Method for detecting explosion cutting pulse noise of aircraft life raft based on simulation platform
By building seat, canopy, and human model on a simulation platform, a scenario of aircraft ejection rescue explosion and cutting is simulated, which solves the problem of inaccurate impulse noise detection in existing technologies and provides accurate test data and safety evaluation support.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AIR FORCE MEDICAL CENT PLA
- Filing Date
- 2023-09-25
- Publication Date
- 2026-06-26
AI Technical Summary
Existing technology cannot accurately detect the pulse noise during the ejection escape explosion, resulting in inaccurate detection results and failing to meet the safety protection needs of pilots.
A simulation platform-based approach was adopted, using seat models, hatch models, and mannequin models to build a simulation platform. Various characteristic parameters were adjusted to simulate the detection scenario during explosive cutting, and impulse noise tests were conducted, recording the distance between the test points and the explosion center and the test data.
It enables precise detection of the cutting pulse noise from aircraft lifesaving explosions, providing accurate test data to support the evaluation of aircraft design and safety protection.
Smart Images
Figure CN117213620B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft ejection rescue explosion cutting pulse noise detection technology, specifically to an aircraft ejection rescue explosion cutting pulse noise detection method based on a simulation platform. Background Technology
[0002] Aircraft ejection escape explosive cutting uses shaped charge explosive cutting technology. By detonating pyrotechnics (mainly detonating cord, cutting cord, micro-explosive cord, etc.) pre-embedded in the canopy, a high-speed metal jet is generated to pre-crack or cut the canopy and then ejected to clear the ejection channel. It is one of the important methods for clearing ejection escape channels in modern aircraft. It has the advantages of short ejection delay, minimal damage, prevention of canopy detachment in flight, and canopy stealth. However, it is necessary to solve the problems of collateral damage caused by shell fragmentation and blast shock wave and pulse noise.
[0003] Currently, based on the safety limits of pulse noise during conventional weapon launch or explosion as defined in GJB 2A-1996, and combined with engineering practice of explosive cutting to clear ejection channels, protection against pulse noise and shock waves from aircraft ejection rescue explosions is achieved by determining the safety limits of pilot injury from the explosion impact during ejection and estimating the overpressure of the explosion impact. However, the damage to humans from explosion shock waves and pulse noise overpressure is not only related to the overpressure but also closely related to the posture, position, and other scene characteristics of the human body in the detection scenario. Accurate detection of explosion impact pulse noise requires consideration of the scene characteristics at the time of the explosion. Due to the numerous parameters and rapid changes in the pulse noise from aircraft ejection rescue explosions, aerial detection is difficult and carries extremely high safety risks. Existing ground-based experimental tests are mostly theoretical experiments based on the explosive yield and distance, without fully simulating the explosion scenario. The aircraft ejection rescue explosion cutting pulse noise detection scenario is a special moment before the pilot ejects, which is related to the intricate design of the aircraft and ejection seat. If the scene during the cutting explosion is not considered, then the experimental simulation test cannot achieve accuracy. Summary of the Invention
[0004] This invention provides a simulation platform-based method for detecting aircraft rescue explosion cutting pulse noise, which can simulate aircraft rescue explosion cutting pulse noise detection scenarios and conduct corresponding tests to obtain accurate and effective test data.
[0005] Therefore, the present invention provides the following technical solution:
[0006] A method for detecting aircraft lifesaving explosion cutting pulse noise based on a simulation platform, wherein the simulation platform includes: a seat model, a canopy model, and a mannequin model; the method includes:
[0007] Arrange the components of the simulation platform and adjust the various characteristic parameters to match the parameters of the detection scenario when pyrotechnics explode;
[0008] Record the adjustment parameters and corresponding data of the simulation platform;
[0009] According to the requirements for pulse noise detection, set up detection points, measure and record the distance between the explosion center and the detection point;
[0010] Explosive cutting pulse noise test was conducted to obtain test data.
