CN211653967U - Simulated rapid decompression chamber of civil aircraft - Google Patents
Simulated rapid decompression chamber of civil aircraft Download PDFInfo
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- CN211653967U CN211653967U CN202020466900.6U CN202020466900U CN211653967U CN 211653967 U CN211653967 U CN 211653967U CN 202020466900 U CN202020466900 U CN 202020466900U CN 211653967 U CN211653967 U CN 211653967U
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Abstract
The utility model relates to a rapid decompression chamber for civil aircraft simulation, which is characterized by comprising a simulation window, a variable adjusting device which is arranged on the simulation window in a matching way, and a negative pressure air extraction system which is arranged outside the chamber and is communicated with the simulation window; the variable adjusting device comprises a template matched with the simulation window and a locking piece used for detachably mounting the template on the simulation window; the negative pressure air exhaust system comprises a negative pressure tank, a negative pressure pipeline, an electric control gate valve and a negative pressure cover, the negative pressure tank is provided with a vacuum pump, one end of the negative pressure pipeline is connected with the negative pressure tank, the other end of the negative pressure pipeline is connected with the negative pressure cover, the negative pressure cover is arranged outside the simulation window, and the negative pressure pipeline is provided with the electric control gate valve. The utility model discloses a simulation aircraft is lost secret, the adjustable of decompression state process, steerable. And a simulation platform and equipment guarantee are provided for the adaptability training and emergency treatment drilling of aircraft drivers and crew members.
Description
Technical Field
The utility model relates to an aviation simulation trainer particularly, is a rapid decompression chamber of civil aviation ware simulation, belongs to aviation ware simulation trainer technical field.
Background
With the rapid development of the countries, various civil aircrafts are used more and more, and China becomes one of the countries with the largest number of civil aircrafts in the world. The situation that the safety of a driver and passengers is endangered due to extreme weather or airplane faults frequently occurs in the flying process of an airplane, and the flying safety of a civil aviation passenger plane becomes the most important subject of the civil aviation transportation industry.
[ case: in the cruising stage of 14 months and 5 months in 2018, when the Sichuan airline 3U8633 flight is in the urban area, the front windshield of the right seat of the cockpit is broken and falls off, and the unit is emergently descended. The pilot is sucked out of the aircraft by instant decompression, so fortunately, the pilot wears a safety belt, and under the conditions of decompression of a cockpit and failure of most instruments, the Liu biography health of a captain depends on an excessively hard flight technique and good psychological quality, and is correctly treated under the close cooperation of all safeguard units in civil aviation, and finally, the passenger can safely land on the ground. The bang Jiu as a retirement cadre of air force, who has been a flight instructor, can have a quality that is inseparable from the professional flight training and special treatment training that he receives during the service period of the army. "C (B)
The above cases fully illustrate the importance of improving the professional emergency handling capabilities of the occupants. However, due to a series of random factors of different flight heights, pressure environments and different emergency situations of the airplane during the flight process, various untreated dangerous situations often occur. China has various civil aviation universities and training institutions for aircraft drivers and crew members, and has various simulation training devices, but no professional device capable of simulating the rapid density loss and decompression state of an aircraft cabin in the high-altitude flight process of an aircraft exists at present, and research and development of the device are urgently needed to meet the requirements of training and scientific research of the aircraft drivers and crew members.
The loss of pressure of the cabin is mainly caused by loss of density, and the loss of density causes different coping strategies due to a series of related factors such as different loss of density degrees, different pressure environments, different flight heights and different loss of density positions. The simulation of various dangerous situations which may be met by an airplane in high altitude on the ground by a set of professional equipment and corresponding technical means is a necessary and effective guarantee means. How to simulate the rapid state of the cockpit and the cabin such as density loss and pressure loss through equipment and enable aircraft drivers and crew members to perform simulation training and emergency treatment rehearsal of various emergent dangerous conditions so as to research effective countermeasure measures is one of the main problems concerned by the civil aviation industry.
