Supply platform for propulsion engine testing

Abstract

The invention discloses a supply platform for propulsion engine testing, and relates to the technical field of propulsion engine testing platforms. The device comprises a supporting frame and a filling system. An air path extrusion system; and a supply system. The filling system, the gas path extrusion system and the supply system are all arranged on the supporting frame; the gas path extrusion system, the filling system and the supply system are connected in sequence; the filling system is used for storing a propellant; the gas path extrusion system is used for conveying high-pressure gas to the filling system so as to convey a propellant to the supply system; the supply system is used for conveying propellants to the propulsion engine and regulating and controlling the pressure and flow in the pipeline.

Description

Technical Field

[0001] The present invention belongs to the technical field of propulsion engine test platforms, and particularly relates to a supply platform for propulsion engine testing. Background Art

[0002] In the development process of spacecraft propulsion technology, more and more propulsion engines have emerged. The application of propulsion engines requires a large number of tests, so a test platform is essential.

[0003] There are deficiencies in the prior art:

[0004] 1. Different types of propellants require different working pressures, and the working pressure of the pump is not adjustable. Therefore, the pump and related pipelines must be separately configured, resulting in extremely high costs.

[0005] 2. Usually, propellants are corrosive, which will corrode the pumping system and cause a short equipment life.

[0006] 3. It is difficult for each component to be universal, resulting in a long construction period for the test platform.

[0007] The information disclosed in this background art section is only intended to enhance the overall understanding of the present invention and should not be regarded as an admission or any form of implication that this information constitutes prior art already known to those of ordinary skill in the art. Summary of the Invention

[0008] The purpose of the present invention is to solve the problem that the supply work of the test platform cannot adapt to different propellants, thus resulting in excessively high costs, and to provide a supply platform for propulsion engine testing.

[0009] The present invention provides a supply platform for propulsion engine testing, including a support frame, a filling system, a gas path extrusion system, and a supply system.

[0010] The filling system, the gas path extrusion system, and the supply system are all arranged on the support frame;

[0011] The gas path extrusion system, the filling system, and the supply system are connected in sequence;

[0012] The filling system is used to store propellants;

[0013] The gas path extrusion system is used to convey high-pressure gas to the filling system so that the propellants are conveyed to the supply system;

[0014] The supply system is used to convey the propellants to the propulsion engine and regulate the pressure and flow rate in the pipeline.

[0015] In an embodiment of the present invention, the filling system includes a storage tank, the inlet of the storage tank is sequentially connected to a first stop valve and a one-way valve through a pipeline; the outlet of the one-way valve is connected to the first stop valve and the inlet is connected to the gas path extrusion system through a pipeline; the outlet of the storage tank is connected to a second stop valve through a pipeline.

[0016] In an embodiment of the present invention, a safety valve is provided in the pipeline between the inlet of the storage tank and the first stop valve.

[0017] In an embodiment of the present invention, the outlet of the second stop valve is connected to a first filter through a pipeline.

[0018] In an embodiment of the present invention, a corrosion-resistant coating is provided on the inner wall of the storage tank.

[0019] In an embodiment of the present invention, the gas path extrusion system includes a gas solenoid valve, a pressure reducing valve group, and a gas tank sequentially connected through a pipeline; the outlet of the gas solenoid valve is connected to the filling system.

[0020] In an embodiment of the present invention, a second filter is provided in the pipeline between the pressure reducing valve group and the gas tank.

[0021] In an embodiment of the present invention, the supply system includes an explosion-proof solenoid valve, a throttle valve, a flow meter, and an engine filling interface sequentially connected through a pipeline.

[0022] In an embodiment of the present invention, the flow meter is a non-contact flow meter.

[0023] In an embodiment of the present invention, a plurality of casters are provided at the bottom of the support frame.

[0024] Compared with the prior art, the technical effects achieved by the present invention are as follows:

[0025] (1) This solution abandons the traditional pumping method for propellant supply and instead uses high-pressure gas to push out the propellant. The first advantage is that the pumping pressure is adjustable, and its working pressure range is between 0.3 - 15 MPa, which is controlled by the release pressure of the gas tank. The working pressure requirement range of the propulsion engine on a small satellite is generally 1 - 5 MPa, so the current equipment can meet the pressure requirements of all working conditions, and thus the relevant pipelines do not need to be replaced, reducing the equipment cost; second, there is no need to consider corrosion problems during the process of high-pressure helium contacting the propellant, so the service life of the product can be extended.

[0026] (2) The gas tank and the storage tank are independently filled, which is flexible during use, so that this product unit is not limited to one type of propellant.

