CN114295772B - Flight fireproof test system and method thereof - Google Patents
Flight fireproof test system and method thereof Download PDFInfo
- Publication number
- CN114295772B CN114295772B CN202111651983.1A CN202111651983A CN114295772B CN 114295772 B CN114295772 B CN 114295772B CN 202111651983 A CN202111651983 A CN 202111651983A CN 114295772 B CN114295772 B CN 114295772B
- Authority
- CN
- China
- Prior art keywords
- pressure
- negative pressure
- vibration
- environment
- tested
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention relates to the field of fireproof testing of an aircraft ignition part, in particular to a flight fireproof testing system and a method thereof, wherein the system comprises an environment simulation module, a control module, a target to be tested and a recording module; and recording the combustion test result of the target to be tested in the negative pressure and vibration environment in the fireproof test process. The invention can improve the reality of the fireproof test environment and the negative pressure of the airplane during actual flight, and improve the flight safety of the airplane.
Description
Technical Field
The invention relates to the field of fire prevention testing of aircraft fire parts, in particular to a flight fire prevention testing system and a flight fire prevention testing method.
Background
An aircraft is an aircraft that has one or more engine-powered devices to produce forward thrust or pull and lift from the fixed wings of the fuselage, flying in the atmosphere heavier than air. Aircraft usually fly with passengers or materials, and the flying safety of the aircraft is related to personal safety and property safety of the aircraft, so that the fire resistance performance and other index tests of the aircraft are very important. In the flight process of an airplane, certain air pressure is required to be maintained in the cabin of the airplane to ensure that passengers breathe normally, so that the fire resistance and other index tests of all parts of the airplane are generally carried out under the atmospheric pressure condition.
However, when an aircraft fires during flight, a small portion of the sealing elements and structural members are in a negative pressure environment, and the fireproof performance obtained by testing in the negative pressure environment is different from that obtained by testing in an atmospheric pressure condition, so that the fireproof performance test results of the sealing elements and structural members are inaccurate.
Disclosure of Invention
The invention aims to provide a flight fireproof test system which aims to solve the problem that the fireproof performance test results of the existing test method on part of sealing elements and structural parts are inaccurate.
The flight fireproof test system in the scheme comprises an environment simulation module, a control module, a target to be tested and a recording module;
the control module sends a test signal to the environment simulation module during testing, and the environment simulation module is used for receiving the test signal of the control module to form a negative pressure and vibration environment for a target to be tested to perform fireproof test;
the control module generates a regulating signal for regulating the negative pressure and the negative pressure of the vibration environment according to a preset strategy, wherein the preset strategy is that the negative pressure is increased to the set pressure in a first time period, the set pressure is kept for a second time period, the negative pressure is firstly decreased according to a preset gradient and then is randomly changed, and the environment simulation module forms the negative pressure and the vibration environment according to the regulating signal;
the recording module is used for recording the test result of the target to be tested in the combustion process under the negative pressure and vibration environment.
The beneficial effect of this scheme is:
the environment simulation module forms negative pressure and vibration environment according to the test signals, a target to be tested is located in the negative pressure and vibration environment to conduct fireproof test, for example, a sealing piece, a structural piece and the like which are located in the negative pressure and vibration environment on an aircraft are used as the target to be tested, meanwhile, in the combustion test process, the control module controls the environment simulation module to regulate the negative pressure of the negative pressure and the negative pressure of the vibration environment according to a preset strategy, the test results are recorded, part of components of the aircraft are subjected to fireproof test of the negative pressure and the vibration environment of different negative pressures in advance, the negative pressure and the vibration environment are pressurized to the set pressure and then are stabilized for a period of time, so that the air pressure of the environment where the target to be tested is located on the aircraft is achieved, and then the air pressure of the environment is randomly changed after being reduced according to a preset gradient, so that the air pressure change condition when the aircraft is abnormal is formed.
Further, the control module obtains the test result of the recording module to identify the change characteristics of the target to be tested, compares the identified change characteristics with preset characteristics, and sends a change signal to the environment simulation module when the change characteristics are the same as the preset characteristics, wherein the environment simulation module enables the negative pressure to change randomly according to the change signal.