Disclosure of Invention
The utility model aims at providing a simulation cabin of similar aircraft structure, through technical means, the true simulation aircraft is at the high altitude flight in-process, dangerous situations such as secret losing and quick decompression take place in cockpit and the cabin, be used for pilot and crew member to carry out adaptability training, the research reply measure, improve reply handling capacity under the emergency, avoid the disaster to take place or furthest reduces casualties and loss of property, this has important meaning to the safety of ensureing and promoting civilian aviation aircraft.
The utility model adopts the technical proposal that:
the civil aircraft simulates a rapid decompression chamber, which is characterized in that,
the device comprises a simulation window communicated with the environment in the cabin, a variable adjusting device matched with the simulation window and a negative pressure air extraction system configured outside the cabin and communicated with the simulation window;
the variable adjusting device is detachably arranged on the simulation window and comprises a template matched with the simulation window and a locking piece used for detachably arranging the template on the simulation window;
the negative pressure air exhaust system comprises a negative pressure tank, a negative pressure pipeline, an electric control gate valve and a negative pressure cover, wherein the negative pressure tank is provided with a vacuum pump, one end of the negative pressure pipeline is connected with the negative pressure tank, the other end of the negative pressure pipeline is connected with the negative pressure cover, the negative pressure cover sealing cover is arranged outside the simulation window, and the negative pressure pipeline is provided with the electric control gate valve.
The simulation window can be set as a front view window of the cockpit, a cabin door of the cabin and/or a porthole of the cabin according to different positions.
The template is an experimental template made of different materials, and preferably an organic glass template.
The organic glass template is processed and customized according to simulation experiment requirements, and different cracks and cracked holes with different cracking forms, different sizes and different positions are prefabricated on different organic glass templates so as to simulate different in-cabin density losing states.
The specific matching structure of the template and the simulation window is as follows: and a positioning clamping groove is processed in advance on the window frame of the simulation window, and the template is arranged in the positioning clamping groove, so that the connection between the template and the simulation window is realized.
The locking part adopts a plurality of locking rotating handles arranged along the periphery of the simulation window, each locking rotating handle is provided with a rotating opening position and a rotating locking position, and at the rotating locking position, the locking part firmly locks the template on the window frame of the simulation window so as to realize the sealing connection of the template and the window frame; in the rotary opening position, the locking member releases the template, so that the template is easy to take down and replace.
The template is provided with a handle which is convenient to take and replace.
In order to simulate the functions of the airplane in various flight processes such as take-off, flat flight, landing, height control, rapid lifting, diving descending and the like, the civil aircraft is also provided with a large negative pressure air exhaust system and a positive pressure air supply system;
the large negative pressure air extraction system comprises a negative pressure tank with a vacuum pump, two sets of negative pressure pipelines and two electric control regulating valves arranged on the two sets of negative pressure pipelines, wherein one set of negative pressure pipeline and the electric control regulating valve are communicated between the cockpit and the negative pressure tank, and the other set of negative pressure pipeline and the electric control regulating valve are communicated between the cabin and the negative pressure tank;
the positive pressure air supply system comprises an air storage tank with an air compressor, two air supply pipelines and two electric control regulating valves arranged on the two air supply pipelines, wherein one air supply pipeline and one electric control regulating valve are communicated between the cockpit and the air storage tank, and the other air supply pipeline and the other electric control regulating valve are communicated between the cabin and the air storage tank.
The utility model discloses a civil aviation ware simulation rapid decompression chamber has consulted various aircraft structure and has designed, and the variable adjusting device of the state of losing secret of its configuration is a revolutionary innovative design, and the breakthrough application of this technique has realized simulation aircraft losing secret, the adjustable of decompression state process, steerable. The device can be matched with a large negative pressure air extraction system to truly simulate various density loss and pressure loss conditions which can occur in the high-altitude flight process of an airplane, meanwhile, the negative pressure air extraction system can be combined with a positive pressure air supply system to simulate various flight processes such as take-off, flat flight, landing, rapid pull-up, dive and the like of the airplane, realistically simulate various true states which can occur in the high-altitude flight process of the airplane, provide a simulation platform and equipment guarantee for adaptability training and emergency treatment rehearsal of airplane drivers and crew members, are mature equipment for relevant scientific experimental researches such as adaptability training and emergency treatment rehearsal of the airplane drivers and crew members, realize breakthrough and innovation of key technology, fill up the blank in China, and have important significance for development of civil aviation flight safety and aviation transportation industry.