[0027] (3) Since the supply platform can be moved, on the premise of being able to supply multiple propellants, it can be used as a general product. Under different engine test requirements, the use site can be quickly adjusted to adapt to different test platforms. Description of the Drawings

[0028] Figure 1 is a schematic structural diagram of a supply platform for a propulsion engine test according to an embodiment of the present invention;

[0029] Figure 2 is according to Figure 1 a schematic structural diagram of the hidden support frame in

[0030] Main reference numeral description:

[0031] 11, support frame; 12, casters; 2, filling system; 21, storage tank; 22, safety valve; 23, first stop valve; 24, check valve; 25, second stop valve; 26, first filter; 3, gas path extrusion system; 31, gas solenoid valve; 32, pressure reducing valve group; 33, second filter; 34, gas tank; 35, third stop valve; 4, supply system; 41, explosion-proof solenoid valve; 42, throttle valve; 43, flowmeter; 44, engine filling interface. Detailed Embodiment

[0032] Unless otherwise clearly stated, throughout the specification and claims, the term "comprising" or its variations such as "including" or "having" etc. will be understood to include the stated elements or components, without excluding other elements or other components.

[0033] The technical solutions of the present invention are described below through specific embodiments. It should be understood that one or more steps mentioned in the present invention do not exclude the existence of other methods and steps before and after the combined steps, or other methods and steps can be inserted between these clearly mentioned steps. It should also be understood that these examples are only used to illustrate the present invention and not to limit the scope of the present invention. Unless otherwise specified, the numbers of the method steps are only for the purpose of identifying the method steps, rather than limiting the arrangement order of each method or defining the scope of implementation of the present invention. The change or adjustment of their relative relationship, under the condition of no substantial change in technical content, can also be regarded as the scope in which the present invention can be implemented.

[0034] There are no specific restrictions on the sources of the raw materials and instruments used in the embodiments, and they can be purchased in the market or prepared according to the conventional methods well-known to those skilled in the art.

[0035] As Figures 1 to 2 shown, a supply platform for a propulsion engine test according to a preferred embodiment of the present invention includes a support frame 11, a filling system 2, a gas path extrusion system 3, and a supply system 4.

[0036] The support frame 11 is formed by connecting aluminum profiles. Four casters 12 are provided and installed at the bottom of the support frame 11 to facilitate movement. The filling system 2, the gas circuit extrusion system 3, and the supply system 4 are all fixed on the support frame 11.

[0037] The gas circuit extrusion system 3, the filling system 2, and the supply system 4 are connected in sequence. The filling system 2 is used to store the propellant; the gas circuit extrusion system 3 is used to deliver high-pressure gas to the filling system 2 to send the propellant to the supply system 4; the supply system 4 is used to deliver the propellant to the propulsion engine and regulate the pressure and flow rate in the pipeline.

[0038] The filling system 2 includes a storage tank 21. The inlet of the storage tank 21 is sequentially connected to a safety valve 22, a first stop valve 23, and a check valve 24 through pipelines. The outlet of the check valve 24 is connected to the first stop valve 23. The outlet of the storage tank 21 is sequentially connected to a second stop valve 25 and a first filter 26 through pipelines.

[0039] The gas circuit extrusion system 3 includes a gas solenoid valve 31, a pressure reducing valve group 32, a second filter 33, and a gas tank 34 that are sequentially connected through pipelines. The inlet of the gas solenoid valve 31 is connected to the pressure reducing valve group 32.

[0040] The outlet of the gas solenoid valve 31 is connected to the inlet of the check valve 24.

[0041] The supply system 4 includes an explosion-proof solenoid valve 41, a throttle valve 42, a flow meter 43, and an engine filling interface 44 that are sequentially connected through pipelines. The inlet of the explosion-proof solenoid valve 41 is connected to the first filter 26.

[0042] The function of the safety valve 22 is to prevent the pressure in the pipeline from exceeding the rated value, thus protecting the safety of equipment and personnel. The functions of the first stop valve 23, the second stop valve 25, and the third stop valve 35 are to cut off the fluid and prevent backflow. The storage tank 21 is used to store the propellant. To improve the corrosion resistance of the storage tank 21, a corrosion-resistant coating, specifically a polytetrafluoroethylene coating, is provided on the inner wall of the storage tank 21. The gas tank 34 is used to store high-pressure helium gas. The functions of the gas solenoid valve 31 and the explosion-proof solenoid valve 41 are to control the opening and closing of the pipeline. The pressure reducing valve group 32 includes a pressure reducing valve and a pressure gauge, but they are integrated into one product, which can reduce and control the pipeline pressure and observe the pressure value at the same time. The first filter 26 and the second filter 33 are respectively used to filter the propellant and helium gas. The throttle valve 42 is used to regulate the pipeline flow rate. The flow meter 43 is used to accurately monitor the flow rate in the pipeline. The engine filling interface 44 is used to connect to the propulsion engine and deliver the propellant to the propulsion engine.