The beneficial effects are that: and identifying the change characteristics of the target to be tested in the test result, such as deformation or cracking of the target to be tested, controlling the environment simulation module to enable the negative pressure to change randomly, and enabling the change of the air pressure to act on the combustion test to obtain the influence of air pressure abnormality caused by the change environment after the target to be tested changes in the combustion process, such as the change of the negative pressure environment caused by the abnormality of an airplane, so as to obtain the accurate fireproof performance of the target to be tested.
Further, the control module continuously transmits a vibration signal to the environmental simulation module in a third time period when the fire protection test is started, and the environmental simulation module receives the vibration signal of the control module and applies vibration of a first intensity to a target to be tested which burns under negative pressure and vibration environment.
The beneficial effects are that: the target to be tested is continuously vibrated in a third duration after the fire protection test starts, vibration brought in the engine operation process can be applied to the target to be tested, accuracy of a simulated flight environment can be improved, combustion test of the target to be tested is conducted under negative pressure and vibration environment and under shaking conditions, and accuracy of a fire protection test result is improved.
Further, the control module sends an intermittent vibration signal to the environment simulation module after sending the change signal, and the environment simulation module applies vibration of a second intensity to the target to be tested according to the intermittent vibration signal, wherein the second intensity is larger than the first intensity.
The beneficial effects are that: after the combustion of the target to be tested changes, the target to be tested randomly vibrates, so that the target to be tested can be in a larger intermittent vibration environment generated by the influence of air flow, whether the protection performance of the target to be tested in the later stage of combustion is influenced by vibration or not is tested, and the reality and the integrity of the simulated environment are improved.
The flight fire prevention testing method comprises the following steps:
placing a target to be tested in a negative pressure and vibration environment for fireproof test, generating a regulating signal for regulating the negative pressure intensity of the negative pressure and the negative pressure intensity of the vibration environment according to a preset strategy, and changing the negative pressure intensity and the negative pressure intensity in the environment according to the preset strategy, wherein the preset strategy is that the negative pressure intensity is increased to a set pressure intensity in a first time period, the set pressure intensity is maintained for a second time period, and finally the negative pressure intensity is decreased according to a preset gradient and then is changed randomly;
and recording the combustion test result of the target to be tested in the negative pressure and vibration environment in the fireproof test process.
The beneficial effect of this scheme is:
the target to be tested is subjected to fireproof test under the negative pressure and vibration environment, for example, the sealing element, the structural element and the like on the aircraft are tested, the negative pressure intensity of the negative pressure and the vibration environment is regulated, the negative pressure intensity is boosted to the set pressure intensity and then is kept for a period of time, the negative pressure intensity of the negative pressure and the vibration environment reaches the pressure state of the aircraft in the actual flight state, finally, the negative pressure intensity is reduced according to the preset gradient and then is changed, the negative pressure and the vibration environment can be close to the condition of air pressure change when the aircraft is abnormal, the negative pressure and the vibration environment can be more in line with the actual negative pressure and vibration environment on the aircraft during flight, and the accuracy of the fireproof test result of the target to be tested is improved.
Compared with the existing testing method, the method has the advantages that the target to be tested is in the combustion test under the same environment as the aircraft, the combustion test is conducted on few parts of the aircraft, the fireproof performance of the target to be tested can be analyzed according to the test result of the combustion test, and the accuracy of the fireproof performance test of the target to be tested under the specific environment is improved. The method is characterized in that combustion tests are carried out on part of components on an aircraft under negative pressure and vibration environments, so that the method is not generally carried out by those skilled in the art, because most of areas on the aircraft are in normal pressure state to adapt to human body requirements, only a few part of areas on the aircraft can be under the negative pressure and vibration environments, the fireproof performance of the few part of areas is out of consideration, and the fireproof performance changes of sealing elements and structural elements in the few part of areas can influence the safety of the aircraft; in addition, even if some people notice the sealing elements and structural members of the partial area, no system capable of performing the negative pressure fireproof test is available, no method is available for performing the actual test, and even further, even if the fireproof test under the specified negative pressure is completed by piecing up various devices, the fire environment in the actual flight state cannot be simulated truly, erroneous test data are obtained, and no guiding significance is available for judging the fireproof performance in the actual flight state, so that the scheme can greatly restore the negative pressure environment on the aircraft for performing the test.
