CN111929043A - Performance test system and method for aircraft ejector - Google Patents
Performance test system and method for aircraft ejector Download PDFInfo
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- CN111929043A CN111929043A CN202010670080.7A CN202010670080A CN111929043A CN 111929043 A CN111929043 A CN 111929043A CN 202010670080 A CN202010670080 A CN 202010670080A CN 111929043 A CN111929043 A CN 111929043A
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- air inlet
- aircraft ejector
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
The invention discloses a performance test system of an aircraft ejector, which comprises a test cabin, an air bottle and a slide simulator, wherein the aircraft ejector is arranged in the test cabin, and the air bottle is connected with the aircraft ejector through an air inlet pipeline; the back end of the test chamber is provided with an air inlet, the front end of the test chamber is provided with an air inlet chamber, the front end of the air inlet chamber is provided with an air outlet, the back end of the air inlet chamber is tightly connected with the test chamber, the back end of the air inlet chamber is provided with an opening, the aircraft ejector main body is arranged in the test chamber, the nozzle insertion opening of the aircraft ejector is arranged in the air inlet chamber, and the slide simulator is positioned at the air outlet; the slide simulator is used for simulating the change of internal back pressure when the slide is inflated. The performance test system of the aircraft ejector is specially used for carrying out performance test on the development of the aircraft ejector, can carry out test without using a slide material object, and is simple and convenient to use and accurate in test.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a system and a method for testing performance of an aircraft ejector.
Background
The ejector is a device which utilizes one high-speed high-energy flow (liquid flow, air flow or other material flow) to eject the other low-speed low-energy flow, and the jet flows into a mixing chamber through a convergent nozzle, and the periphery of the mixing chamber is ejected flow. The energy is transferred to the injected flow by the injection flow through the mixing action of the boundary. The mixing area formed by mixing is gradually enlarged to fill the whole mixing chamber, and then a section of mixing process is carried out until the outlet of the mixing chamber, and the flow is almost uniform.
The aircraft ejector is a key part of the escape slide of the passenger aircraft, and when the inflatable slide needs to be opened, the aircraft ejector utilizes high-pressure gas in the gas cylinder to eject ambient air into the slide to inflate the slide.
At present, the key technology of the escape slide is monopolized abroad. The development of the aircraft ejector is blank in China, and the performance of the aircraft ejector needs to be tested by special testing equipment when the aircraft ejector is developed, so that the testing equipment of the aircraft ejector does not exist in China correspondingly.
Disclosure of Invention
The invention provides a performance test system and a performance test method for an aircraft ejector, and aims to solve the problem that no test equipment for the aircraft ejector exists in the prior art.
In order to solve the technical problems, the technical scheme of the invention is as follows:
the performance test system for the aircraft ejector comprises a test cabin, an air bottle and a slide simulator, wherein the aircraft ejector is arranged in the test cabin, and the air bottle is connected with the aircraft ejector through an air inlet pipeline;
the rear end of the test chamber is provided with an air inlet, the front end of the test chamber is provided with an air inlet chamber, the front end of the air inlet chamber is provided with an air outlet, the rear end of the air inlet chamber is tightly connected with the test chamber, the rear end of the air inlet chamber is provided with an opening,
the aircraft ejector main body is arranged in the test cabin, the nozzle of the aircraft ejector is inserted into the opening and arranged in the air inlet cabin, and the slide simulator is positioned at the air outlet;
the slide simulator is used for simulating the change of internal backpressure when the slide is inflated.
Optionally: the slide simulator comprises a back pressure adjusting cone, a cone head of the back pressure adjusting cone is opposite to the air outlet, the back pressure adjusting cone is connected with a controller, and the controller controls the back pressure adjusting cone to move back and forth in the air outlet so as to simulate the change of back pressure inside the slide when the slide is inflated.
Optionally: the air inlet detection device is characterized by further comprising a detection unit, wherein the detection unit comprises a flow meter arranged on the air inlet pipeline, a first differential pressure sensor arranged at the air inlet, a second differential pressure sensor arranged in the air inlet cabin and a pressure sensor arranged at the air outlet.
Optionally: a plurality of flow nozzles are arranged at the air inlet.
Optionally: the gas cylinder gas pressure regulating device is characterized in that a control valve assembly and a monitoring assembly are further arranged on the gas inlet pipeline, the control valve assembly comprises a hand valve and a pressure regulating valve, the hand valve is arranged at the outlet of the gas cylinder, and the monitoring assembly comprises a pressure gauge.
According to another aspect of the invention, there is also provided a method of testing the performance of an aircraft ejector, the method comprising the steps of:
step 1, testing backpressure curves of slides of various models and synchronizing the backpressure curves into a controller;
and 5, recording the gas cylinder inflation flow recorded by the flow meter, the gas inlet flow at the flow nozzle and the pressure difference in the gas inlet cabin.
