CN113806863A - Design method of fire protection system in aircraft power cabin - Google Patents
Design method of fire protection system in aircraft power cabin Download PDFInfo
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- 238000004088 simulation Methods 0.000 claims description 21
- 238000012795 verification Methods 0.000 claims description 19
- 239000000126 substance Substances 0.000 claims description 7
- 230000035945 sensitivity Effects 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 description 31
- 238000004364 calculation method Methods 0.000 description 6
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- RJCQBQGAPKAMLL-UHFFFAOYSA-N bromotrifluoromethane Chemical compound FC(F)(F)Br RJCQBQGAPKAMLL-UHFFFAOYSA-N 0.000 description 3
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C3/00—Fire prevention, containment or extinguishing specially adapted for particular objects or places
- A62C3/07—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles
- A62C3/08—Fire prevention, containment or extinguishing specially adapted for particular objects or places in vehicles, e.g. in road vehicles in aircraft
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C31/00—Delivery of fire-extinguishing material
- A62C31/02—Nozzles specially adapted for fire-extinguishing
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- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62C—FIRE-FIGHTING
- A62C37/00—Control of fire-fighting equipment
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
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Abstract
The application belongs to the technical field of design of a fire protection system in an aircraft power cabin, and particularly relates to a design method of a fire protection system in an aircraft power cabin, which comprises the following steps: analyzing a possible fire area of the aircraft power cabin based on a fire mechanism to determine an easy fire area; determining a fire detection area based on the easy fire area, designing the type and the arrangement of a fire detector in the fire detection area, and determining a scheme of a fire detection system in the power cabin of the airplane; determining a fire extinguishing protection area based on the easy fire area, designing the using amount of a fire extinguishing agent in the fire extinguishing protection area and the arrangement of fire extinguishing agent nozzles, and determining a scheme of a fire extinguishing system in the power cabin of the airplane; and if the scheme of the fire protection system in the airplane power cabin is verified to not meet the application requirements, the scheme of the fire protection system in the airplane power cabin is updated until the application requirements are met.
Description
Technical Field
The application belongs to the technical field of design of a fire protection system in an aircraft power cabin, and particularly relates to a design method of a fire protection system in an aircraft power cabin.
Background
The fire extinguishing system mainly comprises a fire extinguishing agent and a fire extinguishing agent nozzle, and when the fire extinguishing detector detects fire in the aircraft power cabin, the fire extinguishing agent is sprayed out from the fire extinguishing agent nozzle to extinguish fire in the aircraft power cabin.
Currently, the design of a fire protection system in an aircraft power compartment has the following defects:
1) in the fire alarm detection system, due to improper type selection and arrangement of a fire alarm detector in an aircraft power cabin, the situation that fire in the aircraft power cabin cannot be detected in time exists, the fire alarm detection system is not sensitive enough, and the application requirements cannot be met well;
2) the fire extinguishing system extinguishes fire in the aircraft power cabin, the fire extinguishing agent is insufficient, the fire extinguishing agent nozzles are not properly arranged, the concentration of the fire extinguishing agent and the duration of the fire extinguishing agent maintaining concentration cannot reach the fire extinguishing standard, the fire extinguishing in the aircraft power cabin is difficult to effectively achieve, and the application requirement cannot be well met.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method of designing a fire protection system within an aircraft power bay to overcome or alleviate at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
a method for designing a fire protection system in an aircraft power compartment comprises the following steps:
analyzing a possible fire area of the aircraft power cabin based on a fire mechanism to determine an easy fire area;
determining a fire detection area based on the easy fire area, designing the type and the arrangement of a fire detector in the fire detection area, and determining a scheme of a fire detection system in the power cabin of the airplane;
determining a fire extinguishing protection area based on the easy fire area, designing the using amount of a fire extinguishing agent in the fire extinguishing protection area and the arrangement of fire extinguishing agent nozzles, and determining a scheme of a fire extinguishing system in the power cabin of the airplane;
and if the scheme of the fire protection system in the airplane power cabin is verified to not meet the application requirements, the scheme of the fire protection system in the airplane power cabin is updated until the application requirements are met.
