

[0079] Comparative Example 2 The difference between the thrusters provided in Comparative Example 2 and Example 1 is that the flow distribution of the injector adopts the principle of uniform distribution. Under the premise of the same nozzle diameter, one nozzle is evenly distributed in every square centimeter. The 150N thruster with this structural design, when carrying out the hot test, uses the same catalyst as Example 1. It fails to pass the 100s long steady-state test. The catalyst bed gradually decreases from the center to the outside until the spray is extinguished. Figure 23 As shown, starting from about 35 seconds, the thrust chamber pressure and catalyst bed temperature began to drop significantly. At about 45 seconds, obvious liquid propellant ejection was seen from the engine outlet, and liquid spraying occurred, causing shutdown.

[0080] 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 above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A monopropellant thruster with enhanced heat and mass transfer, characterized in that: It comprises a uniformly distributed injector assembly (1), an enhanced catalyst bed assembly (2) and a nozzle (3) which are arranged in sequence; The uniformly distributed injector assembly (1) comprises an injector (4), a uniformly distributed net (5) and a support net (6) connected in sequence; the injection surface of the injector (4) is divided into a central area and a peripheral area, and the areas of the central area and the peripheral area are respectively 50% of the area of ​​the injection surface; the flow distribution ratio of the injector (4) in the central area is not higher than 45%, and the flow distribution ratio in the peripheral area is not lower than 55%; the outlets of the capillaries in the injector (4) are uniformly distributed on the injection surface according to concentric circles of different diameters, and the diameter of the innermost concentric circle is greater than the difference between the diameter of the injection surface and the diameter of the outermost concentric circle; The enhanced catalyst bed assembly (2) comprises a shell (7) and a bed partitioning plate net (9), a bed partitioning plate (10), a bed stop plate net (12) and a bed stop plate (13) which are sequentially installed in the axial direction inside the shell (7); the shell (7) inlet serves as the inlet of the enhanced catalyst bed assembly (2) and is connected to the outlet of the uniformly distributed injector assembly (1); the shell (7) outlet serves as the outlet of the enhanced catalyst bed assembly (2) and is connected to the inlet of the nozzle (3); the internal space of the shell (7) is divided into a front bed catalyst filling space and a rear bed catalyst filling space from the inlet to the outlet, the bed partitioning plate net (9) and the bed partitioning plate (10) are located between the front bed catalyst filling space and the rear bed catalyst filling space, and the bed stop plate net (12) and the bed stop plate (13) are located at the other end of the rear bed catalyst filling space; The structure of the housing (7) adopts one of the following four schemes: a. The inner surface of the shell (7) is conical, the large diameter end is the inlet of the shell (7), and the small diameter end is the outlet of the shell (7); b. The inner surface of the shell (7) is cylindrical; c. In the shell (7), the inner surface of the front bed catalyst filling space is conical, and the large diameter end is the inlet of the shell (7), and the inner surface of the rear bed catalyst filling space is cylindrical; d. In the shell (7), the inner surface of the front bed catalyst filling space is cylindrical, the inner surface of the rear bed catalyst filling space is conical, and the small diameter end is the outlet of the shell (7); When the structure of the shell (7) adopts solution a, the bed partition plate (10) and the bed stop plate (13) are both conical flat plates with a plurality of through holes; When the structure of the shell (7) adopts solution b, the structures of the bed partition plate (10) and the bed stop plate (13) respectively adopt one of the following two solutions: a cylindrical plate with a conical groove with a large diameter end facing outward and a bottom surface provided with a plurality of through holes on the side facing the inlet of the shell (7), or a cylindrical flat plate with a plurality of through holes; When the structure of the shell (7) adopts solution c: the bed partition plate (10) is a conical flat plate with a plurality of through holes; the bed stop plate (13) is a cylindrical plate with a conical groove with a large diameter end facing outward on the side facing the inlet of the shell (7) and a plurality of through holes on the bottom surface; When the structure of the shell (7) adopts solution d: the bed partition plate (10) is a cylindrical flat plate with a plurality of through holes; the bed stop plate (13) is a conical flat plate with a plurality of through holes in the center.

2. The monopropellant thruster with enhanced heat and mass transfer according to claim 1, characterized in that: The inner surface of the front bed catalyst filling space is cylindrical, the inner surface of the rear bed catalyst filling space is conical, and the small diameter end is the outlet of the shell (7); the bed plate (10) is a cylindrical flat plate with a plurality of through holes; the bed stop plate (13) is a conical flat plate with a plurality of through holes in the center.