Drawings
FIG. 1: a schematic diagram of a simulated rapid decompression chamber of a civil aircraft;
FIG. 2: FIG. 1 is a top view;
FIG. 3: a schematic structural diagram of a variable adjusting device for simulating a front window decryption state;
FIG. 4: the structure schematic diagram of the variable adjusting device;
FIG. 5: the prefabricated organic glass template shows the breaking state (a front window and a porthole);
FIG. 6: breaking state indication of prefabricated organic glass template (cabin door)
In the figure, 1, a cockpit, 2, a cabin, 3, a simulated front window, 4, a front window negative pressure hood, 5, a front window negative pressure pipeline, 6, a negative pressure tank, 7, a front window electric control gate valve, 8, a vacuum pump, 9, a front window variable adjusting device, 10, a simulated cabin door, 11, a cabin negative pressure hood, 12, a cabin negative pressure pipeline, 13, a cabin door electric control gate valve, 14, a cabin door variable adjusting device, 15, a simulated porthole, 16, a porthole variable adjusting device, 17, a porthole negative pressure hood, 18, a porthole negative pressure pipeline, 19, a porthole electric control gate valve, 20, a cockpit negative pressure pipeline, 21, a cockpit electric control adjusting valve, 22, a cabin negative pressure pipeline, 23, a cabin electric control adjusting valve, 24, an air storage tank, 25, an air compressor, 26, a cockpit air supply pipeline, 27, a cabin air supply pipeline, 28, a cockpit electric control adjusting valve, 29, an electric control cabin adjusting, 30. positioning clamping grooves 31, an organic glass template 32, a locking rotary handle 33 and a handle.
Detailed Description
The structural components, design principles and operation of the present invention are described in further detail with reference to the accompanying drawings, and it should be understood that the following embodiments are only exemplary illustrations made for fully explaining the present invention and should not be construed as limiting the technical solution and protection scope of the present invention.
Example one
The embodiment discloses a quick decompression chamber of civilian cabin air cooler simulation, the cabin body includes cockpit 1 and cabin 2, establishes window 3 before the simulation in cockpit 1 the place ahead, and window 3 divides into about two before the simulation, corresponds main driving position and copilot position respectively, and the window size can be adjusted according to the needs of different model simulation training. The simulation front view window is arranged on the cabin body, the simulation front view window is fixed on the cabin body by a welding process through processing a customized flange to form a window frame, a front view window negative pressure cover 4 is fixedly connected to the outer side of the window frame, and the front view window negative pressure cover 4 is a steel pressure-resistant connecting piece which is matched with the window frame in size and has a certain thickness. The rear surface of the front window negative pressure cover 4 is connected with a large-caliber front window negative pressure pipeline 5 and is connected with a negative pressure tank 6 through the front window negative pressure pipeline 5. A front window electric control gate valve 7 is additionally arranged between the front window negative pressure pipeline 5 and the negative pressure tank 6, and the negative pressure tank 6 is connected with a vacuum pump 8.
The basic flow and principle of the simulated rapid decompression process are as follows:
the first step is as follows: the electric control gate valve 7 of the front view window is closed, the vacuum pump 8 is opened, the vacuum pump 8 carries out air extraction operation to enable negative pressure to be generated in the negative pressure tank 6, the negative pressure value in the negative pressure tank 6 can be adjusted according to the requirements of a simulation experiment, and the state required by the experiment (generally, the maximum simulated altitude can reach 30000 m) is achieved.
The second step is that: when an experiment for simulating the density and pressure loss state of the cockpit 1 is started, the electric control gate valve 7 of the front view window is opened (the opening degree of the electric control gate valve 7 of the front view window can be adjusted according to the requirement of the experimental state), at the moment, the cockpit 1 is communicated with the negative pressure tank 6 through the simulation front view window 3, the negative pressure cover 4 of the front view window and the negative pressure pipeline 5 of the front view window, the negative pressure tank 6 which is in the negative pressure state is created in advance to generate the negative pressure air suction effect on the cockpit 1, and therefore the scene state of density and pressure loss in the cockpit 1 is simulated.