Adopt above-mentioned technical scheme, owing to drive the quick travel of back pressure regulation awl through the controller, change the flow resistance in the pipeline, realize the quick change of backpressure to the backpressure curve of real slide is simulated in reality, does not use the performance that real slide tested the aircraft ejector, and convenience simple to use tests accurately.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft ejector performance testing system according to the present invention;
in the figure, 1 is a test chamber, 2 is an air inlet chamber, 3 is an air inlet chamber opening, 4 is an aircraft ejector, 5 is an air bottle, 6 is a counter pressure adjusting cone, 7 is a controller, 8 is a flow nozzle, 9 is a rectifying grid, 10 is a first differential pressure sensor, 11 is a second differential pressure sensor, 12 is a second pressure sensor, 13 is a second temperature sensor, 14 is a first temperature sensor, 15 is a first pressure sensor, 16 is a hand valve, 17 is a flow meter, 18 is a first electromagnetic stop valve, 19 is a pressure regulating valve, 20 is a second electromagnetic stop valve, 21 is a weighing sensor, 22 is a third pressure sensor and 23 is a pressure gauge.
Detailed Description
The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
A kind of aircraft ejector performance test system, the performance test used in the development of the aircraft ejector, fig. 1 is the structure schematic diagram of the aircraft ejector performance test system of the invention, including test chamber 1, gas cylinder 5 and slide simulator, the aircraft ejector 4 is set up in test chamber 1, the gas cylinder 5 connects the aircraft ejector 4 through the air inlet pipeline;
the rear end of the test chamber 1 is provided with an air inlet, the front end of the test chamber 1 is provided with an air inlet chamber 2, the front end of the air inlet chamber 2 is provided with an air outlet, the rear end of the air inlet chamber 2 is tightly connected with the test chamber 1, and the rear end of the air inlet chamber 2 is provided with an air inlet chamber opening 3;
the main body of the airplane ejector 4 is arranged in the test chamber 1, the nozzle of the airplane ejector 4 is inserted into the opening 3 of the air inlet chamber and is arranged in the air inlet chamber 2, and the slide simulator is positioned at the air outlet;
the slide simulator is used for simulating the change of internal back pressure when the slide is inflated.
Specifically, in the embodiment of the present invention, the slide simulator is of a structure in which: the slide simulator includes that the backpressure is adjusted awl 6, and the cone head of backpressure regulation awl 6 is just to the gas outlet, and backpressure regulation awl 6 is connected with controller 7, and controller 7 control backpressure is adjusted awl 6 and is changed the flow resistance in the gas outlet back-and-forth movement in the gas outlet, realizes the rapid change of backpressure to inside backpressure changes when the simulation slide is aerifyd.
In order to control the intake air amount of the intake port, a plurality of flow rate nozzles 8 are also provided. For illustration, in the embodiment of the present invention, three flow nozzles 8 are provided at the air inlet.
By opening different numbers of flow nozzles 8, control of the flow of inlet air in the test chamber 1 can be achieved.
Because the airflow entering the test chamber 1 through the flow nozzle 8 is uneven, in order to perfectly simulate the uniform and natural airflow state of the aircraft ejector 4 in use, the rectifier grid 9 is further arranged in the test chamber 1, the rectifier grid 9 is positioned between the air inlet and the aircraft ejector 4, the airflow can be adjusted through the rectifier grid 9, the airflow is uniform and stable, and the test result of the aircraft ejector 4 is not influenced.
The test system mainly detects the performance of the aircraft ejector 4, and in the embodiment of the invention, the performance is tested by checking the inlet flow, the outlet pressure difference and the outlet flow of the gas cylinder 5, so that in the embodiment of the invention, the test system further comprises a detection unit, wherein the detection unit comprises a flow meter 17 arranged on an inlet pipeline, a first pressure difference sensor 10 arranged at the inlet, a second pressure difference sensor 11 arranged in the inlet cabin 2 and a first pressure sensor 15 arranged at the outlet.
In a natural state, the temperature and the pressure of the surrounding environment also affect the performance of the aircraft ejector 4, so that a second pressure sensor 12 and a second temperature sensor 13 are further arranged at the air inlet, and a first temperature sensor 14 is further arranged at the air outlet.
In order to control the opening of the gas cylinder 5, in the embodiment of the invention, a hand valve 16 is arranged at the outlet of the gas cylinder 5, in addition, in order to facilitate the control during the test and to be capable of timely processing in case of accidents, in the embodiment of the invention, a first electromagnetic cut-off valve 18 and a second electromagnetic cut-off valve 20 are also arranged. A first electromagnetic shut-off valve 18 and a second electromagnetic shut-off valve 20 are provided on the intake line.
In order to adjust the gas output of the gas cylinder 5, a pressure adjusting valve 19 is also arranged on the gas inlet pipeline.