[0011] The layout simulation platform includes various components, and adjusting various characteristic parameters to match the parameters of the detection scenario during a pyrotechnic explosion, including:
[0012] Install the seat model, canopy model, and mannequin model in sequence, and make adjustments so that the installed structure can selectively simulate the position and state of the pilot when triggering ejection;
[0013] Place and mark the layout of the pyrotechnics on the hatch model, and determine the locations of the pyrotechnic detonation points.
[0014] Optionally, the sequential installation of the seat model, canopy model, and mannequin model includes: installing the seat model and the canopy model onto the simulation platform, and fixing the mannequin model onto the seat model.
[0015] Optionally, the ability of the installed structure to mimic the position and state of a pilot triggering ejection includes:
[0016] The state of the seat model and the simulated human model is made consistent with the state of the cockpit at the moment of the aircraft pyrotechnic explosion.
[0017] The height and tilt angle of the canopy model are made to match the height and tilt angle of the aircraft cockpit.
[0018] Optionally, the hatch model is made from disposable materials.
[0019] Optionally, the adjustment parameters of the simulation platform include any one or more of the following: initial reference position, seat height, head height, seat back chamfer angle, seat adjustment angle, hatch height, distance between the center of the blast point and the blast test point, and explosive mass.
[0020] Optionally, the pyrotechnic device is equipped with an explosion-propellant switch;
[0021] The explosive cutting pulse noise test was conducted, and the test data obtained included:
[0022] Place the shock wave pressure testing system at the test point;
[0023] The detonation switch is remotely controlled to detonate the pyrotechnic device.
[0024] The explosive cutting pulse noise test was conducted using the aforementioned shock wave pressure testing system to obtain test data.
[0025] Optionally, the shock wave pressure testing system includes any one or more of the following devices: a sound level meter, a sensor, a signal amplifier, a dynamic signal testing and analysis device, and a microcomputer with data processing software installed.
[0026] Optionally, the method further includes: calculating various hearing impairment evaluation results and / or protection evaluation results for the test items based on the test data and recorded data.
[0027] Optionally, the seat is a 1:1 simulation model of an aircraft ejection seat, and the canopy is a 1:1 simulation model of an aircraft canopy.
[0028] This invention provides a simulation platform-based method for detecting aircraft lifesaving explosion cutting pulse noise. The simulation platform is constructed using seat models, canopy models, and mannequin models. The various components of the simulation platform are arranged, and the characteristic parameters are adjusted to match the parameters of a detection scenario during a pyrotechnic explosion. After adjusting the characteristic parameters, the adjusted parameters and corresponding data of the simulation platform are recorded. Detection points are set according to the pulse noise detection requirements, and the distance between the explosion center and the measurement points is measured and recorded. An explosion cutting pulse noise test is then conducted to obtain test data. Using this invention, a realistic aircraft lifesaving explosion cutting pulse noise scenario can be accurately and effectively simulated, thereby obtaining precise test data.
[0029] Furthermore, based on the test data, the recorded simulation platform, and other static data, various hearing impairment evaluation results and protection evaluation results of the test items can be calculated, providing data support for product design and evaluation. Attached Figure Description
[0030] Figure 1 This is a schematic diagram of the simulation platform used for detecting the explosion-cutting pulse noise of aircraft lifesaving in an embodiment of the present invention;
[0031] Figure 2 This is a flowchart of the aircraft lifesaving explosion cutting pulse noise detection method based on a simulation platform provided in an embodiment of the present invention;
[0032] Figure 3 This is a schematic diagram of helmet-mounted noise testing using a simulation platform;
[0033] Figure 4 This is a schematic diagram of using a simulation platform to conduct an external overpressure test on a helmet;
[0034] Figure 5 This is a schematic diagram of the test results obtained by using the present invention and existing technology to conduct helmet internal noise test and helmet external overpressure test. Detailed Implementation
[0035] To enable those skilled in the art to better understand the embodiments of the present invention, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings and implementation methods.
