Testing device of liquid propellant auxiliary power system
By setting a stop valve, flowmeter, leakage valve and solenoid valve in the test device of the liquid propellant auxiliary power system, the problems of insufficient pre-cooling of the liquid propellant pipeline and poor impulse response are solved, and the rapid pre-cooling and stable flow of the liquid propellant are achieved, which significantly improves the stability and performance verification effect of the test device.
Patent Information
- Application Number
- CN202422079346.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-27
- Publication Date
- 2025-06-13
- Estimated Expiration
- 2034-08-27
AI Technical Summary
In liquid rockets, the auxiliary power system of the low-temperature liquid propellant is small inflow and unstable in working mode, resulting in insufficient pre-cooling of the pipeline and the non-flow of propellant, resulting in unstable working of the thrust chamber and poor pulse effect, making it difficult to verify the performance of the thrust chamber.
Design a test device for a liquid propellant auxiliary power system. By setting a stop valve, a flowmeter, a leakage valve and a solenoid valve on the propellant pipeline in turn, the rapid pre-cooling of the liquid propellant and real-time flow monitoring are achieved, ensuring the liquid state of the propellant in the pipeline and improving the impulse response of the test device.
The full pre-cooling of the pipeline and the improvement of impulse response have been achieved, ensuring that the propellant remains in liquid state during the test, and the stability and performance verification effect have been significantly improved.
Smart Images
Figure CN222976927U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of aerospace engines, and particularly relates to a test device for a liquid propellant auxiliary power system. Background Art
[0002] When a liquid rocket uses cryogenic liquid propellants, due to the small flow rate of the rocket's auxiliary power system and the existence of an irregular pulsed working mode, it is easy to cause phenomena such as insufficient precooling in the pipeline and non-flow of the propellant in the pipeline, resulting in the "gasification" of the cryogenic propellant, making the thrust chamber work unstably and having a poor pulsed effect, which brings difficulties to the performance verification of the thrust chamber.
[0003] In view of this, it is urgent to design a test device for a liquid propellant auxiliary power system that can achieve sufficient precooling of the pipeline and improve the pulse response. Summary of the Utility Model
[0004] The purpose of the utility model is to overcome the deficiencies of the prior art and provide a test device for a liquid propellant auxiliary power system.
[0005] The utility model provides a test device for a liquid propellant auxiliary power system, including: a liquid oxidizer storage tank for storing liquid oxidizer; a liquid oxidizer pre-pipeline arranged upstream of the liquid oxidizer storage tank for introducing pressurized gas into the liquid oxidizer storage tank; a first pipeline connected between the liquid oxidizer storage tank and the thrust chamber, and a first stop valve, a first flow meter, a first drain valve and a first solenoid valve are sequentially arranged on the first pipeline from upstream to downstream; a liquid fuel storage tank for storing liquid fuel; a liquid fuel pre-pipeline arranged upstream of the liquid fuel storage tank for introducing pressurized gas into the liquid fuel storage tank; a second pipeline connected between the liquid fuel storage tank and the thrust chamber, and a second stop valve, a second flow meter, a second drain valve and a second solenoid valve are sequentially arranged on the second pipeline from upstream to downstream.
[0006] According to an embodiment of the present application, the first drain valve is arranged on a first branch of the first pipeline.
[0007] According to an embodiment of the present application, a first drain path cavitation tube in series with the first drain valve is further arranged on the first branch.
[0008] According to an embodiment of the present application, there are two first drain valves, and the other drain valve is arranged on a second branch of the first pipeline.
[0009] According to an embodiment of the present application, a first purging path communicating with the first pipeline is further arranged at the end of the first pipeline close to the thrust chamber.
[0010] According to an embodiment of the present application, the second drain valve is disposed on the third branch of the second pipeline.
[0011] According to an embodiment of the present application, a second drain line cavitation tube connected in series with the second drain valve is further disposed on the third branch.
[0012] According to an embodiment of the present application, there are two second drain valves, and the other drain valve is disposed on the fourth branch of the second pipeline.
[0013] According to an embodiment of the present application, a second purge line communicating with the second pipeline is further disposed at the end of the second pipeline close to the thrust chamber.
[0014] According to an embodiment of the present application, the liquid oxidant is liquid oxygen and the liquid fuel is liquid methane.
[0015] The test device of the liquid propellant auxiliary power system of the present application can monitor the flow rate of the liquid propellant in real time by sequentially arranging a stop valve, a flow meter, a drain valve and a solenoid valve on the pipeline of the propellant, realize rapid precooling of the propellant and have no pipeline blind cavity, ensure that the propellant in the pipeline remains in a liquid state, and effectively improve the pulse response of the test device.