According to at least one embodiment of the application, in the method for designing a fire protection system in an aircraft power cabin, the amount of the fire extinguishing agent in the fire extinguishing protection area is designed, specifically:
if 0.8V > 0.32V +0.25Wa, then W is 0.8V;
otherwise, W is 0.32V +0.25 Wa;
wherein the content of the first and second substances,
v is the net capacity of the fire extinguishing protection area;
wa is the air flow of a fire extinguishing protection area under the cruising state of the airplane;
w is the dosage of the fire extinguishing agent in the fire extinguishing protection area.
According to at least one embodiment of the application, in the design method of the fire protection system in the aircraft power cabin, the simulation model of the scheme of the aircraft power cabin and the fire protection system thereof is constructed, and when the scheme of the fire protection system in the aircraft power cabin is subjected to simulation verification, half of the symmetrical structure of the simulation model is adopted for calculation.
According to at least one embodiment of the application, in the method for designing a fire protection system in an aircraft power cabin, the simulation verification of the scheme of the fire protection system in the aircraft power cabin is performed, and if the scheme of the fire protection system in the aircraft power cabin is verified to not meet the application requirement, the updating of the scheme of the fire protection system in the aircraft power cabin is performed until the application requirement is met, and the method includes:
simulating the fire in the easy fire area in the aircraft power cabin, verifying the sensitivity of a fire alarm detector in the scheme of the fire alarm detection system in the aircraft power cabin, and updating the scheme of the fire alarm detection system in the aircraft power cabin if the verification does not meet the application requirements until the application requirements are met.
According to at least one embodiment of the application, in the method for designing a fire protection system in an aircraft power cabin, the simulation verification of the scheme of the fire protection system in the aircraft power cabin is performed, and if the scheme of the fire protection system in the aircraft power cabin is verified to not meet the application requirement, the updating of the scheme of the fire protection system in the aircraft power cabin is performed until the application requirement is met, and the method includes:
simulating the fire catching of the easy fire catching area in the aircraft power cabin, verifying the concentration of the fire extinguishing agent sprayed by the fire extinguishing agent nozzle in the scheme of the fire extinguishing system in the aircraft power cabin and the duration time for maintaining the concentration, and updating the scheme of the fire extinguishing system in the aircraft power cabin if the verification does not meet the application requirement until the application requirement is met.
According to at least one embodiment of the present application, the method for designing a fire protection system in an aircraft power compartment further includes:
the design requirements of the fire protection system in the power cabin of the airplane are captured, the design requirements are combed, the performance, the function and the non-functional requirements of the fire protection system in the power cabin of the airplane are determined, the design requirements of the fire protection system in the power cabin of the airplane are formed, and the scheme design of the fire protection system in the power cabin of the airplane is restrained.
According to at least one embodiment of the present application, the method for designing a fire protection system in an aircraft power compartment further includes:
and constructing a functional logic model of a moving graph and a timing graph of the fire protection system in the aircraft power compartment to guide the scheme design of the fire protection system in the aircraft power compartment.
Drawings
FIG. 1 is a flow chart of a method for designing a fire protection system in a power compartment of an aircraft according to an embodiment of the present disclosure;
fig. 2 is a cloud diagram of the mass fraction distribution of the Halon 1301 fire extinguishing agent of the typical section in the aircraft power cabin, which is obtained by simulating the fire in the easy-fire area in the aircraft power cabin.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
A method for designing a fire protection system in an aircraft power compartment comprises the following steps:
analyzing a possible fire area of the aircraft power cabin based on a fire mechanism to determine an easy fire area;
determining a fire detection area based on the easy fire area, designing the type and the arrangement of a fire detector in the fire detection area, and determining a scheme of a fire detection system in the power cabin of the airplane;
determining a fire extinguishing protection area based on the easy fire area, designing the using amount of a fire extinguishing agent in the fire extinguishing protection area and the arrangement of fire extinguishing agent nozzles, and determining a scheme of a fire extinguishing system in the power cabin of the airplane;
and if the scheme of the fire protection system in the airplane power cabin is verified to not meet the application requirements, the scheme of the fire protection system in the airplane power cabin is updated until the application requirements are met.