[0036] In aircraft ejection rescue explosion cutting, the blast shock wave and pulse noise overpressure can cause injury to personnel. Therefore, accurate detection of the blast shock pulse noise is necessary to ensure the safety of onboard personnel. However, existing ground-based experimental detection methods do not consider the cutting explosion scenario, resulting in inaccurate simulation results and the inability to provide effective data. To address this issue, this invention provides a simulation platform-based method for detecting aircraft ejection rescue explosion cutting pulse noise. A simulation platform is constructed using seat models, canopy models, and mannequin models. The various components of the simulation platform are arranged, and the characteristic parameters are adjusted to match the parameters of the detection scenario during a pyrotechnic explosion. After adjusting the characteristic parameters, the adjusted parameters and corresponding data of the simulation platform are recorded. Detection points are set according to the pulse noise detection requirements, and the distance between the explosion center and the measurement point is measured and recorded. Explosion cutting pulse noise tests are conducted to obtain test data. Using this invention, the real aircraft ejection rescue explosion cutting pulse noise scenario can be accurately and effectively simulated, thereby obtaining accurate test data.
[0037] like Figure 1 The diagram shown is a schematic representation of the simulation platform used for detecting the explosion-cutting pulse noise of an aircraft in an embodiment of the present invention.
[0038] The simulation platform includes: seat model 11, canopy model 12, and humanoid model 13.
[0039] It should be noted that, in specific applications, the seat model 11 can be a 1:1 simulation model of an aircraft ejection seat, and can be adjusted forward and backward, and tilted upward. Similarly, the canopy model 12 can also be a 1:1 simulation model of an aircraft canopy, and the material, size, and structure of the canopy model 12 can be the same as those of the aircraft cockpit. In addition, the simulated person 13 can specifically be a dummy or an artificial head, and this embodiment of the invention does not limit this.
[0040] In addition, the hatch model 12 can be made from disposable materials, and multiple spares can be made at once according to the number of experimental measurements.
[0041] Using this simulation platform, the flowchart of the aircraft lifesaving explosion cutting pulse noise detection method provided in this embodiment of the invention is as follows: Figure 2 As shown, it includes the following steps:
[0042] Step 201: Arrange the components of the simulation platform and adjust the various characteristic parameters to match the parameters of the detection scenario when the pyrotechnic device explodes.
[0043] Specifically, refer to Figure 1 As shown, the process of laying out the components of the simulation platform is as follows:
[0044] First, install the seat model 11, canopy model 12, and mannequin model 13 in sequence, referring to... Figure 1 As shown, the seat model 11 and the canopy model 12 are installed on the simulation platform, and the humanoid model 13 is fixed to the seat model 11.
[0045] After the above items are installed, the components are adjusted according to the pilot's position and state when triggering ejection, so that the installed structure can mimic the pilot's position and state when triggering ejection.
[0046] For example, retrieve the static parameters of the aircraft seat and the spatial parameters of the seat at the moment of the pyrotechnic explosion, and adjust the posture of the seat model 11 according to these parameters so that the state of the seat model and the simulated human model 13 is consistent with the state of the cabin at the moment of the pyrotechnic explosion; adjust the height of the canopy model 12 so that the height and tilt angle of the canopy model 12 are consistent with the height and tilt angle of the aircraft cabin.
[0047] Furthermore, such as Figure 1 As shown, to facilitate adjustment of the posture of the seat model 11, the seat model 11 can be fixed on the base 21, and the base 21 is designed as an adjustable structure. In this way, when it is necessary to adjust the posture of the seat model 11, only the position and tilt angle of the base 21 need to be adjusted.
[0048] Furthermore, such as Figure 1 As shown, to facilitate the adjustment of the height of the hatch model 12, the hatch model 12 can be mounted on the support member 22, which is designed as a height-adjustable structure. Accordingly, the height of the hatch model 12 can be easily adjusted simply by adjusting the height of the support member 22.