[0016] It should be understood that the above general description and the following specific embodiments are only exemplary and explanatory, and cannot limit the scope claimed by the present invention. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The following drawings are part of the specification of the present invention, which illustrate exemplary embodiments of the present invention. The accompanying drawings, together with the description of the specification, are used to explain the principles of the present invention.
[0018] Figure 1 It is a schematic diagram of a test device for a liquid propellant auxiliary power system according to an embodiment of the present invention;
[0019] Figure 2 It is a schematic diagram of a test device for a liquid propellant auxiliary power system according to another embodiment of the present invention.
[0020] Reference Signs:
[0021] 100 - First pipeline, 101 - Liquid oxidant storage tank, 102 - Liquid oxidant front pipeline, 103 - First stop valve, 104 - First flowmeter, 105 - First drain valve, 106 - First solenoid valve, 107 - First drain path cavitation tube, 108 - First purging path, 200 - Second pipeline, 201 - Liquid fuel storage tank, 202 - Liquid fuel front pipeline, 203 - Second stop valve, 204 - Second flowmeter, 205 - Second drain valve, 206 - Second solenoid valve, 207 - Second drain path cavitation tube, 208 - Second purging path. Detailed implementation manners
[0022] The features of each aspect and the exemplary embodiments of the present invention will be described in detail below. In order to make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention, for exemplarily illustrating the principle of the present invention, and are not configured to limit the present invention. In addition, the components in the drawings are not necessarily drawn to scale. For example, the dimensions of some components or regions in the drawings may be enlarged for other components or regions to help understand the embodiments of the present invention.
[0023] The orientation terms appearing in the following description are all the directions shown in the drawings, and do not limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that unless otherwise specified, the terms "installed", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0024] In addition, the terms "including", "comprising", "having" or any other variant thereof are intended to cover non-exclusive inclusion, so that a series of elements, structures or components include not only those elements, but also other components that are not explicitly listed or are inherent to the structures and components. Without further limitation, the elements defined by the statement "including..." do not exclude the existence of additional identical elements in the articles or devices including the elements.
[0025] Spatial relationship terms such as "below", "beneath", "under", "lower", "above", "on", "higher", etc. are used for convenience of description to explain the positioning of one element relative to a second element, and these terms are intended to cover different orientations of the device in addition to orientations different from those shown in the figures. Additionally, for example, "one element is on / under another element" may mean that the two elements are in direct contact or that there are other elements between the two elements. Furthermore, terms such as "first", "second", etc. are also used to describe various elements, regions, parts, etc., and should not be construed as limiting. Similar terms denote similar elements throughout the description.
[0026] For those skilled in the art, the present utility model can be implemented without some of these specific details. The following description of the embodiments is only provided to better understand the present utility model by showing examples of the present utility model.
[0027] Figure 1 is a schematic diagram of a test device for a liquid propellant auxiliary power system according to an embodiment of the present utility model; Figure 2 is a schematic diagram of a test device for a liquid propellant auxiliary power system according to another embodiment of the present utility model.
[0028] As Figure 1 shown, the present utility model provides a test device for a liquid propellant auxiliary power system, including a liquid oxidizer storage tank 101 for storing liquid oxidizer; a liquid oxidizer front pipeline 102 provided upstream of the liquid oxidizer storage tank 101 for introducing pressurized gas into the liquid oxidizer storage tank 101; a first pipeline 100 connected between the liquid oxidizer storage tank 101 and the thrust chamber T, and the first pipeline 100 is sequentially provided with a first shut-off valve 103, a first flowmeter 104, a first drain valve 105, and a first solenoid valve 106 from upstream to downstream; a liquid fuel storage tank 201 for storing liquid fuel; a liquid fuel front pipeline 202 provided upstream of the liquid fuel storage tank 201 for introducing pressurized gas into the liquid fuel storage tank 201; a second pipeline 200 connected between the liquid fuel storage tank 201 and the thrust chamber T, and the second pipeline 200 is sequentially provided with a second shut-off valve 203, a second flowmeter 204, a second drain valve 205, and a second solenoid valve 206 from upstream to downstream.
[0029] Specifically, the first shut-off valve 103 is used to control the cut-off of the liquid oxidizer from the storage tank to the first pipeline 100, and the second shut-off valve 203 is used to control the cut-off of the liquid fuel from the storage tank to the second pipeline 200. The first flowmeter 104 is used to measure the flow rate of the liquid oxidizer in the first pipeline 100 during the test, and the second flowmeter 204 is used to measure the flow rate of the liquid fuel in the second pipeline 200 during the test. The first drain valve 105 is used to control the flow discharge of the liquid oxidizer during the test, and the second drain valve 205 is used to control the flow discharge of the liquid fuel during the test. The first solenoid valve 106 is used to control the on-off of the liquid oxidizer in the first pipeline 100 entering the thrust chamber T, and the second solenoid valve 206 is used to control the on-off of the liquid oxidizer in the second pipeline 200 entering the thrust chamber T.