3. The monopropellant thruster with enhanced heat and mass transfer according to claim 1, characterized in that: The inner surface of the front bed catalyst filling space is conical, and the large diameter end is the inlet of the shell (7), and the inner surface of the rear bed catalyst filling space is cylindrical; the bed plate (10) is a conical flat plate with a plurality of through holes; the bed stop plate (13) is a cylindrical plate with a conical groove with the large diameter end facing outward on the side facing the inlet of the shell (7) and a plurality of through holes on the bottom surface.

4. The monopropellant thruster with enhanced heat and mass transfer according to claim 1, characterized in that: The opening area on the bed plate (10) is not less than 60%.

5. The monopropellant thruster with enhanced heat and mass transfer according to claim 1, characterized in that: The opening area on the bed stop plate (13) is not less than 25%.

6. A method for manufacturing a monopropellant thruster with enhanced heat and mass transfer according to any one of claims 1 to 5, characterized in that: The catalyst is loaded into the enhanced catalyst bed assembly (2) in any of the following ways: (1) After the nozzle (3) and the housing (7) are fixedly connected to form an integral structure, the catalyst is loaded from the inlet of the enhanced catalyst bed assembly (2), and then the uniform injector assembly (1) is connected to the enhanced catalyst bed assembly (2); (2) After the uniform injector assembly (1) and the housing (7) are fixedly connected to form an integrated structure, the catalyst is loaded from the outlet of the enhanced catalyst bed assembly (2), and then the nozzle (3) is connected to the enhanced catalyst bed assembly (2).

7. The method for manufacturing a monopropellant thruster with enhanced heat and mass transfer according to claim 6, wherein: When the catalyst is loaded using method (1), the following steps are specifically included: a) connecting the nozzle (3) and the shell (7) into an integral structure by welding; spot welding the bed stop plate net (12) to the bed stop plate (13), and installing the bed stop plate net (12) from the inlet end of the shell (7) onto the bed stop plate mounting platform at the bottom of the shell (7), so that the bed stop plate net (12) faces the inlet of the shell (7); b) filling the rear bed catalyst (11) into the rear bed catalyst filling space of the shell (7) and compacting it; c) installing a bed plate (10) in the housing (7), filling the through holes on the bed plate (10) with the rear bed catalyst (11) and compacting the filler; d) spot welding the bed partition plate mesh (9) to the bed partition plate (10) and the inner wall of the shell (7); e) filling the front bed catalyst (8) into the front bed catalyst filling space of the shell (7) and compacting it; f) Connect the uniform injector assembly (1) to the inlet end of the housing (7) by bolting or welding.

8. The method for manufacturing a monopropellant thruster with enhanced heat and mass transfer according to claim 6, wherein: When the catalyst is loaded using method (2), the following steps are specifically included: a) connecting the uniformly distributed injector assembly (1) and the shell (7) into an integrated structure by welding; loading the front bed catalyst (8) into the front bed catalyst loading space of the shell (7) from the outlet end of the shell (7) and compacting the same; b) spot welding the bed plate mesh (9) to the bed plate (10), with the bed plate mesh (9) facing the front bed catalyst (8), and installing the bed plate mesh (9) and the bed plate (10) together into the housing (7); c) filling the rear bed catalyst (11) into the rear bed catalyst filling space of the shell (7) and compacting it; d) After spot welding the bed stopper mesh (12) to the bed stopper plate (13), the bed stopper mesh (12) is placed facing the rear bed catalyst (11), and the bed stopper mesh (12) and the bed stopper plate (13) are installed together into the housing (7); e) Connect the nozzle (3) to the outlet end of the housing (7) by bolting or welding.

9. An application of a monopropellant thruster with enhanced heat and mass transfer according to any one of claims 1 to 5, characterized in that: The catalyst used in the enhanced catalyst bed assembly (2) is a non-iridium spontaneous catalyst, and the active component is a single metal ruthenium or a bimetallic ruthenium-based catalyst; the normal temperature start-up temperature range of the thruster is 0°C to 35°C; the low temperature start-up temperature range of the thruster is -20°C to 0°C; the continuous opening time of the thruster does not exceed 1800s; the thrust range provided by the thruster is 5N to 500N, and the bed load range is (1.5 to 6) g / cm 2 •s.

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