[0049] Of course, other adjustments can be made based on the actual state of the aircraft cabin in a real-world aircraft rescue explosion cutting scenario, and these will not be illustrated in detail in this embodiment of the invention.
[0050] Secondly, after the layout and adjustment of each component of the simulation platform are completed, the layout of the pyrotechnics is placed and marked on the hatch model, and the location of the pyrotechnic detonation point is determined.
[0051] It should be noted that, in order to obtain better simulation results, the layout, equivalent quantity, and number of pyrotechnic devices should be the same as those in the aircraft cockpit.
[0052] Step 202: Record the adjustment parameters and corresponding data of the simulation platform.
[0053] The adjustment parameters of the simulation platform include, but are not limited to, any one or more of the following: initial reference position, seat height, head position height, seat back chamfer angle, seat adjustment angle, hatch height, distance between the center of the blast point and the blast test point, and explosive mass. The definition and function of each parameter can be found in Table 1 below.
[0054] Table 1
[0055]
[0056] Step 203: According to the requirements of impulse noise detection, set the detection points, measure and record the distance between the test points and the explosion center (i.e., the distance from the test point to the explosion center, also known as the explosion distance).
[0057] Step 204: Perform an explosive cutting pulse noise test to obtain test data.
[0058] In practical applications, in order to facilitate the detonation of pyrotechnics and ensure the safety of test personnel, a detonation switch can be installed on the pyrotechnics. By triggering the detonation switch, the pyrotechnics can be detonated to simulate an aircraft life-saving explosion scenario.
[0059] The detonation switch can be remotely controlled, which allows test personnel to maintain a safe distance from the simulation platform.
[0060] In one non-limiting embodiment, an existing shock wave pressure testing system can be used to perform explosive cutting pulse noise testing. The shock wave pressure testing system may include, but is not limited to, any one or more of the following devices: sound level meter, sensor, signal amplifier, dynamic signal testing and analysis equipment, microcomputer with data processing software installed, etc.
[0061] Accordingly, the explosive cutting pulse noise test, and the test data obtained, can be performed according to the following process:
[0062] (1) Place the shock wave pressure testing system at the test point;
[0063] (2) Remotely control the detonation switch to detonate the pyrotechnic device;
[0064] (3) The explosive cutting pulse noise test was performed using the shock wave pressure test system to obtain test data.
[0065] It should be noted that, depending on the actual test data required, the above test process can be repeated multiple times to measure different parameter data, and this embodiment of the invention does not limit this.
[0066] Furthermore, in a non-limiting embodiment, the method may further include the following steps: calculating various hearing impairment evaluation results and / or protection evaluation results for the tested items based on the test data and recorded data. For example, using the simulation platform to conduct helmet-in-helmet noise testing and helmet-out-of-helmet overpressure testing, and determining hearing impairment evaluation results and protection evaluation results based on the test data.
[0067] Figure 3 This is a schematic diagram of helmet-mounted noise testing using a simulation platform. Figure 4 This is a schematic diagram of using a simulation platform to conduct an external overpressure test on a helmet.
[0068] An example of the above simulation test is as follows:
[0069] The platform was adjusted to reflect the characteristic parameters of the cabin scene during a pyrotechnic explosion, and experimental testing was conducted in accordance with the scene simulation design process.
[0070] For example, the testing instrument uses a sound artificial head and a DA-21 data logger to collect noise data, and AS-70 waveform processing software and Cool Edit Pro 2.0 pulse width analysis software to perform data statistical analysis.
[0071] An artificial head is fitted with a flight helmet, and detectors are placed inside and outside the helmet at the ear positions of the artificial head to test noise exposure and sound pressure at the ear positions.
[0072] Simultaneously, comparative tests were conducted using commonly used ground-based experiments, and the results of the two tests were obtained. Figure 5 The test curve is shown.
[0073] The experimental data were processed and calculated to obtain... Figure 5 The test curve is shown.