[0043] The working principle is as follows: High-pressure helium gas is released from the gas path extrusion system 3 to the filling system 2. Under the action of the high-pressure helium gas, the propellant in the storage tank 21 is pushed into the supply system 4, and the supply system 4 pushes the propellant to the propulsion engine to achieve the supply of the propellant.

[0044] The specific implementation process is as follows:

[0045] (1) Make the filling pressure in the gas tank 34 not less than 30 MPa, and fill the propellant in the storage tank 21 without exceeding 60% of the maximum volume. After the gas tank 34 and the storage tank 21 are prepared, they are connected to the test platform.

[0046] (2) Open the gas solenoid valve 31 and the explosion-proof solenoid valve 41 to establish a passage, adjust the throttle valve 42 to achieve flow regulation, and obtain the flow value based on the flowmeter 43 to feedback to the control of the throttle valve 42. When the flow reaches the target value, such as 30 sccm, then close the gas solenoid valve 31 and the explosion-proof solenoid valve 41.

[0047] (3) Install the propulsion engine in place and connect the engine filling interface 44.

[0048] (4) Keep personnel away and remotely test the propulsion engine.

[0049] The advantages of this solution are as follows:

[0050] (1) This solution abandons the traditional pumping method for propellant supply and uses high-pressure gas to push out the propellant. One of the advantages is that the pumping pressure is adjustable, and its working pressure range is between 0.3 - 15 MPa, which is controlled by the release pressure of the gas tank 34. The working pressure requirement range of the propulsion engine on small satellites is generally 1 - 5 MPa. Therefore, the current equipment can meet the pressure requirements of all working conditions, and the relevant pipelines do not need to be replaced, reducing the equipment cost; furthermore, when high-pressure helium gas contacts the propellant, the corrosion problem does not need to be considered, so the service life of the product can be extended.

[0051] (2) Both the gas tank 34 and the storage tank 21 are independently filled, which is flexible during use, making this product unit not limited to one type of propellant.

[0052] (3) Since the supply platform can be moved, on the premise of having the above two advantages, it can be used as a general product. Under different engine test requirements, the use site can be quickly adjusted to adapt to different test platforms, shortening the construction cycle of the test platform.

[0053] The foregoing description of the specific exemplary embodiments of the present invention is for purposes of illustration and exemplification. These descriptions are not intended to limit the invention to the precise forms disclosed, and it is apparent that many modifications and variations are possible in light of the above teachings. The purpose of selecting and describing the exemplary embodiments is to explain the specific principles of the present invention and its practical applications, so that those skilled in the art can implement and utilize the various different exemplary embodiments of the present invention, as well as various different selections and modifications. The scope of the present invention is intended to be defined by the claims and their equivalents.

Claims

1. A supply platform for promoting engine testing, characterized in that It includes a support frame, a filling system, a gas path extrusion system, and a supply system. The filling system, the gas path extrusion system, and the supply system are all arranged on the support frame; The gas path extrusion system, the filling system, and the supply system are connected in sequence; The filling system is used to store propellants; The gas path extrusion system is used to convey high-pressure gas to the filling system so that the propellants are conveyed to the supply system; The supply system is used to convey the propellants to a propulsion engine and regulate the pressure and flow rate in the pipeline.

2. The supply platform for the propulsion engine test according to claim 1, characterized in that, The filling system includes a storage tank. The inlet of the storage tank is sequentially connected to a first stop valve and a check valve through pipelines. The outlet of the check valve is connected to the first stop valve, and the inlet is connected to the gas path extrusion system through a pipeline. The outlet of the storage tank is connected to a second stop valve through a pipeline.

3. The supply platform for the propulsion engine test according to claim 2, characterized in that, A safety valve is provided in the pipeline between the inlet of the storage tank and the first stop valve.

4. The supply platform for propulsion engine testing according to claim 2, characterized in that, The outlet of the second stop valve is connected to a first filter through a pipeline.

5. The supply platform for the propulsion engine test according to claim 2, characterized in that The inner wall of the storage tank is provided with a corrosion-resistant coating.

6. The supply platform for propulsion engine testing according to claim 1, characterized in that, The gas path extrusion system includes a gas solenoid valve, a pressure reducing valve group, and a gas tank that are sequentially connected through pipelines. The outlet of the gas solenoid valve is connected to the filling system.

7. The supply platform for the propulsion engine test according to claim 6, characterized in that, A second filter is provided in the pipeline between the pressure reducing valve group and the gas tank.

8. The supply platform for propulsion engine testing according to claim 1, characterized in that, The supply system includes an explosion-proof solenoid valve, a throttle valve, a flow meter, and an engine filling interface that are sequentially connected through pipelines.

9. The supply platform for the propulsion engine test according to claim 8, characterized in that, The flow meter is a non-contact flow meter.

10. The supply platform for the propulsion engine test according to claim 1, characterized in that, Multiple casters are provided at the bottom of the support frame.

Images