[0030] Among them, the flow of the liquid oxidizer in the first pipeline 100 is as follows: The booster gas provided by the pipeline 102 in front of the liquid oxidizer enables the liquid oxidizer storage tank 101 to reach the target pressure. The liquid oxidizer flows out from the bottom of the liquid oxidizer storage tank 101, flows through the first shut-off valve 103, the first flowmeter 104, reaches the thrust chamber T through the first solenoid valve 106, and part of the liquid oxidizer is discharged from the first drain valve 105.
[0031] Among them, the flow of the liquid fuel in the second pipeline 200 is as follows: The booster gas provided by the pipeline 202 in front of the liquid fuel enables the liquid fuel storage tank 201 to reach the target pressure. The liquid fuel flows out from the bottom of the liquid fuel storage tank 201, flows through the second shut-off valve 203, the second flowmeter 204, reaches the thrust chamber T through the second solenoid valve 206, and part of the liquid fuel is discharged from the second drain valve 205.
[0032] In this embodiment, by sequentially arranging the first shut-off valve 103, the first flowmeter 104, the first drain valve 105, and the first solenoid valve 106 on the first pipeline 100 for transporting the liquid oxidizer, the flow rate of the liquid oxidizer can be monitored in real time, rapid precooling of the liquid oxidizer can be achieved, and there is no pipeline blind cavity, so that the liquid oxidizer in the first pipeline 100 remains in a liquid state, effectively improving the pulse response of the test device. Similarly, in this application, by sequentially arranging the second shut-off valve 203, the second flowmeter 204, the second drain valve 205, and the second solenoid valve 206 on the second pipeline 200 for transporting the liquid fuel, the flow rate of the liquid fuel can be monitored in real time, rapid precooling of the liquid fuel can be achieved, and there is no pipeline blind cavity, so that the liquid fuel in the second pipeline 200 remains in a liquid state, effectively improving the pulse response of the test device.
[0033] As Figure 2 shown, according to an embodiment of the present application, the first drain valve 105 is arranged on the first branch of the first pipeline 100.
[0034] According to an embodiment of the present application, a first drain path cavitation tube 107 in series with the first drain valve 105 is further provided on the first branch path.
[0035] According to an embodiment of the present application, there are two first drain valves 105, and another drain valve is provided on the second branch path of the first pipeline 100.
[0036] According to an embodiment of the present application, a first purge path 108 communicating with the first pipeline is further provided at the end of the first pipeline 100 close to the thrust chamber T, and a solenoid valve for opening and closing is provided on the first purge path 108.
[0037] According to an embodiment of the present application, the second drain valve 205 is provided on the third branch path of the second pipeline 200.
[0038] According to an embodiment of the present application, a second drain path cavitation tube 207 in series with the second drain valve 205 is further provided on the third branch path.
[0039] According to an embodiment of the present application, there are two second drain valves 205, and another drain valve is provided on the fourth branch path of the second pipeline 200.
[0040] According to an embodiment of the present application, a second purge path 208 communicating with the second pipeline 200 is further provided at the end of the second pipeline 200 close to the thrust chamber T, and a solenoid valve for opening and closing the second purge path 208 is provided on the second purge path 208.
[0041] According to an embodiment of the present application, the liquid oxidizer is liquid oxygen and the liquid fuel is liquid methane.
[0042] Specifically, the first drain valve 105 and the first drain path cavitation tube 107 on the first branch path cooperate with each other to realize the precooling of the first pipeline 100 before the test and the flow discharge of the liquid oxidizer during the test. If the discharge amount is large, the other first drain valve 105 on the second branch path can be controlled for discharge. The second drain valve 205 and the second drain path cavitation tube 207 on the third branch path cooperate with each other to realize the precooling of the second pipeline 200 before the test and the flow discharge of the liquid fuel during the test. If the discharge amount is large, the other second drain valve 205 on the fourth branch path can be controlled for discharge.
[0043] Among them, the first purge path 108 is used to control the purge of the oxidizer head cavity of the thrust chamber T before startup, isolate air and avoid ice blockage when low-temperature liquid oxidizer enters the head cavity. The second purge path 208 is used to control the purge of the fuel head cavity of the thrust chamber T before startup, isolate air and avoid ice blockage when low-temperature liquid fuel enters the head cavity.