For the method for designing the fire protection system in the aircraft power compartment disclosed in the above embodiment, it can be understood by those skilled in the art that the method is based on the fire mechanism to determine the easy-fire area in the aircraft power compartment, determine the fire detection area in the aircraft power compartment according to the easy-fire area, design the type and arrangement of the fire detectors based on the reality of the fire detection area, determine the scheme of the fire detection system in the aircraft power compartment, determine the fire area in the aircraft power compartment according to the easy-fire area, and design the dosage of the fire extinguishing agent and the arrangement of the fire extinguishing agent nozzles based on the reality of the fire area, so as to ensure the reasonability of the scheme of the fire protection system in the aircraft power compartment and ensure that the scheme of the fire protection system in the aircraft power compartment can meet the application requirements to a certain extent.
For the method for designing the fire protection system in the aircraft power cabin disclosed in the above embodiment, it can be further understood by those skilled in the art that a simulation model of the aircraft power cabin and the fire protection system scheme thereof is constructed, and based on the simulation verification, the fire protection system scheme in the aircraft power cabin is subjected to simulation verification, and when the fire protection system scheme in the aircraft power cabin is verified to be not capable of meeting the application requirement, the method can be used for improving the part which is not capable of meeting the application requirement in the fire protection system scheme in the aircraft power cabin, updating the fire protection system scheme in the aircraft power cabin, and performing simulation verification again until the application requirement can be met, so that the designed fire protection system scheme in the aircraft power cabin can be effectively ensured to well meet the application requirement.
With respect to the method for designing the fire protection system in the power compartment of the aircraft disclosed in the above embodiments, it can be understood by those skilled in the art that a fire must occur while including a combustible substance, an oxidant substance, and an ignition source, and this can be used as a fire mechanism to analyze a region where the power compartment of the aircraft may fire, and determine the region where the power compartment of the aircraft may fire while including the combustible substance, the oxidant substance, and the ignition source as an easy-fire region.
As to the method for designing a fire protection system in an aircraft power compartment disclosed in the above embodiments, it can be understood by those skilled in the art that, in the scheme of the fire detection system in the aircraft power compartment, the fire detector mainly detects an easily-fired region, and the range of the fire detection region can be determined to be approximately equivalent to a volatile fire region, so that the scheme of the fire detection system in the aircraft power compartment can detect the fire in the volatile fire region in time, and meet the application requirements.
In the method for designing the fire protection system in the aircraft power compartment disclosed in the above embodiment, it can be further understood by those skilled in the art that the scheme of the fire protection system in the aircraft power compartment mainly ensures that the fire-prone area can be effectively extinguished, the range of the fire protection area can be determined to be slightly larger than that of the fire-prone area, so that the scheme of the fire protection system in the aircraft power compartment can spray enough fire extinguishing agent when the fire-prone area is on fire, and the concentration of the fire extinguishing agent in the fire protection area and the time for maintaining the concentration of the fire extinguishing agent can meet the application requirements.
In some optional embodiments, in the method for designing a fire protection system in an aircraft power cabin, the amount of the fire extinguishing agent in the fire protection area is designed, specifically:
if 0.8V > 0.32V +0.25Wa, then W is 0.8V;
otherwise, W is 0.32V +0.25 Wa;
wherein the content of the first and second substances,
v is the net capacity of the fire extinguishing protection area;
wa is the air flow of a fire extinguishing protection area under the cruising state of the airplane;
w is the dosage of the fire extinguishing agent in the fire extinguishing protection area.
With respect to the method for designing the fire protection system in the power cabin of the aircraft disclosed in the above embodiments, it can be understood by those skilled in the art that the larger amount of 0.8V, 0.32V +0.25Wa is used as the amount of the fire extinguishing agent in the fire extinguishing protection area, and the size and the air circulation condition of the fire extinguishing protection area are comprehensively considered, so that the amount of the fire extinguishing agent can be ensured to meet the application requirement to a certain extent, and the fire extinguishing agent cannot be excessively excessive.