[0074] Curve 51 is the helmet noise curve obtained by commonly used ground test, and curve 52 is the helmet noise curve obtained by testing using the scheme of the present invention.
[0075] Among them, dashed line 60 represents the helmet noise obtained after helmet sound pressure conversion in two tests; dashed line 61 represents the helmet noise obtained using a common overpressure calculation formula; and dashed line 62 represents the helmet noise calculated by incorporating the characteristic parameters of the detection scene. Dashed line 62 is slightly lower than dashed line 61, indicating that after considering scene parameters, the theoretically calculated maximum peak overpressure is smaller than that without them, which is consistent with the actual measurement.
[0076] Depend on Figure 5As can be seen from the curves, the pulse peak of curve 52 lags behind that of curve 51, and its subsequent attenuation is also faster and lower. This indicates that the simulation's measurements considering the cabin environment are consistent with the shock wave pulse noise protection requirements of the aircraft design, and the simulation of this invention closely approximates the actual situation in the aircraft cabin. The helmet external sound pressure levels of curves 51 and 52 are the same, indicating that the testing standards are consistent.
[0077] In addition, the dashed line 62 is slightly lower than the dashed line 61, indicating that after considering the scenario parameters, the theoretically calculated maximum peak overpressure is smaller than that without them, which is consistent with the actual measurement.
[0078] Depend on Figure 5 The experimental data shows that the pulse peak value is slightly delayed after adjusting the detection scenario using the method of this invention, and the subsequent attenuation is faster and lower. This indicates that the aircraft design takes into account the effects of explosion shock waves and pulse noise, and the cabin scenario helps to resist shock noise damage. In addition, the comparison also shows that the helmet external sound pressure obtained by the two different methods is the same, indicating that the detection standards are consistent.
[0079] pass Figure 5 The test results mainly reflect the following points:
[0080] 1) The simulation test using the scheme of this invention shows that the peak value of the noise curve is delayed;
[0081] 2) The simulation test using the scheme of this invention shows that the secondary peak decays quickly;
[0082] 3) The simulation detection using the scheme of this invention results in low secondary peak values;
[0083] 4) The aircraft cockpit design, seat ejection design, and ejection channel design have all taken into account the effects of the blast shock wave and pulse noise during ejection. Therefore, the design of its seats, canopy, ejection angle, etc. is reasonable and in line with the actual situation.
[0084] 5) Existing ground simulation methods do not consider the cabin conditions, only the explosive yield and the distance to the test point. Therefore, their measurement curves will definitely be higher than the actual values of aircraft ejection. The reason it is higher rather than lower is because it does not simulate seat tilt, and the distance to the test point is smaller than that considering tilt, which is equivalent to being closer to the ear, thus resulting in a higher peak value.
[0085] 6) The present invention takes into account the spatiotemporal characteristics of the cabin during the explosion, which is closer to the state of the aircraft, cockpit, seat, ejection, and pilot ejection. Therefore, the curve peak lag, fast curve decay, and low curve detected by the present invention indicate that the accuracy is better than other simple simulation detection, and it is also consistent with the design of aircraft cockpit, seat, canopy, ejection, etc.
[0086] 7) Since the simulation results for both helmets are consistent, it indicates that the testing standards are the same. This further proves that, under the condition of consistent testing standards, the testing results of the present invention are closer to the actual situation, thus also corroborating the theoretical analysis in point 5) above.
[0087] As can be seen, the aircraft lifesaving explosion cutting pulse noise detection method based on a simulation platform provided by this invention utilizes a simulation platform constructed from seat models, canopy models, and mannequin models. The various components of the simulation platform are arranged, and the characteristic parameters are adjusted to match the parameters of the detection scenario during a pyrotechnic explosion. After adjusting the characteristic parameters, the adjusted parameters and corresponding data of the simulation platform are recorded. Detection points are set according to the pulse noise detection requirements, and the distance between the explosion center and the detection point is measured and recorded. An explosion cutting pulse noise test is conducted to obtain test data. Using this invention, the real aircraft lifesaving explosion cutting pulse noise scenario can be accurately and effectively simulated, thereby obtaining precise test data.