[0044] Furthermore, the liquid oxidizer tank 101 can be filled with supercooled liquid oxygen, and the liquid fuel tank 201 can be filled with supercooled methane. Among them, the target working pressure of the thrust chamber T is determined, and the corresponding saturation temperature of the propellant is determined. After exceeding the saturation temperature, the cryogenic propellant will change from liquid to gas. By using supercooled propellant, the liquid temperature of the propellant will be reduced, and the difference between the saturation temperature and the initial liquid temperature entering the thrust chamber will increase during the working process, which is beneficial to keeping the propellant in a liquid state during the working process, reducing gasification, and maintaining the stability of the working characteristics of the thrust chamber. The lengths of the first pipeline 100 and the second pipeline 200 are as short as possible, and adiabatic coating is carried out on the outer sides of the first pipeline 100 and the second pipeline 200 to reduce heat exchange. During the pre-cooling process, nitrogen protection of the oxygen head cavity and methane head cavity of the thrust chamber T is achieved through the first purge path 108 and the second purge path 208, so as to avoid ice blockage when liquid oxygen or liquid methane enters the head cavity. For example, the purge of the oxygen head cavity and methane head cavity can be stopped two seconds before the test.
[0045] In specific operations, when pre-cooling the first pipeline 100 and the second pipeline 200 before the test, the first drain valve 105 on the second branch and the second drain valve 205 on the fourth branch are opened to achieve rapid pre-cooling of the first pipeline 100 and the second pipeline 200. Two seconds before the test, the first drain valve 105 on the second branch and the second drain valve 205 on the fourth branch are closed, and the first drain valve 105 on the first branch and the second drain valve 205 on the third branch are opened.
[0046] The test device of the present application can achieve control of the propellant discharge flow rate through the first drain path cavitation tube 107 and the second drain path cavitation tube 207 corresponding to the first drain valve 105 and the second drain valve 205, simulate the discharge amount of the propellant during actual flight, improve the flow state of the first pipeline 100 and the second pipeline 200, and keep the propellant in a liquid cryogenic state during the test process.
[0047] In an optional embodiment, the first solenoid valve 106 and the second solenoid valve 206 are integrally designed with the thrust chamber T, and the outlets of the first solenoid valve 106 and the second solenoid valve 206 are the inlets of the thrust chamber T. This method can reduce the cavity between the two components and achieve sealing at the inlet of the thrust chamber T, improving the response ability of the thrust device in the pulse working mode.
[0048] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.
Claims
1. A test device for a liquid propellant auxiliary power system, characterized in that: include: A liquid oxidant storage tank, used for storing liquid oxidant; A liquid oxidant front pipeline, arranged upstream of the liquid oxidant tank, for introducing pressurized gas from the liquid oxidant tank; A first pipeline is connected between the liquid oxidant tank and the thrust chamber, wherein the first pipeline is provided with a first stop valve, a first flow meter, a first discharge valve and a first solenoid valve in sequence from upstream to downstream; Liquid fuel tank, used for storing liquid fuel; A liquid fuel front pipeline, arranged upstream of the liquid fuel tank, for introducing pressurized gas into the liquid fuel tank; The second pipeline is connected between the liquid fuel tank and the thrust chamber. The second pipeline is provided with a second stop valve, a second flow meter, a second discharge valve and a second solenoid valve in sequence from upstream to downstream.
2. The test device for the liquid propellant auxiliary power system according to claim 1, characterized in that: The first discharge valve is disposed on the first branch of the first pipeline.
3. The test device for the liquid propellant auxiliary power system according to claim 2, characterized in that: The first branch is also provided with a first discharge cavitation pipe connected in series with the first discharge valve.
4. The test device for a liquid propellant auxiliary power system according to claim 2, characterized in that: There are two first discharge valves, and another of the discharge valves is disposed on the second branch of the first pipeline.
5. The test device for the liquid propellant auxiliary power system according to claim 1, characterized in that: A first blow-off passage communicating with the first pipeline is also provided at the end of the first pipeline close to the thrust chamber.
6. The test device for a liquid propellant auxiliary power system according to claim 1, characterized in that: The second discharge valve is disposed on the third branch of the second pipeline.
7. The test device for a liquid propellant auxiliary power system according to claim 6, characterized in that: The third branch is also provided with a second discharge cavitation pipe connected in series with the second discharge valve.
8. The test device for the liquid propellant auxiliary power system according to claim 6, characterized in that: There are two second discharge valves, and another of the discharge valves is disposed on the fourth branch of the second pipeline.
9. The test device for a liquid propellant auxiliary power system according to claim 1, characterized in that: A second blow-off passage communicating with the second pipeline is also provided at the end of the second pipeline close to the thrust chamber.
10. The test device for a liquid propellant auxiliary power system according to any one of claims 1 to 9, characterized in that: The liquid oxidant is liquid oxygen, and the liquid fuel is liquid methane.