The process is a basic principle and a process for simulating various density and pressure loss states in the cockpit 1. The situation of losing pressure and density of the civil aircraft which may be encountered in the flying process is complex, and various different states may be presented, such as cracks, holes, fragmentation or integral falling of the front view window glass and flying out of the cockpit, etc. (5 and 14 days in 2018, 3U8633 flights in Sichuan aviation, and the situation that the front view window glass at the position of the copilot falls integrally and flies out of the cockpit occurs in the flying process). In order to simulate various possible pressure loss states, the process needs to be changeable, adjustable and controllable through technical means. To achieve this, the present embodiment is characterized by adding a front window variable adjusting device 9 simulating different density losing states at the position of the simulated front window 3 of the cockpit 1.
The front view window variable adjusting device 9 is divided into a left part and a right part 2, has the same structure, respectively corresponds to the positions of a main driver and a copilot, and is composed of a positioning clamping groove 30, an organic glass template 31, a locking rotary handle 32 and a handle 33 which are processed on a window frame in advance; the organic glass template 31 can be processed and customized according to the needs of experimental states, and can be prefabricated into cracks, holes, irregular broken holes and the like with different sizes. The organic glass template is arranged in the positioning clamping groove 30 and is fixed through locking rotary handles 32 arranged on the window frames around. The organic glass template 31 can be replaced and reused at will, and can be selected according to the requirements of the experimental state.
Obviously, the organic glass template 31 of the front window variable adjusting device 9 should be located in the positioning clamping groove 30 on the window frame of the front window 3 after being assembled, and a sealing strip or a sealing ring is additionally arranged on the positioning clamping groove 30 to match with the pressing force of the locking rotary handle 32, so that the sealing connection state between the two is realized.
Example two
The present embodiment differs from the first embodiment in that a cabin door variable adjustment device 14 is provided on the cabin door of the cabin 2 in addition to the front window variable adjustment device 9 provided on the simulated front window 3 of the cockpit 1.
Like the possible conditions of density loss and pressure loss of the cockpit 1, the airplane can also cause the conditions of density loss and pressure loss in the cockpit 2 due to various reasons in the flying process, such as cabin door air leakage caused by cabin door faults or the whole falling of the cabin door and flying out of the cabin. In order to perform adaptive training and emergency treatment exercises for crew members in the cabin 2, the simulated rapid decompression chamber of the present embodiment is provided with a simulation device (shown in fig. 1) for simulating the door privacy loss in the cabin 2.
The density losing of the simulated cabin door is realized by that a large flange which is processed by opening a hole and welding is used as a fixed door frame (the size of the large flange can be customized according to the size of the cabin door) on a cabin body to form the simulated cabin door 10, a cabin door negative pressure cover 11 is additionally arranged on the simulated cabin door 10, and the cabin door negative pressure cover 11 is connected with a negative pressure tank 6 through a cabin door negative pressure pipeline 12. A hatch electric control gate valve 13 is additionally arranged on the hatch negative pressure pipeline 12. In order to simulate different leakage states such as holes, cracks, dislocation, falling and the like which may occur in the cabin door, a cabin door variable adjusting device 14 is additionally arranged on the inner side of the simulated cabin door 10, and the principle and the process of the situation that rapid decompression occurs in the cabin when the simulated cabin door is in the leakage state are the same as those of the cockpit 1 (see attached figures 1/2 for details).
EXAMPLE III
The present embodiment is different from the first embodiment in that a front window variable adjustment device 9 is disposed in the pseudo front window 3 of the cockpit 1, a hatch door variable adjustment device 14 is disposed in the hatch door of the cockpit 2, and a hatch window variable adjustment device 16 is disposed in the hatch door of the cockpit 2.
Similarly, in order to simulate the situation that the inner side window of the cabin 2 has a crack, falls off and the like and causes rapid decompression in the cabin, a simulation side window 15 and a side window variable adjusting device 16 are additionally arranged on the cabin wall of the cabin 2, the outer side of the simulation side window is connected with the negative pressure tank 6 through a side window negative pressure cover 17 and a side window negative pressure pipeline 18, a side window electric control gate valve 19 is additionally arranged on the side window negative pressure pipeline 18, and the principle and the flow of the situation that rapid decompression occurs in the cabin when the simulation side window has a density losing situation are the same as the above (see the attached figure 1/the attached figure 2).