Further, the change characteristics in the test result are identified, the change characteristics are compared with preset characteristics, and when the change characteristics are the same as the preset characteristics, the negative pressure intensity is changed randomly.
The beneficial effects are that: judging whether the characteristic is preset according to the real-time recorded and recognized change characteristic of the target to be tested, such as deformation or cracking of the target to be tested, if so, enabling the negative pressure intensity to change randomly, changing the negative pressure and vibration environment at the later stage of the fireproof test of the target to be tested, and improving the integrity of the fireproof test of the target to be tested.
Further, at the start of the fire test, a vibration stimulus is applied to the target to be tested during the fire test for a third period of time, the vibration stimulus applying vibration to the target to be tested at a first intensity.
The beneficial effects are that: and vibration excitation is applied to the target to be tested in the test process, so that the negative pressure and vibration environment of the fireproof test of the target to be tested are more real, and the accuracy of the fireproof test result is improved.
Further, the set pressure is-15 KPa to 0KPa, when the first time is over, real-time pressure of the preset quantity in the negative pressure and vibration environment is collected in real time, the collected real-time pressure is sequentially subjected to difference, the air pressure variation is calculated, the adjusted predicted pressure is predicted according to the air pressure variation and the real-time pressure at the current time, and the adjustment quantity is corrected in real time according to the predicted pressure.
The beneficial effects are that: in a time period for keeping the negative pressure constant, the regulated air pressure environment is predicted through the air pressure variation of the real-time pressure, the real-time pressure and the regulating variable of the negative pressure, the regulating variable is corrected in real time, the regulating variable of the pressure is regulated in advance by the regulating variable, the regulating variable is corrected in advance before the air pressure is about to be located outside the range of the set pressure, the regulation is avoided after the real-time pressure is located outside the range of the set pressure, the stability of the regulated pressure is kept, the combustion environment under the condition of firing in the flight process of an airplane is simulated truly, and the measured fireproof performance is more truly and reliable.
Drawings
FIG. 1 is a schematic block diagram of a flight fire protection test system in accordance with a first embodiment of the invention;
fig. 2 is a flow chart of a method for testing fire protection in flight according to a second embodiment of the invention.
Detailed Description
Further details are provided below with reference to the specific embodiments.
Example 1
A flight fire protection test system, as shown in fig. 1: the system comprises an environment simulation module, a control module, a target to be tested and a recording module, wherein the environment simulation module comprises a negative pressure unit and a vibration unit, the negative pressure unit can use an existing air pump, the vibration unit can use an existing VSK-ZF-ZN vibrator, the control module is controlled to be connected with the environment simulation module, the control module can use an existing SOC chip, the target to be tested comprises a sealing element and a structural member, and the recording module can select an existing infrared thermal imager according to actual requirements.
The control module sends a test signal to the environment simulation module during testing, the control module can send the test signal during power-on, the environment simulation module is used for receiving the test signal of the control module to form negative pressure and vibration environment for the target to be tested to carry out fireproof test, namely, the negative pressure unit in the environment simulation module is started to pump away air, meanwhile, the vibration unit in the environment simulation module is started to apply vibration excitation of first intensity to the target to be tested, the first intensity sets the vibration intensity value applied to corresponding parts during operation of an engine on an aircraft, when vibration is applied, the platform for placing the target to be tested is applied, the target to be tested can be mounted on any side wall of the cube-shaped test box through screws and the like according to the mounting mode on the aircraft, namely, the backfire surface equivalent to the target to be tested is located in the test box, the windward surface of the test target is located outside the test box, the environment simulation module is enabled to form the negative pressure and vibration environment, the capacity of the test box is set according to actual requirements, and the test box is made of metal, such as stainless steel.