[0088] Furthermore, based on the test data, the recorded simulation platform, and other static data, various hearing impairment evaluation results and protection evaluation results of the test items can be calculated, providing data support for product design and evaluation.
[0089] This invention closely integrates the simulation of aircraft lifesaving explosion cutting pulse noise detection with actual scenarios. The designed simulation platform is reusable, the experimental testing scenarios are unified, and the calculation and evaluation methods are consistent, which can obtain accurate test results. It can be used for research on aircraft explosion cutting pulse noise detection, and improve the platform support for noise protection design of aircraft explosion cutting ejection lifesaving.
[0090] It should be noted that the terms "comprising" and "having" and any variations thereof in the specification, claims and accompanying drawings of this invention are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are explicitly listed, but may include other steps or units that are not explicitly listed or that are inherent to such processes, methods, products or devices.
[0091] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to interchangeably. Each embodiment focuses on its differences from other embodiments. Furthermore, the system embodiments described above are merely illustrative. The modules and units described as separate components may or may not be physically separate; that is, they may be located on a single network unit or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.
[0092] The embodiments of the present invention have been described in detail above. Specific implementation methods have been used to illustrate the present invention. The descriptions of the embodiments above are only for the purpose of helping to understand the methods and systems of the present invention, and are merely some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention, and the content of this specification should not be construed as a limitation of the present invention. Therefore, any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.
Claims
1. A method for detecting aircraft lifesaving explosion cutting pulse noise based on a simulation platform, characterized in that, The simulation platform includes: a seat model, a canopy model, and a humanoid model; the method includes: Arrange the components of the simulation platform and adjust the various characteristic parameters to match the parameters of the detection scenario when pyrotechnics explode; Record the adjustment parameters and corresponding data of the simulation platform; According to the requirements for pulse noise detection, set up detection points, measure and record the distance between the explosion center and the detection point; Explosive cutting pulse noise test was conducted to obtain test data; The layout simulation platform includes various components, and adjusting various characteristic parameters to match the parameters of the detection scenario during a pyrotechnic explosion. Install the seat model, canopy model, and mannequin model in sequence, and make adjustments so that the installed structure can mimic the position and state of the pilot when triggering ejection; Place and mark the layout of the pyrotechnics on the hatch model, and determine the locations of the pyrotechnic detonation points; The pyrotechnic device is equipped with an explosion-activated switch. The explosive cutting pulse noise test was conducted, and the test data obtained included: Place the shock wave pressure testing system at the test point; The detonation switch is remotely controlled to detonate the pyrotechnic device. The explosive cutting pulse noise test was performed using the aforementioned shock wave pressure testing system to obtain test data. The structure, once installed, is designed to mimic the position and state of a pilot triggering an ejection, including: The state of the seat model and the simulated human model is made consistent with the state of the cockpit at the moment of the aircraft pyrotechnic explosion. The height and tilt angle of the canopy model are made to match the height and tilt angle of the aircraft cockpit. The sequential installation of the seat model, canopy model, and humanoid model includes: The seat model and the canopy model are installed on the simulation platform, and the humanoid model is fixed to the seat model. The hatch model is made from disposable materials; The adjustment parameters of the simulation platform include any one or more of the following: initial reference position, seat height, head position height, seat back chamfer angle, seat adjustment angle, canopy height, distance between the center of the blast point and the center of the blast point, distance between the blast measurement points, and explosive mass. The shock wave pressure testing system includes any one or more of the following devices: sound level meter, sensor, signal amplifier, dynamic signal testing and analysis equipment, and microcomputer with data processing software installed. The method further includes: Based on the test data and recorded data, various hearing impairment evaluation results and / or protection evaluation results for the tested items are calculated; The seat is a 1:1 simulation model of an aircraft ejection seat, and the canopy is a 1:1 simulation model of an aircraft canopy.