The significance of the above three embodiments is that: the device can simulate, adjust and control the decompression state caused by the decompression of a front window of a cockpit of a cabin or the cabin door and a porthole of the cabin through the simulated variable adjusting device of the decompression state, and the whole matched equipment comprises a large negative pressure air pumping system and a positive pressure air supply system to truly simulate various real scenes of the decompression state caused by the decompression of the cabin and the cabin, so that equipment guarantee is provided for simulation training and emergency drilling of an aircraft driver.
Example four
The embodiment provides a civil aircraft simulation rapid decompression chamber with the functions of simulating various flight processes of takeoff, flat flight, landing, height control rapid pull-up, dive descent and the like of an aircraft, and the civil aircraft simulation rapid decompression chamber is more advanced in performance and more complete in function. In order to realize the function, the embodiment is additionally provided with a large negative pressure air exhaust system and a positive pressure air supply system on the basis of the three embodiments. As shown in fig. 1, the negative pressure air exhaust system comprises a cockpit negative pressure pipeline 20 and a cockpit electronic control regulating valve 21, wherein one end of the cockpit negative pressure pipeline 20 is communicated with the negative pressure tank 6, and the other end is communicated with the cockpit 1. The negative pressure air extraction system further comprises a cabin negative pressure pipeline 22 and a cabin electric control adjusting valve 23, wherein one end of the cabin negative pressure pipeline 22 is communicated with the negative pressure tank 6, and the other end of the cabin negative pressure pipeline is communicated with the cabin 2. When the cockpit 1 and the cabin 2 need to simulate and create a conventional negative pressure environment, the cockpit electronic control regulating valve 21 and the cabin electronic control regulating valve 23 are respectively opened. The cockpit electrically controlled regulating valve 21 and the cabin electrically controlled regulating valve 23 can be commanded and controlled by a computer system according to experimental needs.
In order to achieve positive pressure air supply to the cockpit 1 and the cabin 2, an air reservoir 24 and an air compressor 25 connected thereto are provided. The rear end of the air storage tank 24 is connected with the cockpit 1 and the cabin 2 through a cockpit air supply line 26 and a cabin air supply line 27, and is respectively provided with a cockpit electronic control regulating valve 28 and a cabin electronic control regulating valve 29. When positive pressure air supply needs to be provided for the cockpit 1 and the cabin 2, the air compressor 25 can be started in advance, air with certain pressure is injected into the air storage tank 24, and then the cockpit electronic control regulating valve 28 and the cabin electronic control regulating valve 29 are respectively started.
The structure of several kinds of organic glass templates in different breaking states is given in figures 5-6, and the organic glass templates in different breaking states can be replaced according to different requirements in the experimental process so as to simulate the countermeasure under different secret losing states, and the mode can lead the aircraft driver and crew members to carry out the simulation training and emergency treatment drilling of various emergency situations.
The utility model discloses a civil aviation ware simulation rapid decompression chamber has consulted various aircraft structure and has designed, and the variable adjusting device of the secret state of losing of its configuration has realized adjustable, steerable that simulation aircraft lost secret, decompression state process. The device can be matched with a large negative pressure air extraction system to truly simulate various density loss and pressure loss conditions which can occur in the high-altitude flight process of an airplane, meanwhile, the negative pressure air extraction system can be combined with a positive pressure air supply system to simulate various flight processes such as take-off, flat flight, landing, rapid pull-up, dive and the like of the airplane, realistically simulate various true states which can occur in the high-altitude flight process of the airplane, provide a simulation platform and equipment guarantee for adaptability training and emergency treatment rehearsal of airplane drivers and crew members, are mature equipment for relevant scientific experimental researches such as adaptability training and emergency treatment rehearsal of the airplane drivers and crew members, realize breakthrough and innovation of key technology, fill up the blank in China, and have important significance for development of civil aviation flight safety and aviation transportation industry.
The utility model discloses a rapid decompression chamber of civil aircraft simulation combines with computer program, can simulate the various emergency that the aircraft probably met at the actual motion in-process according to the continuous adjustment and the change of experimental data and state, provides scientific basic foundation for civil aircraft's flight safety.