The control module generates a regulating signal for regulating the negative pressure and the negative pressure of the vibration environment according to a preset strategy, the preset strategy is that the negative pressure is increased to a set pressure in a first time period, the first time period can be set according to actual test conditions, for example, the first time period is set to six minutes, the set pressure can be set to-15 KPa to 0KPa, the set pressure is kept in a second time period, namely, the negative pressure is kept in a range of-15 KPa to 0KPa, the second time period is set according to test requirements, for example, ten minutes, the negative pressure is finally allowed to be reduced according to a preset gradient and then randomly changed, the preset gradient can be 2KPa, for example, the preset strategy can be prestored in the control module, and the environment simulation module forms the negative pressure and the vibration environment according to the regulating signal, namely, the negative pressure unit of the environment simulation module is used for exhausting air to form the negative pressure and the vibration environment.
The recording module is used for recording the test result of the target to be tested in the combustion process under the negative pressure and vibration environment, recording the image of the target to be tested in the combustion process to be used as the test result, and the control module acquires the test result and recognizes the test information such as the flame state, the flame spreading range, the flame temperature and the like of the target to be tested in the combustion process through the existing algorithm.
The control module obtains a test result of the recording module to identify the change characteristic of the target to be tested, compares the identified change characteristic with a preset characteristic, obtains a test contour of the target to be tested through an existing contour extraction algorithm, compares the test contour with an initial contour of the target to be tested before the combustion test is not carried out, judges whether the test contour is identical to the initial contour of the target to be tested, sends a change signal to the environment simulation module when the change characteristic is identical to the preset characteristic, enables the negative pressure to change randomly according to the change signal, the number of times of random change of the negative pressure can be set to three, the random change of the negative pressure is in an increasing and decreasing sequence, and the increasing and decreasing amounts are not fixed, for example, the negative pressure is increased from-2 KPa to-1 KPa, then decreased to-8 KPa and finally increased to-5 KPa. The control module sends an intermittent vibration signal to the environment simulation module after sending the change signal, and the environment simulation module applies vibration with second intensity to the target to be tested according to the intermittent vibration signal, wherein the second intensity is larger than the first intensity.
The control module continuously sends a vibration signal to the environment simulation module in a third time period when the fireproof test is started, namely the vibration unit in the environment simulation module always generates vibration, the third time period is set according to the combustion process of the target to be tested, for example, the third time period can be set to be five minutes, the environment simulation module receives the vibration signal of the control module and vibrates the target to be tested which is combusted under the negative pressure and vibration environment, namely the control module controls the vibration unit to drive the target to be tested to vibrate. The first time length, the second time length and the third time length are obtained and calculated from an internal clock by the control module.
The control module obtains the preset number of real-time pressures at the end of the first time period and sequentially calculates the pressure variation, the control module obtains the sampling frequency of the real-time pressures as 10 times/min, namely the preset number of values of the 10 real-time pressures, the control module sums the differences obtained by the differences and then averages the differences to obtain the pressure variation, for example, the obtained pressure variation is-0.4 KPa, the control module obtains the adjustment quantity of the environmental simulation module for negative pressure and vibration environmental air flow, for example, the adjustment quantity is the pump air flow quantity and the opening of an air inlet, the control module predicts and calculates the adjusted predicted pressure according to the pressure variation quantity and the real-time pressure at the current time, for example, the real-time pressure at the current time is-7.3 KPa, the control module predicts the real-time pressure at the current time and the pressure variation, the control module compares the predicted pressures with the set pressures, namely, the control module judges whether each predicted pressure is positioned in the set pressure range, when the predicted pressures are not coincident with the set pressures, namely, the predicted pressures are not all positioned in the set pressure range, the control module compares the predicted pressures with the lower limit value and the upper limit value of the set pressures respectively, when the predicted pressures are smaller than the lower limit value of the set pressures, namely, part of the predicted pressures are smaller than the lower limit value of the set pressures, namely, the control module sends an adjusting signal for reducing the adjusting quantity to the environment simulation module, i.e. decreasing the opening of the air inlet, and when the predicted pressure is greater than the upper limit value of the set pressure, i.e. when part of the predicted pressure is greater than the upper limit value of the set pressure, 0KPa, the control module sends an adjusting signal for increasing the adjusting amount to the environment simulation module, i.e. increasing the opening of the air inlet, the increasing amount and the decreasing amount of the adjusting amount are fixed, for example, the adjusting amount is 1/4 of the opening amount, and the increasing or decreasing of the adjusting amount can be performed by adjusting the opening of the air inlet of the air pump. Thereby achieving the aim of keeping the negative pressure and the vibration environment stable.
