Pressure reducer performance online testing device and method for liquid propulsion attitude control power system

Abstract

The invention discloses a pressure reducer performance online testing device and method for a liquid propulsion attitude control power system. The online testing device is mainly composed of an inert gas source, a first high-pressure testing pipeline, a pressure reducer online testing module, a second high-pressure testing pipeline, an attitude control system product module and a low-pressure testing pipeline. The pressure reducer on-line test module is mainly composed of a high-pressure circuit and a low-pressure circuit, the high-pressure circuit comprises a high-pressure pressure gauge, a first hand valve and a filter which are connected in series, and the low-pressure circuit comprises a second hand valve, a safety valve and a low-pressure pressure gauge which are connected in series. During on-line testing, the inert gas source is opened, the first hand valve is opened, and the outlet locking pressure of the pressure reducer is tested by interpreting the reading of the low-pressure pressure gauge; and the second hand valve is continuously opened, and the dynamic precision pressure of the outlet of the pressure reducer is tested by interpreting the reading of the low-pressure pressure gauge. According to the invention, online testing can be realized, the actual outlet dynamic precision and the locking pressure of the pressure reducer can be known and mastered in time, and the pressure reducer can be ensured to work safely and reliably in the flight test process of the system.

Description

Technical Field

[0001] The invention belongs to the technical field of liquid propulsion attitude control power system testing, and relates to an online testing device and method for the performance of a pressure reducer for a liquid propulsion attitude control power system. Background Art

[0002] The liquid propulsion attitude control power system for launch vehicles generally adopts a constant pressure extrusion scheme. The pressure of the high-pressure gas cylinder is not less than 35MPa. When the high-pressure electric explosion valve on the high-pressure gas pipeline is detonated, the pressure reducer adjusts the high-pressure gas at the inlet to stabilize the outlet dynamic accuracy pressure to AMPa±0.2MPa (A is not greater than 3.5MPa), and the outlet locking pressure is not greater than 3.8MPa, providing stable and reliable working pressure and safety pressure for the tank air cavity, liquid pipeline, solenoid valve and engine room pressure downstream of the attitude control system, which has a huge impact on the normal operation of the attitude control system and precise attitude control.

[0003] For the above reasons, it is very important to install a pressure reducer on the upstream gas path of the tank gas cavity, and the pressure reducer can provide a stable and reliable pressure range for the system. After the pressure reducer is installed in the system product, the system product needs to timely understand and master the actual working performance of the pressure reducer during the factory test, assembly plant test and launch site test, to ensure that the pressure reducer can work safely and reliably during the flight test, and to ensure that the system successfully completes the flight test mission. Summary of the invention

[0004] The present invention aims to provide an online testing device and method for the performance of a pressure reducer for a liquid propulsion attitude control power system. After the pressure reducer is installed in a system product, the system product can timely understand and grasp the actual working performance (outlet dynamic accuracy and locking pressure) of the pressure reducer in the form of online detection during various stages such as factory testing, final assembly plant testing and launch site testing, so as to ensure that the pressure reducer can work safely and reliably during the flight test of the system and ensure that the system successfully completes the flight test mission.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] An online testing device for the performance of a pressure reducer for a liquid propulsion attitude control power system, comprising:

[0007] Inert gas source;

[0008] A pressure reducer online test module, the pressure reducer online test module mainly consists of a high-pressure circuit and a low-pressure circuit, wherein the high-pressure circuit includes a high-pressure pressure gauge, a first hand valve and a filter connected in series, and the low-pressure circuit includes a second hand valve, a safety valve and a low-pressure pressure gauge connected in series, the inlet of the high-pressure pressure gauge is connected to the outlet of the inert gas source via the first high-pressure test pipeline, and the outlet of the second hand valve is connected to the rated flow device;

[0009] An attitude control system product module, the attitude control system product module comprising a first test interface arranged on the high-pressure side of the pressure reducer and a second test interface arranged on the low-pressure side of the pressure reducer, and a high-pressure electric explosion valve connected to the pressure reducer, the first test interface being located between the high-pressure electric explosion valve and the pressure reducer, and the second test interface being located between the pressure reducer and the tank air cavity;

[0010] a second high-pressure test pipeline, one end of which is connected to the first test interface, and the other end of which is connected to the outlet of the filter;

[0011] A low-pressure test pipeline, one end of which is connected to the inlet of the low-pressure pressure gauge, and the other end of which is connected to the second test interface.

[0012] As a solution, the inert gas source is a nitrogen bottle with a built-in shut-off valve.

[0013] As a solution:

[0014] The first high-pressure test pipeline is connected to the inert gas source and the high-pressure pressure gauge respectively through a combination of a ball joint and a jacket nut;

[0015] The second high-pressure test pipeline is connected to the first test interface and the filter respectively through a combination of a spherical joint and a jacket nut;

[0016] The low-pressure test pipeline is connected to the low-pressure pressure gauge and the second test interface respectively through a combination of a spherical joint and a sleeve nut.

[0017] As a solution, the second test interface includes a reversing valve, which seals and isolates the pipeline from the low-pressure side of the pressure reducer to the air chamber of the tank while connecting the low-pressure side of the pressure reducer to the low-pressure pressure gauge through the low-pressure test pipeline.

[0018] An online testing method for the performance of a pressure reducer for a liquid propulsion attitude control power system adopts the online testing device including the reversing valve and comprises the following steps:

[0019] Step 1: Open the reversing valve to connect the low-pressure side of the pressure reducer to the low-pressure gauge through the low-pressure test pipeline, open the inert gas source, open the first hand valve, and test the outlet locking pressure of the pressure reducer by reading the low-pressure gauge.

[0020] Step 2: Continue to open the second manual valve and test the outlet dynamic accuracy pressure of the pressure reducer by reading the low-pressure pressure gauge.

[0021] Compared with the prior art, the online performance testing device for the pressure reducer of the liquid propulsion attitude control power system of the present invention has a sophisticated structure and is particularly suitable for online testing on system products, so as to timely understand and grasp the actual working performance of the pressure reducer under actual working conditions, and make full use of the test interface and external test pipeline module set up in the system to carry out online performance testing of the pressure reducer as required. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is an assembly diagram of an online performance testing device for a pressure reducer for a liquid propulsion attitude control power system of the present invention;

[0023] In the figure: 1—inert gas source; 2—first high-pressure test pipeline; 3—pressure reducer online test module; 4—second high-pressure test pipeline; 5—attitude control system product module; 6—low-pressure test pipeline. DETAILED DESCRIPTION

[0024] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0025] like Figure 1 As shown, an online test device for the performance of a pressure reducer for a liquid propulsion attitude control power system is mainly composed of an inert gas source 1, a first high-pressure test pipeline 2, a pressure reducer online test module 3, a second high-pressure test pipeline 4, an attitude control system product module 5 and a low-pressure test pipeline 6. Figure 1 The arrows at the module inlet 1, module outlet 1, and module inlet 2 indicate the gas flow direction.

[0026] Among them, the pressure reducer online test module 3 includes a high-pressure circuit and a low-pressure circuit. The high-pressure circuit is mainly composed of a high-pressure pressure gauge P1 (pressure range is 0MPa~15MPa), a first manual valve K1 and a filter (GLQ) in series; the low-pressure circuit is mainly composed of a low-pressure pressure gauge P2 (pressure range is 0MPa~5MPa), a second manual valve K01 and a safety valve (AQF) in series.

[0027] The attitude control system product module 5 is the online test area for the performance of the pressure reducer, which is mainly composed of a high-pressure electric explosion valve (DBF), a first test interface CS2, a pressure reducer (JYQ), a second test interface CS3 and pipelines.

[0028] Before testing the online performance of the pressure reducer on the attitude control system product, install the ball joint + outer nut (M16×1.5) of the first high-pressure test pipeline 2 at the welding nozzle of the module inlet 1 of the pressure reducer online test module 3, and install the ball joint + outer nut (M16×1.5) at the other end of the first high-pressure test pipeline 2 to the welding nozzle of the inert gas source 1. The inert gas source 1 is a standard nitrogen cylinder with a stop valve.

[0029] The first test interface CS2 includes a tee, and the three interfaces of the tee are respectively connected to the high-voltage electric explosion valve, the second high-voltage test pipeline 4 and the pressure reducer. The ball joint + outer sleeve nut (M16×1.5) of the second high-voltage test pipeline 4 is installed by welding the take-over nozzle at the first test interface CS2 of the attitude control system product module 5, and the ball joint + outer sleeve nut (M16×1.5) at the other end of the second high-voltage test pipeline 4 is installed to the module outlet 1 of the pressure reducer online test module 3.

[0030] A three-way reversing valve is installed at the second test interface CS3 of the attitude control system product module 5, which is respectively connected to the pressure reducer, the tank air cavity and the low-pressure test pipeline 6. The action of the reversing valve can seal and cut off the pipeline leading to the tank air cavity while switching to the low-pressure test pipeline 6. One end of the low-pressure test pipeline 6 is connected to the reversing valve through a ball joint + outer sleeve nut, and the other end of the low-pressure test pipeline 6 is installed to the module inlet 2 welding nozzle of the pressure reducer online test module 3 by using a ball joint + outer sleeve nut, and is connected to the low-pressure pressure gauge P2.

[0031] A rated flow device is installed at the welding nozzle of the module outlet 2 of the pressure reducer online test module 3. The rated flow device in this embodiment is a rated flow throttling orifice plate.

[0032] The welding nozzle in this embodiment is a nozzle with a conical bell mouth and external threads, and is installed in cooperation with a spherical joint+jacket nut.

[0033] The function of the high-pressure pressure gauge P1 in this embodiment is to monitor the pressure data changes of the high-pressure circuit in real time.

[0034] When testing the performance of the pressure reducer on the attitude control system product online, the reversing valve is used to seal and cut off the pipeline leading to the tank air chamber, while switching to the low-pressure test pipeline 6, open the manual valve of the nitrogen bottle, open the first manual valve K1, and test the outlet locking pressure of the pressure reducer by reading the low-pressure pressure gauge P2 (should be no more than 3.8MPa); continue to open the second manual valve K01, and test the outlet dynamic accuracy pressure of the pressure reducer by reading the low-pressure pressure gauge P2 (the pressure should be AMPa±0.2MPa (A is no more than 3.5MPa)).

[0035] The above are the main concepts of the invention. All online testing devices and methods for the performance of pressure reducers for liquid propulsion attitude control power systems designed based on the concepts of the present invention fall within the protection scope of the present invention.

Claims

1. An online performance test device for a pressure reducer for a liquid propulsion attitude control power system, characterized in that: include: Inert gas source (1); A pressure reducer online test module (3), the pressure reducer online test module (3) mainly consisting of a high-pressure circuit and a low-pressure circuit, wherein the high-pressure circuit comprises a high-pressure pressure gauge, a first hand valve and a filter connected in series, and the low-pressure circuit comprises a second hand valve, a safety valve and a low-pressure pressure gauge connected in series, the inlet of the high-pressure pressure gauge is connected to the outlet of the inert gas source (1) via a first high-pressure test pipeline (2), and the outlet of the second hand valve is connected to a rated flow device; An attitude control system product module (5), the attitude control system product module (5) comprising a first test interface arranged on the high-pressure side of the pressure reducer and a second test interface arranged on the low-pressure side of the pressure reducer, and a high-pressure electric explosion valve connected to the pressure reducer, the first test interface being located between the high-pressure electric explosion valve and the pressure reducer, and the second test interface being located between the pressure reducer and the tank air cavity; A second high-pressure test pipeline (4), one end of the second high-pressure test pipeline (4) being connected to the first test interface, and the other end of the second high-pressure test pipeline (4) being connected to the outlet of the filter; A low-pressure test pipeline (6), one end of which is connected to the inlet of the low-pressure pressure gauge, and the other end of which is connected to the second test interface.

2. The on-line testing device for the performance of a pressure reducer for a liquid propulsion attitude control power system according to claim 1, characterized in that: The inert gas source (1) is a nitrogen gas bottle with a built-in shut-off valve.

3. The on-line testing device for the performance of a pressure reducer for a liquid propulsion attitude control power system according to claim 1, characterized in that: The first high-pressure test pipeline (2) is connected to the inert gas source and the high-pressure pressure gauge respectively through a combination of a spherical joint and a sleeve nut; The second high-pressure test pipeline (4) is connected to the first test interface and the filter respectively through a combination of a spherical joint and a sleeve nut; The low-pressure test pipeline (6) is respectively connected to the low-pressure pressure gauge and the second test interface through a combination of a spherical joint and a sleeve nut.

4. The on-line performance testing device for a pressure reducer for a liquid propulsion attitude control power system according to claim 1, characterized in that: The second test interface comprises a reversing valve, which seals and cuts off the pipeline from the low-pressure side of the pressure reducer to the air chamber of the tank while connecting the low-pressure side of the pressure reducer to the low-pressure pressure gauge via a low-pressure test pipeline (6).

5. A method for online testing the performance of a pressure reducer for a liquid propulsion attitude control power system, characterized in that: The online testing device of claim 4 is adopted, and comprises the following steps: Step 1: Open the reversing valve so that the low-pressure side of the pressure reducer is connected to the low-pressure gauge via the low-pressure test pipeline (6), open the inert gas source, open the first hand valve, and test the outlet locking pressure of the pressure reducer by reading the low-pressure gauge; Step 2: Continue to open the second manual valve and test the outlet dynamic accuracy pressure of the pressure reducer by reading the low-pressure pressure gauge.

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