Claims (10)
1. A simulated rapid decompression chamber for a civil aircraft, characterized in that,
the device comprises a simulation window communicated with the environment in the cabin, a variable adjusting device matched with the simulation window and a negative pressure air extraction system configured outside the cabin and communicated with the simulation window;
the variable adjusting device is detachably arranged on the simulation window and comprises a template matched with the simulation window and a locking piece used for detachably arranging the template on the simulation window;
the negative pressure air exhaust system comprises a negative pressure tank, a negative pressure pipeline, an electric control gate valve and a negative pressure cover, wherein the negative pressure tank is provided with a vacuum pump, one end of the negative pressure pipeline is connected with the negative pressure tank, the other end of the negative pressure pipeline is connected with the negative pressure cover, the negative pressure cover sealing cover is arranged outside the simulation window, and the negative pressure pipeline is provided with the electric control gate valve.
2. The civilian aircraft simulated rapid decompression module of claim 1,
the simulation window is set as a front window of the cockpit, a cabin door of the cabin and/or a porthole of the cabin.
3. The civilian aircraft simulated rapid decompression module of claim 2,
the template is an experimental template made of different materials.
4. The civil aircraft simulated rapid decompression chamber of claim 3,
the template adopts the organic glass template, and its quantity is customized according to simulation experiment demand processing and is had a plurality ofly, and the prefabricated crack and the cracked hole that have different forms of breaking, different sizes and different positions on the template of difference for simulate different under-deck state of losing secret.
5. The civilian aircraft simulated rapid decompression module of claim 1,
the specific matching structure of the template and the simulation window is as follows: and a positioning clamping groove is processed in advance on the window frame of the simulation window, and the template is arranged in the positioning clamping groove, so that the connection between the template and the simulation window is realized.
6. The civilian aircraft simulated rapid decompression module of claim 1,
the locking piece adopts a plurality of locking rotating handles arranged along the periphery of the simulation window, and each locking rotating handle is provided with a rotating opening position and a rotating locking position.
7. The civilian aircraft simulated rapid decompression module of claim 1,
the template is provided with a handle which is convenient to take and replace.
8. The civilian aircraft simulated rapid decompression module of claim 1,
and a large negative pressure air exhaust system and a positive pressure air supply system are also arranged.
9. The civilian aircraft simulated rapid decompression module of claim 8,
the large negative pressure air extraction system comprises a negative pressure tank with a vacuum pump, two sets of negative pressure pipelines and two electric control regulating valves arranged on the two sets of negative pressure pipelines, wherein one set of negative pressure pipeline and the electric control regulating valve are communicated between the cockpit and the negative pressure tank, and the other set of negative pressure pipeline and the electric control regulating valve are communicated between the cabin and the negative pressure tank.
10. The civilian aircraft simulated rapid decompression module of claim 8,
the positive pressure air supply system comprises an air storage tank with an air compressor, two air supply pipelines and two electric control regulating valves arranged on the two air supply pipelines, wherein one air supply pipeline and one electric control regulating valve are communicated between the cockpit and the air storage tank, and the other air supply pipeline and the other electric control regulating valve are communicated between the cabin and the air storage tank.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111210695A (en) * | 2020-04-02 | 2020-05-29 | 烟台宏远氧业股份有限公司 | Simulated rapid decompression chamber of civil aircraft |
| CN114446105A (en) * | 2022-01-07 | 2022-05-06 | 山东金东数字创意股份有限公司 | Aviation experience cabin and working method thereof |
-
2020
- 2020-04-02 CN CN202020466900.6U patent/CN211653967U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111210695A (en) * | 2020-04-02 | 2020-05-29 | 烟台宏远氧业股份有限公司 | Simulated rapid decompression chamber of civil aircraft |
| CN114446105A (en) * | 2022-01-07 | 2022-05-06 | 山东金东数字创意股份有限公司 | Aviation experience cabin and working method thereof |
| CN114446105B (en) * | 2022-01-07 | 2024-03-29 | 山东金东数字创意股份有限公司 | Aviation experience cabin and working method thereof |
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