Since most of the area on the aircraft is set to be in a normal pressure environment according to the respiratory requirement of the human body, but a very small part of the area is still in a negative pressure environment, safety tests on components of the aircraft are generally carried out in the normal pressure environment, and because the number of the components in the negative pressure and vibration environments is small, the cost of separately carrying out the tests is high, no special equipment is used for the tests, and the component in the negative pressure environment is also in a negative pressure environment on one side wall and in a normal pressure environment on the other side wall. Because the components needing to be subjected to fireproof verification deform or crack under the action of flame, and the like, a large amount of air enters the negative pressure simulation environment of the system, so that negative pressure changes suddenly and is unstable, and the components are always in a constant negative pressure environment no matter whether the components catch fire or are damaged in the flying process of the aircraft, the system of the embodiment provides a fireproof performance test on the sealing element and the structural element of the aircraft under the negative pressure and vibration environment, and the fireproof performance test is performed on the object to be tested under the negative pressure and vibration environment through the simulation of the negative pressure and the vibration environment on the sealing element and the structural element of the aircraft, so that the object to be tested can be tested under the negative pressure and vibration environment of the real aircraft flying, and the accuracy of the test result is improved. Even if the test of a small part of the components is supposed to be performed under the negative pressure and vibration environment, the negative pressure and vibration environment similar to that of the aircraft cannot be accurately simulated by the prior art, and an accurate test result cannot be obtained.
Example two
As shown in fig. 2, the present embodiment provides a flight fire protection testing method, which is applied to the flight fire protection testing system in the first embodiment, and includes the following contents:
the method comprises the steps of placing a target to be tested in a negative pressure and vibration environment for fireproof test, igniting the target to be tested for combustion test after the target to be tested is placed in the negative pressure and vibration environment, generating negative pressure intensity for adjusting the negative pressure and the vibration environment according to a preset strategy, wherein the preset strategy is that the negative pressure intensity is increased to a set pressure intensity in a first time period, the set pressure intensity is kept for a second time period, the negative pressure intensity is decreased according to a preset gradient and then is changed randomly after the second time period, and the first time period and the second time period are set according to parameter values in the embodiment.
The test results of the burning of the object to be tested in the fire protection test under negative pressure and vibration conditions are recorded, for example by taking images with temperature, for example infrared imaging.
The method in the first embodiment is used for identifying the change feature in the test result, the change feature is identified by acquiring the test contour of the target to be tested through the existing contour extraction algorithm, the change feature is compared with the preset feature, the preset feature can be an initial contour before the target to be tested is tested, the feature information of the contour can be extracted through the existing SIFT algorithm, SURF algorithm and the like when the test contour is matched with the initial contour, namely, the feature points on the contour are extracted and the feature information is calculated, the robustMatch is matched through the robust matching algorithm according to the feature information, and when the change feature is identical with the preset feature, the negative pressure is changed randomly.
When the fire protection test is started, vibration excitation of a third duration is applied to the target to be tested in the fire protection test process, vibration is applied to the target to be tested by the vibration excitation with the first intensity, setting of the third duration is performed according to the first embodiment, the vibration excitation is set according to the obtained vibration information, and the vibration information comprises vibration amplitude and vibration frequency. And when the change characteristics are the same as the preset characteristics, intermittently applying vibration with a second intensity to the target to be detected, wherein the second intensity is larger than the first intensity.