In addition, in the embodiment of the present invention, a load cell 21 is further installed at the bottom of the gas cylinder 5 to obtain the remaining gas capacity in the gas cylinder 5 by detecting the weight of the gas cylinder 5.
The intake line is also provided with a monitoring assembly, for example, in an embodiment of the present invention, the monitoring assembly includes a pressure gauge 23 and a third pressure sensor 22.
According to another aspect of the invention, there is provided a method of testing the performance of an aircraft ejector 4, the method comprising the steps of:
step 1, testing back pressure curves of slides of various models and synchronizing the back pressure curves into a controller 7;
and 5, recording the flow rate of the gas cylinder 5 during charging, the air inlet flow rate at the flow nozzle 8, the pressure difference in the gas inlet chamber 2 and the like recorded by the flow meter 17.
The following table shows the performance parameter indexes of the aircraft ejector of the invention:
wherein, the temperature is the ambient temperature during the test, namely the values measured by the first temperature sensor 14 and the second temperature sensor 13; the pressure 1 is a pressure value of the gas ejected by the aircraft ejector and measured by the first pressure sensor 15; pressure 2 is the pressure at the flow nozzle 8 measured by the second pressure sensor 12; the pressure difference is the pressure difference between the gas ejected by the aircraft ejector and the external environment measured by the second pressure difference sensor 11; the flow rate 1 is the pressure difference between the inside of the test chamber and the external environment obtained by the first differential pressure sensor 10; the flow rate 2 is a flow rate value of the gas cylinder obtained by the flow meter 17.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, and the scope of protection is still within the scope of the invention.
Claims (6)
1. The performance test system of the aircraft ejector is characterized in that: the test device comprises a test chamber, an air bottle and a slide simulator, wherein an aircraft ejector is arranged in the test chamber, and the air bottle is connected with the aircraft ejector through an air inlet pipeline;
the rear end of the test chamber is provided with an air inlet, the front end of the test chamber is provided with an air inlet chamber, the front end of the air inlet chamber is provided with an air outlet, the rear end of the air inlet chamber is tightly connected with the test chamber, the rear end of the air inlet chamber is provided with an opening,
the aircraft ejector main body is arranged in the test cabin, the nozzle of the aircraft ejector is inserted into the opening and arranged in the air inlet cabin, and the slide simulator is positioned at the air outlet;
the slide simulator is used for simulating the change of internal backpressure when the slide is inflated.
2. The aircraft ejector performance testing system of claim 1, wherein: the slide simulator comprises a back pressure adjusting cone, a cone head of the back pressure adjusting cone is opposite to the air outlet, the back pressure adjusting cone is connected with a controller, and the controller controls the back pressure adjusting cone to move back and forth in the air outlet so as to simulate the change of back pressure inside the slide when the slide is inflated.
3. The aircraft ejector performance testing system of claim 2, wherein: the air inlet detection device is characterized by further comprising a detection unit, wherein the detection unit comprises a flow meter arranged on the air inlet pipeline, a first differential pressure sensor arranged at the air inlet, a second differential pressure sensor arranged in the air inlet cabin and a pressure sensor arranged at the air outlet.
4. The aircraft ejector performance testing system of claim 3, wherein: a plurality of flow nozzles are arranged at the air inlet.
5. The aircraft ejector performance testing system of claim 4, wherein: the gas cylinder gas pressure regulating device is characterized in that a control valve assembly and a monitoring assembly are further arranged on the gas inlet pipeline, the control valve assembly comprises a hand valve and a pressure regulating valve, the hand valve is arranged at the outlet of the gas cylinder, and the monitoring assembly comprises a pressure gauge.
6. An aircraft ejector performance testing method applied to the testing system of claims 1-5, characterized by comprising the following steps:
step 1, testing backpressure curves of slides of various models and synchronizing the backpressure curves into a controller;
step 2, opening at least one flow nozzle;
step 3, opening a hand valve;
step 4, the controller moves the back-pressure regulating cone back and forth according to the back-pressure curve to change the flow resistance at the air outlet so as to realize the simulation of the back-pressure curve;
and 5, recording the gas cylinder inflation flow recorded by the flow meter, the gas inlet flow at the flow nozzle and the pressure difference in the gas inlet cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010670080.7A CN111929043A (en) | 2020-07-13 | 2020-07-13 | Performance test system and method for aircraft ejector |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010670080.7A CN111929043A (en) | 2020-07-13 | 2020-07-13 | Performance test system and method for aircraft ejector |
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| Publication Number | Publication Date |
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| CN111929043A true CN111929043A (en) | 2020-11-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010670080.7A Pending CN111929043A (en) | 2020-07-13 | 2020-07-13 | Performance test system and method for aircraft ejector |
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| CN1675501A (en) * | 2002-08-09 | 2005-09-28 | 杰富意钢铁株式会社 | Tubular flame burner and method for controlling combustion |
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Application publication date: 20201113 |
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