In some optional embodiments, in the above method for designing a fire protection system in an aircraft power pod, the simulation model of the aircraft power pod and the fire protection system scheme thereof is constructed, and when the fire protection system scheme in the aircraft power pod is subjected to simulation verification, half of the symmetric structure of the simulation model is used for calculation.
For the design method of the fire protection system in the aircraft power cabin disclosed in the above embodiment, as can be understood by those skilled in the art, the aircraft power cabin has a large volume, the whole and the fire protection system scheme thereof are subjected to simulation calculation, the calculation amount is huge, the efficiency is low, and when the aircraft power cabin is of a symmetrical structure, when the fire protection system scheme in the aircraft power cabin is subjected to simulation verification, half of the symmetrical structure of a simulation model is adopted for calculation, so that the calculation efficiency can be greatly improved, and the reliability of result analysis cannot be influenced.
In some optional embodiments, in the method for designing a fire protection system in an aircraft power pod, the simulating and verifying a scheme of the fire protection system in the aircraft power pod, and if it is verified that the scheme of the fire protection system in the aircraft power pod does not meet an application requirement, updating the scheme of the fire protection system in the aircraft power pod until the application requirement is met includes:
simulating the fire in the easy fire area in the aircraft power cabin, verifying the sensitivity of a fire alarm detector in the scheme of the fire alarm detection system in the aircraft power cabin, and updating the scheme of the fire alarm detection system in the aircraft power cabin if the verification does not meet the application requirements until the application requirements are met.
In some optional embodiments, in the method for designing a fire protection system in an aircraft power pod, the simulating and verifying a scheme of the fire protection system in the aircraft power pod, and if it is verified that the scheme of the fire protection system in the aircraft power pod does not meet an application requirement, updating the scheme of the fire protection system in the aircraft power pod until the application requirement is met includes:
the method includes the steps that simulation is conducted when an easily-fired area in the aircraft power cabin is fired, the fact that fire extinguishing agent nozzles spray fire extinguishing agents in the scheme of the fire extinguishing system in the aircraft power cabin is verified, the concentration in the fire extinguishing protection area and the duration of the concentration can be maintained is specifically achieved by adopting a Halon 1301 fire extinguishing agent, the judgment condition that the volume concentration can reach 6% in the fire extinguishing protection area and the volume concentration lasts for 0.5S is met, if the verification is that the application requirement is not met, the scheme of the fire extinguishing system in the aircraft power cabin is updated until the application requirement is met.
In a more specific embodiment, a fire of an easy fire area in an aircraft power cabin is simulated, and a mass fraction distribution cloud chart of a Halon 1301 fire extinguishing agent of a typical section in the aircraft power cabin is obtained and is shown in FIG. 2.
In some optional embodiments, in the method for designing a fire protection system in a power compartment of an aircraft, the method further includes:
the design requirements of the fire protection system in the power cabin of the airplane are captured, the design requirements are combed, the performance, the function and the non-functional requirements of the fire protection system in the power cabin of the airplane are determined, the design requirements of the fire protection system in the power cabin of the airplane are formed, the scheme design of the fire protection system in the power cabin of the airplane is restrained, and the scheme of the designed fire protection system in the power cabin of the airplane is made to be consistent with the design requirements.
In some optional embodiments, in the method for designing a fire protection system in a power compartment of an aircraft, the method further includes:
constructing a functional logic model of a moving graph and a timing graph of the fire protection system in the aircraft power compartment to guide the scheme design of the fire protection system in the aircraft power compartment, wherein,
the activity diagram is used for describing a workflow, a business process, or a process for decomposing and executing activities and sub-activities flowing to a system, and can be a simple linear sequence or a complex branched and parallel sequence with conditions, and is essentially a flow diagram which emphasizes the control flow from one activity to another, and intuitively means what the system needs to do step by step in order to complete a certain function;
the timing diagram presents interactions between participants and blocks, elaborates interactions and messaging between systems, emphasizes describing how objects interact, describes how messages are sent and received between objects, and consists of a vertical lifeline of participants and blocks, on which is an ordered set of messaging between these entities over a period of time.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (7)
1. A method for designing a fire protection system in an aircraft power compartment is characterized by comprising the following steps:
analyzing a possible fire area of the aircraft power cabin based on a fire mechanism to determine an easy fire area;
determining a fire detection area based on the easy fire area, designing the type and the arrangement of a fire detector in the fire detection area, and determining a scheme of a fire detection system in the power cabin of the airplane;
determining a fire extinguishing protection area based on the easy fire area, designing the using amount of a fire extinguishing agent in the fire extinguishing protection area and the arrangement of fire extinguishing agent nozzles, and determining a scheme of a fire extinguishing system in the power cabin of the airplane;
and if the scheme of the fire protection system in the airplane power cabin is verified to not meet the application requirements, the scheme of the fire protection system in the airplane power cabin is updated until the application requirements are met.
2. The method of designing a fire protection system for an aircraft power bay as claimed in claim 1,
the design is carried out the quantity of fire extinguishing agent in the protection area of putting out a fire, specifically does:
if 0.8V > 0.32V +0.25Wa, then W is 0.8V;
otherwise, W is 0.32V +0.25 Wa;
wherein the content of the first and second substances,
v is the net capacity of the fire extinguishing protection area;
wa is the air flow of a fire extinguishing protection area under the cruising state of the airplane;
w is the dosage of the fire extinguishing agent in the fire extinguishing protection area.
3. The method of designing a fire protection system for an aircraft power bay as claimed in claim 1,
the method comprises the steps of constructing a simulation model of the scheme of the aircraft power cabin and the fire protection system thereof, and calculating by adopting one half of the symmetrical structure of the simulation model when carrying out simulation verification on the scheme of the fire protection system in the aircraft power cabin.
4. The method of designing a fire protection system for an aircraft power bay as claimed in claim 1,
the simulation verification of the scheme of the fire protection system in the aircraft power cabin is carried out, if the verification shows that the scheme of the fire protection system in the aircraft power cabin does not meet the application requirements, the scheme of the fire protection system in the aircraft power cabin is updated until the application requirements are met, and the method comprises the following steps:
simulating the fire in the easy fire area in the aircraft power cabin, verifying the sensitivity of a fire alarm detector in the scheme of the fire alarm detection system in the aircraft power cabin, and updating the scheme of the fire alarm detection system in the aircraft power cabin if the verification does not meet the application requirements until the application requirements are met.
5. The method of designing a fire protection system for an aircraft power bay as claimed in claim 1,
the simulation verification of the scheme of the fire protection system in the aircraft power cabin is carried out, if the verification shows that the scheme of the fire protection system in the aircraft power cabin does not meet the application requirements, the scheme of the fire protection system in the aircraft power cabin is updated until the application requirements are met, and the method comprises the following steps:
simulating the fire catching of the easy fire catching area in the aircraft power cabin, verifying the concentration of the fire extinguishing agent sprayed by the fire extinguishing agent nozzle in the scheme of the fire extinguishing system in the aircraft power cabin and the duration time for maintaining the concentration, and updating the scheme of the fire extinguishing system in the aircraft power cabin if the verification does not meet the application requirement until the application requirement is met.
6. The method of designing a fire protection system for an aircraft power bay as claimed in claim 1,
further comprising:
the design requirements of the fire protection system in the power cabin of the airplane are captured, the design requirements are combed, the performance, the function and the non-functional requirements of the fire protection system in the power cabin of the airplane are determined, the design requirements of the fire protection system in the power cabin of the airplane are formed, and the scheme design of the fire protection system in the power cabin of the airplane is restrained.
7. The method of designing a fire protection system for an aircraft power bay as claimed in claim 1,
further comprising:
and constructing a functional logic model of a moving graph and a timing graph of the fire protection system in the aircraft power compartment to guide the scheme design of the fire protection system in the aircraft power compartment.
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