Setting the pressure to be-15 KPa to 0KPa, collecting the preset number of real-time pressures in the negative pressure and vibration environment in real time at the end of the first time, collecting the sampling frequency of the real-time pressures to be 10 times/min, namely, the preset number of the numerical values of the 10 real-time pressures, sequentially differencing the collected real-time pressures and calculating the air pressure variation, averaging the differences obtained by the differencing to obtain the air pressure variation, for example, the obtained air pressure variation is-0.4 KPa, obtaining the regulating variable of the regulation of the negative pressure and the vibration environment pressure, predicting the regulated predicted pressure according to the air pressure variation and the real-time pressure at the current moment, for example, -12.3KPa, adding the real-time pressure at the current moment and the air pressure variation according to the preset number of times, sequentially obtaining the predicted pressure of the preset number, for example, the obtained predicted pressures are-12.7 KPa, -13.1KPa, -13.5KPa, -13.9KPa, -14.3KPa, -14.7KPa, -15.1KPa, -15.5KPa, -15.9KPa, -16.3KPa, the predicted pressures are compared with the set pressures, namely, whether each predicted pressure is located in a set pressure range is judged, when the predicted pressures are not coincident with the set pressures, the predicted pressures are respectively compared with a lower limit value and an upper limit value of the set pressures, when the predicted pressures are smaller than the lower limit value of the set pressures, an adjusting signal for reducing the adjusting quantity, namely, the opening degree of the air inlet is reduced, when the predicted pressures are larger than the upper limit value of the set pressures, an adjusting signal for increasing the adjusting quantity, namely, the opening degree of the air inlet is increased, the increasing quantity and the reducing quantity are fixed, for example, the adjusting quantity is 1/4 opening quantity, namely, the adjusting quantity is corrected according to the predicted pressures in real time.
According to the method, negative pressure and vibration environments of the sealing element and the structural element on the aircraft are simulated, negative pressure intensity in the negative pressure and vibration environments is regulated, in the pressure stabilizing process, the regulated predicted pressure intensity is calculated, whether the predicted pressure intensity is in the range of the set pressure intensity is judged, if not, the regulation is carried out in advance, the authenticity of the simulated negative pressure and vibration environments and the negative pressure and vibration environments on the aircraft is improved, and the accuracy of the fireproof test result of the target to be tested is improved.
The foregoing is merely exemplary embodiments of the present invention, and specific structures and features that are well known in the art are not described in detail herein. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the structure of the present invention, and these should also be considered as the scope of the present invention, which does not affect the effect of the implementation of the present invention and the utility of the patent. The protection scope of the present application shall be subject to the content of the claims, and the description of the specific embodiments and the like in the specification can be used for explaining the content of the claims.
Claims (7)
1. A flight fire protection test system, characterized by: the environment simulation system comprises an environment simulation module, a control module, a target to be tested and a recording module, wherein the target to be tested comprises a sealing element and a structural member;
the control module sends a test signal to the environment simulation module during testing, and the environment simulation module is used for receiving the test signal of the control module to form a negative pressure and vibration environment for a target to be tested to perform fireproof test;
the control module generates a regulating signal for regulating the negative pressure and the negative pressure of the vibration environment according to a preset strategy, wherein the preset strategy is that the negative pressure is increased to the set pressure in a first time period, the set pressure is kept for a second time period, the negative pressure is firstly decreased according to a preset gradient and then is randomly changed, and the environment simulation module forms the negative pressure and the vibration environment according to the regulating signal;
the control module obtains the regulating quantity of the environment simulation module aiming at negative pressure and vibration environment airflow, the control module predicts and calculates the regulated expected pressure according to the air pressure changing quantity and the real-time pressure at the current moment, the control module compares the expected pressure with the set pressure, when the expected pressure is not overlapped with the set pressure, the control module respectively compares the lower limit value and the upper limit value of the expected pressure with the set pressure, when the expected pressure is smaller than the lower limit value of the set pressure, the control module sends a regulating signal for reducing the regulating quantity to the environment simulation module, and when the expected pressure is larger than the upper limit value of the set pressure, the control module sends a regulating signal for increasing the regulating quantity to the environment simulation module;
the recording module is used for recording the test result of the target to be tested in the combustion process under the negative pressure and vibration environment.
2. The flying fire test system according to claim 1, wherein: the control module obtains the test result of the recording module to identify the change characteristics of the target to be tested, compares the identified change characteristics with preset characteristics, and sends a change signal to the environment simulation module when the change characteristics are the same as the preset characteristics, wherein the environment simulation module enables the negative pressure to change randomly according to the change signal.
3. The flying fire test system according to claim 2, wherein: the control module continuously transmits a vibration signal to the environment simulation module in a third duration when the fireproof test is started, and the environment simulation module receives the vibration signal of the control module and applies vibration of a first intensity to a target to be tested which burns under negative pressure and vibration environment.
4. A flight fire protection test system as claimed in claim 3, wherein: the control module sends an intermittent vibration signal to the environment simulation module after sending the change signal, and the environment simulation module applies vibration of a second intensity to the target to be tested according to the intermittent vibration signal.
5. The flight fireproof testing method is characterized by comprising the following steps of:
placing a target to be tested in a negative pressure and vibration environment for fireproof test, wherein the target to be tested comprises a sealing element and a structural member, generating a regulating signal for regulating the negative pressure of the negative pressure and the vibration environment according to a preset strategy, and enabling the negative pressure and the negative pressure in the environment to change according to the preset strategy, wherein the preset strategy is that the negative pressure is increased to a set pressure in a first time period, the set pressure is kept for a second time period, and finally the negative pressure is decreased according to a preset gradient and then randomly changed;
the set pressure is-15 KPa to 0KPa, when the first time is over, real-time pressure of the preset quantity in the negative pressure and vibration environment is collected in real time, the collected real-time pressure is subjected to difference in sequence, the air pressure variation is calculated, the adjusted predicted pressure is predicted according to the air pressure variation and the real-time pressure at the current moment, and the adjustment quantity is corrected in real time according to the predicted pressure;
comparing the predicted pressure with the set pressure, respectively comparing the lower limit value and the upper limit value of the predicted pressure with the set pressure when the predicted pressure is not coincident with the set pressure, and transmitting an adjusting signal for reducing the adjusting quantity when the predicted pressure is smaller than the lower limit value of the set pressure and transmitting an adjusting signal for increasing the adjusting quantity when the predicted pressure is larger than the upper limit value of the set pressure;
and recording the combustion test result of the target to be tested in the negative pressure and vibration environment in the fireproof test process.
6. The flying fire test method according to claim 5, wherein: and identifying the change characteristics in the test result, comparing the change characteristics with preset characteristics, and when the change characteristics are the same as the preset characteristics, enabling the negative pressure to change randomly.
7. The flying fire test method according to claim 5, wherein: and when the fireproof test is started, applying vibration excitation to the target to be tested in the fireproof test process in a third time period, wherein the vibration excitation applies vibration to the target to be tested with a first intensity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111651983.1A CN114295772B (en) | 2021-12-30 | 2021-12-30 | Flight fireproof test system and method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111651983.1A CN114295772B (en) | 2021-12-30 | 2021-12-30 | Flight fireproof test system and method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114295772A CN114295772A (en) | 2022-04-08 |
| CN114295772B true CN114295772B (en) | 2023-08-04 |
Family
ID=80973243
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111651983.1A Active CN114295772B (en) | 2021-12-30 | 2021-12-30 | Flight fireproof test system and method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114295772B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104963724A (en) * | 2015-06-25 | 2015-10-07 | 苏州市英富美欣科技有限公司 | Goaf fireproof monitoring system |
| CN107144663A (en) * | 2017-03-23 | 2017-09-08 | 北京科技大学 | A kind of temperature-controllable tests the method and system of metal material burning behavior |
| CN109506968A (en) * | 2018-11-26 | 2019-03-22 | 天地（常州）自动化股份有限公司 | Underground coal mine beam tube negative pressure ventilation back-fire relief test device and test method |
| CN109580869A (en) * | 2018-12-25 | 2019-04-05 | 中国航空综合技术研究所 | The fire protecting performance test method and its test device of civil aircraft component and its attachment |
| CN210803181U (en) * | 2019-10-29 | 2020-06-19 | 中国民用航空总局第二研究所 | Aircraft warehouse test device |
| CN111650245A (en) * | 2020-07-10 | 2020-09-11 | 天津大学 | System and method for testing flameless combustion spontaneous combustion temperature of combustible gas in high-pressure environment |
| CN113295432A (en) * | 2021-05-20 | 2021-08-24 | 永安行科技股份有限公司 | Hydrogen fuel electric bicycle working condition testing system and method |
| CN215178654U (en) * | 2021-02-04 | 2021-12-14 | 东莞市中诺质检仪器设备有限公司 | Fire prevention and fire resistance testing machine for airborne equipment of airplane |
-
2021
- 2021-12-30 CN CN202111651983.1A patent/CN114295772B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104963724A (en) * | 2015-06-25 | 2015-10-07 | 苏州市英富美欣科技有限公司 | Goaf fireproof monitoring system |
| CN107144663A (en) * | 2017-03-23 | 2017-09-08 | 北京科技大学 | A kind of temperature-controllable tests the method and system of metal material burning behavior |
| CN109506968A (en) * | 2018-11-26 | 2019-03-22 | 天地（常州）自动化股份有限公司 | Underground coal mine beam tube negative pressure ventilation back-fire relief test device and test method |
| CN109580869A (en) * | 2018-12-25 | 2019-04-05 | 中国航空综合技术研究所 | The fire protecting performance test method and its test device of civil aircraft component and its attachment |
| CN210803181U (en) * | 2019-10-29 | 2020-06-19 | 中国民用航空总局第二研究所 | Aircraft warehouse test device |
| CN111650245A (en) * | 2020-07-10 | 2020-09-11 | 天津大学 | System and method for testing flameless combustion spontaneous combustion temperature of combustible gas in high-pressure environment |
| CN215178654U (en) * | 2021-02-04 | 2021-12-14 | 东莞市中诺质检仪器设备有限公司 | Fire prevention and fire resistance testing machine for airborne equipment of airplane |
| CN113295432A (en) * | 2021-05-20 | 2021-08-24 | 永安行科技股份有限公司 | Hydrogen fuel electric bicycle working condition testing system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114295772A (en) | 2022-04-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104345118B (en) | Solid propellant many targets line Dynamic Burning Performance Test System and method | |
| US9989253B2 (en) | Combustion instability control method | |
| JP2001174366A (en) | Method and device for diagnosing model base | |
| CN114295772B (en) | Flight fireproof test system and method thereof | |
| CN103323624A (en) | Method and device for verifying the consistency of the measurements of the angle-of-attack probe of an aircraft | |
| Engelund et al. | Propulsion system airframe integration issues and aerodynamic database development for the Hyper-X flight research vehicle | |
| CN108318238A (en) | A kind of fatigue test system of engine blade | |
| CN101707925B (en) | Method of controlling the combustion of a diesel engine | |
| CN103729508B (en) | A kind of fuel injector selection method and device | |
| RU2660214C1 (en) | Method for testing a gas turbine engine | |
| US9915210B2 (en) | Method and apparatus for controlling an engine based on a target pressure curve | |
| Meli et al. | Proof of Concept for Hardware-in-the-Loop Based Knock Detection Calibration | |
| CN114326845B (en) | Negative pressure regulating system and method | |
| CN110765637B (en) | Layer cloud and cloud environment simulation method | |
| Vargas et al. | Ice Particles Impacting on a Flat Plate: Temperature and Velocity Effect | |
| CN106290701A (en) | A kind of metal fuel efficiency of combustion method of testing | |
| US20220220904A1 (en) | Method for controlling a gas turbine | |
| RU2809401C1 (en) | Method for conducting flight tests to obtain loudness of sonic boom on ground, taking into account effect of vertical overload of aircraft | |
| RU2766927C1 (en) | Method for simulating icing at the research object | |
| JP6732705B2 (en) | Environmental test equipment and environmental test method | |
| CN110542563A (en) | Engine ground test POGO excitation method | |
| RU2211934C1 (en) | Method for recording fuel ingnition in afterburner of gas turbine engine | |
| CN110100085B (en) | Method for maximizing engine torque | |
| US20220195958A1 (en) | Method for determining a quantity of fuel injected into an internal combustion engine | |
| RU862679C (en) | Method of testing controlled nozzle of aircraft gas-turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |