Airplane mockup test system

Abstract

The application relates to the field of aviation technology, in particular to an airplane simulation cabin test system, which comprises a fuselage front-end simulation cabin, a fuselage middle-section simulation cabin and a fuselage tail-end simulation cabin; wherein both sides along the respective width directions of the fuselage front-end simulation cabin, the fuselage middle-section simulation cabin and the fuselage tail-end simulation cabin are formed with simulation detection stations, and the cabin walls of the fuselage front-end simulation cabin, the cabin walls of the fuselage middle-section simulation cabin and the cabin walls of the fuselage tail-end simulation cabin are formed with detection openings corresponding to the simulation detection stations on both sides, so that simulation personnel can enter the two simulation detection stations on both sides via the detection openings on both sides correspondingly. It can be seen that two independent and fully functional test stations are integrated in the interiors of the airplane part simulation cabins, namely the nose cabin, the middle-section cabin and the tail cabin, so that the efficiency and resource optimization are improved.

Description

Technical Field

[0001] This application relates to the field of aviation technology, and in particular to an aircraft simulator testing system. Background Technology

[0002] Currently, in the process of aircraft research and development, production and maintenance, functional testing, environmental simulation or calibration of key equipment (such as avionics system, hydraulic system, transmission system, sensors, actuators, etc.) in the nose, fuselage midsection and tail are essential steps. In the existing technology, the equipment testing of different parts of the aircraft (nose, midsection and tail) is usually carried out using independent single-station simulation cabins. Such single-station simulation cabins have the following problems: The existing technology adopts the scheme of independent single-station simulation cabins for the front section of the fuselage, the midsection of the fuselage and the tail section of the fuselage. Its main defects are: (1) Single-station limitation: Each cabin can only test one device at a time, and the test is interrupted when the equipment is replaced. (2) Low resource utilization: A large number of test equipment and human resources are idle during the equipment replacement. (3) Low overall efficiency: The serial test mode leads to low test throughput, which becomes a bottleneck in the production or maintenance process. (4) Lack of flexibility: It is difficult to adapt to the needs of quickly switching test objects or conducting multi-state comparison tests. Therefore, it is necessary to continue to develop an efficient aircraft simulation cabin test system with reasonable resource optimization. Utility Model Content The purpose of this application is to provide an aircraft simulator testing system, which to a certain extent solves the technical problem of the urgent need to develop an efficient and resource-optimized aircraft simulator testing system in the existing technology.

[0003] This application provides an aircraft simulator testing system, including a front fuselage simulator, a mid-fuselage simulator, and a rear fuselage simulator. Simulation testing stations are formed on both sides along the width direction of each of the front fuselage simulator, the mid-fuselage simulator, and the rear fuselage simulator. The walls of each of these simulators have testing ports corresponding to the simulation testing stations on both sides, allowing simulator personnel to enter the two simulation testing stations on either side via these ports.

[0004] In the above technical solution, brackets are further provided below the bottom of the front fuselage simulation cabin, below the bottom of the middle fuselage simulation cabin, and below the bottom of the rear fuselage simulation cabin. The bottom walls of the front fuselage simulation cabin, the middle fuselage simulation cabin, and the rear fuselage simulation cabin all have inspection ports corresponding to the simulated inspection stations on both sides.

[0005] In any of the above technical solutions, a telescopic support leg and a roller are further provided below at least one of the brackets.

[0006] In any of the above technical solutions, the detection port on the bottom wall of the fuselage front simulation cabin extends to the side wall of the fuselage front simulation cabin.

[0007] In any of the above technical solutions, the detection port on the bottom wall of the fuselage tail-end simulation cabin extends to the side wall of the fuselage tail-end simulation cabin.

[0008] In any of the above technical solutions, further, the side walls of the fuselage front simulation cabin, the side walls of the fuselage mid-section simulation cabin, and the side walls of the fuselage rear simulation cabin are all provided with observation ports corresponding to the simulation testing stations on both sides.

[0009] In any of the above technical solutions, each of the observation ports is further provided with a closed door that can be opened or closed.

[0010] In any of the above technical solutions, a first partition is further provided in the fuselage front simulation cabin, and the first partition is fixed to the cabin wall of the fuselage front simulation cabin; the first partition is arranged along the length direction of the fuselage front simulation cabin, and divides the fuselage front simulation cabin into two front sub-simulation testing cabins along its width direction, and both front sub-simulation testing cabins are provided with the simulation testing station.

[0011] In any of the above technical solutions, further, each of the simulation testing stations on both sides of the fuselage front simulation cabin is equipped with a support frame and a computer, and the support frame is fixed to the cabin wall of the fuselage front simulation cabin, and the computer is placed on the support frame.

[0012] In any of the above technical solutions, a second partition is further provided inside the fuselage mid-section simulation cabin, and the second partition is fixed to the cabin wall of the fuselage mid-section simulation cabin; the second partition is arranged along the width direction of the fuselage mid-section simulation cabin, and divides the fuselage mid-section simulation cabin into a first fuselage mid-section simulation cabin and a second fuselage mid-section simulation cabin along its length direction. A third partition is provided in both the first fuselage mid-section simulation compartment and the second fuselage mid-section simulation compartment, and any third partition is fixed to the second partition and / or the compartment wall; any third partition is arranged along the length direction of the fuselage mid-section simulation compartment, and one of the third partitions divides the corresponding first fuselage mid-section simulation compartment into two first mid-section sub-simulation testing compartments along its width direction, and the other third partition divides the corresponding second fuselage mid-section simulation compartment into two second mid-section sub-simulation testing compartments along its width direction, and the simulation testing station is provided in both the two first mid-section sub-simulation testing compartments and the two second mid-section sub-simulation testing compartments.

[0013] In any of the above technical solutions, a fourth partition is further provided in the tail end simulation compartment of the fuselage, and the fourth partition is fixed to the compartment wall of the tail end simulation compartment of the fuselage; the fourth partition is arranged along the length direction of the front end simulation compartment of the fuselage, and divides the tail end simulation compartment of the fuselage into two tail end sub-simulation testing compartments along its width direction, and both tail end sub-simulation testing compartments are provided with the simulation testing station.

[0014] In any of the above technical solutions, each of the detection ports is further provided with a door that can be opened or closed.

[0015] In any of the above technical solutions, the simulated testing stations on both sides of the fuselage front simulation cabin are symmetrically arranged about the centerline extending along the length of the fuselage front simulation cabin.

[0016] In any of the above technical solutions, at least a portion of the simulated testing stations on both sides of the fuselage midsection simulation cabin are symmetrically arranged about the centerline extending along the length of the fuselage midsection simulation cabin.

[0017] In any of the above technical solutions, the simulation testing stations on both sides of the fuselage tail end simulation cabin are symmetrically arranged about the centerline extending along the length direction of the fuselage tail end simulation cabin.

[0018] Compared with the prior art, the beneficial effects of this application are as follows: The aircraft simulator testing system provided in this application integrates two independent and fully functional test stations (station A and station B) within the simulators of various parts of the aircraft (nose / mid section / tail section). The two stations within the same simulator can operate independently or work collaboratively. The control system can independently control each station, or share some resources according to testing needs (such as sharing an environmental chamber but independently controlling the temperature zone of each station). This eliminates test downtime caused by equipment changeover. The testing process (station A / B) and the preparation process (station B / A) completely overlap in time. Theoretically, as long as the preparation time is less than or equal to the testing time, the testing equipment can operate almost 100% continuously. For batch testing scenarios (such as production lines), the efficiency improvement can reach 50%~100% (depending on the ratio of testing to preparation time).

[0019] As can be seen, without adding additional physical chambers, both the "testing" and "preparing" states can be managed simultaneously within the same chamber. The same set of chamber environment simulation resources (such as temperature control systems and vacuum / pressure systems) can be optimized to serve two workstations (such as zone control or rapid switching), avoiding redundant construction. Operators can work continuously within the same physical space, reducing the time lost by moving between different independent chambers. The output per unit physical space (single simulation chamber) (number of test devices / time) is significantly increased. The same number of simulation chambers (three) can support twice the number of parallel testing / preparation tasks as a single workstation. The idle rate of expensive test equipment (such as high-power power supplies, high-precision signal sources, and environmental simulation devices) and manpower (operators and engineers) is greatly reduced, and the overall resource utilization rate is improved.

[0020] Furthermore, since each compartment is equipped with dual workstations, the equipment at one workstation can be repaired, updated, or replaced without affecting the use of the other workstation, thus improving the efficiency of simulation testing and increasing resource utilization. Attached Figure Description To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a structural schematic diagram of the fuselage front-end simulation cabin provided in an embodiment of this application; Figure 2 Another structural schematic diagram of the fuselage front simulation cabin provided in the embodiments of this application; Figure 3 Another structural schematic diagram of the fuselage front simulation cabin provided in the embodiments of this application; Figure 4 Another structural schematic diagram of the fuselage front simulation cabin provided in the embodiments of this application; Figure 5 Another structural schematic diagram of the fuselage front simulation cabin provided in the embodiments of this application; Figure 6 Another structural schematic diagram of the fuselage front simulation cabin provided in the embodiments of this application; Figure 7 This is a structural schematic diagram of the fuselage midsection simulation cabin provided in an embodiment of this application; Figure 8 Another structural schematic diagram of the fuselage midsection simulation cabin provided in this application embodiment; Figure 9 Another structural schematic diagram of the fuselage midsection simulation cabin provided for an embodiment of this application; Figure 10 Another structural schematic diagram of the fuselage midsection simulation cabin provided for an embodiment of this application; Figure 11 Another structural schematic diagram of the fuselage midsection simulation cabin provided for an embodiment of this application; Figure 12 Another structural schematic diagram of the fuselage midsection simulation cabin provided for an embodiment of this application; Figure 13 This is a structural schematic diagram of the fuselage tail section provided in an embodiment of this application; Figure 14 Another structural schematic diagram of the fuselage tail section simulation cabin provided in this application embodiment; Figure 15 Another structural schematic diagram of the fuselage tail section simulation cabin provided in the embodiments of this application; Figure 16 This is another structural schematic diagram of the fuselage tail section provided in the embodiments of this application.

[0022] Figure label: 1-Fuselage front end simulation cabin, 101-Front section sub-simulation and testing cabin, 2-Fuselage mid-section simulation cabin, 201-First fuselage mid-section simulation cabin, 2011-First mid-section sub-simulation and testing cabin, 3-Fuselage rear end simulation cabin, 31-Rear end sub-simulation and testing cabin, 4-Simulation and testing station, 5-Test port, 6-Observation port, 7-Bracket, 8-Telescopic support leg, 9-Roller, 10-First bulkhead, 11-Support frame, 12-Computer, 13-Second bulkhead, 14-Third bulkhead, 15-Fourth bulkhead, 16-Door, 17-Sealed door. Detailed Implementation

[0023] The technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of this application, but not all embodiments.

[0024] The components of the embodiments of this application described and shown in the accompanying drawings can be arranged and designed in a variety of different configurations. Therefore, the following detailed description of the embodiments of this application provided in the drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application.

[0025] Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0027] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0028] The following reference Figures 1 to 16 This application describes an aircraft simulator test system according to some embodiments.

[0029] See Figures 1 to 16 As shown, an embodiment of this application provides an aircraft simulator testing system, including a front fuselage simulator 1, a mid-fuselage simulator 2, and a rear fuselage simulator 3. Simulation testing stations 4 are formed on both sides along their respective width directions in the front fuselage simulator 1, the mid-fuselage simulator 2, and the rear fuselage simulator 3. The walls of the front fuselage simulator 1, the mid-fuselage simulator 2, and the rear fuselage simulator 3 are all formed with testing ports 5 corresponding to the simulation testing stations 4 on both sides, so that simulated personnel can enter the two simulation testing stations 4 on both sides through the testing ports 5 on both sides.

[0030] As can be seen from the structure described above, the aircraft simulator testing system provided in this application integrates two independent and fully functional test stations (station A and station B) inside the simulators of various parts of the aircraft (nose / mid section / tail section). The two stations in the same simulator can operate independently or work collaboratively. The control system can independently control each station, or share some resources according to test requirements (such as sharing an environmental chamber, but independently controlling the temperature zone of each station). This eliminates test downtime caused by equipment changeover. The test process (station A / B) and the preparation process (station B / A) completely overlap in time. Theoretically, as long as the preparation time is less than or equal to the test time, the test equipment can operate almost 100% continuously. For batch testing scenarios (such as production lines), the efficiency improvement can reach 50%~100% (depending on the ratio of test to preparation time).

[0031] As can be seen, without adding additional physical chambers, both the "testing" and "preparing" states can be managed simultaneously within the same chamber. The same set of chamber environment simulation resources (such as temperature control systems and vacuum / pressure systems) can be optimized to serve two workstations (such as zone control or rapid switching), avoiding redundant construction. Operators can work continuously within the same physical space, reducing the time lost by moving between different independent chambers. The output per unit physical space (single simulation chamber) (number of test devices / time) is significantly increased. The same number of simulation chambers (three) can support twice the number of parallel testing / preparation tasks as a single workstation. The idle rate of expensive test equipment (such as high-power power supplies, high-precision signal sources, and environmental simulation devices) and manpower (operators and engineers) is greatly reduced, and the overall resource utilization rate is improved.

[0032] Furthermore, since each compartment is equipped with dual workstations, the equipment at one workstation can be repaired, updated, or replaced without affecting the use of the other workstation, thus improving the efficiency of simulation testing and increasing resource utilization.

[0033] In this embodiment, preferably, as follows: Figure 1 , Figure 7 and Figure 13 As shown, brackets 7 are provided at the bottom of the front fuselage simulation cabin 1, the bottom of the middle fuselage simulation cabin 2, and the bottom of the rear fuselage simulation cabin 3. like Figure 4 , Figure 5 , Figure 11 , Figure 12 as well as Figure 15 As shown, the bottom wall of the front fuselage simulation cabin 1, the bottom wall of the mid-fuselage simulation cabin 2, and the bottom wall of the rear fuselage simulation cabin 3 all have the aforementioned inspection ports 5 corresponding to the simulation inspection stations 4 on both sides.

[0034] As can be seen from the structure described above, brackets 7 are provided at the bottom of the front fuselage simulation cabin 1, the bottom of the mid-fuselage simulation cabin 2, and the bottom of the rear fuselage simulation cabin 3. The three brackets 7 respectively support the corresponding front fuselage simulation cabin 1, mid-fuselage simulation cabin 2, and rear fuselage simulation cabin 3, so as to avoid the instability caused by placing them directly on the ground.

[0035] In addition, two inspection ports are provided on the bottom wall of the front fuselage simulation cabin 1, the middle fuselage simulation cabin 2, and the rear fuselage simulation cabin 3. Each inspection port corresponds to the simulation inspection station 4 on both sides. This makes it convenient for simulation personnel to enter the corresponding station through the bottom inspection port 5. The inspection port at the bottom of the cabin facilitates processing and manufacturing. Furthermore, a bracket 7 is provided under the cabin to provide space for simulation personnel to enter the cabin through the bottom inspection port 5.

[0036] Furthermore, preferably, the inspection port 5 on the bottom wall of the fuselage front simulation cabin 1 extends to the side wall of the fuselage front simulation cabin 1, increasing the space for the inspection port 5 and making it easier for the operator to enter the cabin. Of course, it is not limited to this; the inspection port 5 on the fuselage front simulation cabin 1 may also be located only on the bottom wall.

[0037] Furthermore, preferably, the inspection port 5 on the bottom wall of the aft simulation cabin 3 extends to the side wall of the aft simulation cabin 3, increasing the space for the inspection port 5 and making it easier for the operator to enter the cabin. Of course, it is not limited to this; the inspection port 5 on the aft simulation cabin 3 may also be located only on the bottom wall.

[0038] Of course, the access ports on the front fuselage simulation cabin 1, the mid-fuselage simulation cabin 2, and the rear fuselage simulation cabin 3 are not limited to being located on their respective bottom walls. They can also be located on the side walls, or the access ports can be located on the side walls or bottom walls, depending on the actual needs.

[0039] In this embodiment, preferably, as follows: Figure 1 and Figure 13 As shown, each of the three brackets 7 is equipped with a telescopic support leg 8 and a roller 9. Based on the structure described above, taking one of the cabins, namely the fuselage front simulation cabin 1, as an example, when the fuselage front simulation cabin 1 is needed, the first telescopic support leg 8 can be shortened, allowing the first roller 9 to contact the ground, thus facilitating the movement of the fuselage front simulation cabin 1 to the designated position. After the fuselage front simulation cabin 1 is moved to the designated position, the first telescopic support leg 8 can be extended, allowing the first telescopic support leg 8 to support the ground, and the first roller 9 to detach from the ground, thus providing stable support for the fuselage front simulation cabin 1. The usage process of the telescopic support leg 8 and roller 9 on the bracket 7 of the fuselage mid-section simulation cabin 2 and the fuselage tail-end simulation cabin 3 can be referred to that of the fuselage front simulation cabin 1, and will not be described in detail here.

[0040] It should be noted that: it is not limited to installing telescopic support legs 8 and rollers 9 on the brackets 7 of the front fuselage simulation cabin 1, the mid-fuselage simulation cabin 2, and the rear fuselage simulation cabin 3. Telescopic support legs 8 and rollers 9 can also be installed on only one or two of the brackets 7, depending on the actual needs. In this embodiment, preferably, as follows: Figure 4 , Figure 9 , Figure 10 , Figure 13 and Figure 14 As shown, the side walls of the front fuselage simulation cabin 1, the middle fuselage simulation cabin 2, and the rear fuselage simulation cabin 3 all have observation ports 6 corresponding to the simulation testing stations 4 on both sides.

[0041] As can be seen from the structure described above, observation ports 6 are provided on the side walls of the front fuselage simulation cabin 1, the side walls of the middle fuselage simulation cabin 2, and the side walls of the rear fuselage simulation cabin 3. This allows instructors to observe the simulated personnel's specific operations from the outside, thus facilitating the provision of correct guidance.

[0042] Furthermore, preferably, each observation port 6 is equipped with a closable door 17 that can be opened or closed. After the simulation test is completed, the closable door 17 can be closed to prevent dust and water damage. Of course, this closable door 17 may not be provided, depending on the actual needs.

[0043] Furthermore, preferably, the closed door 17 can be made of a transparent material, thus forming a visible structure, so that the interior of the cabin can be observed even without opening the closed door 17.

[0044] Furthermore, preferably, the rear side of the front simulation cabin 1 along its length direction is provided with a detection port 5 corresponding to the simulation detection stations 4 on the left and right sides. That is, detection ports 5 are respectively provided on the rear side of the front simulation detection cabin 101.

[0045] Furthermore, preferably, the two side walls of the first fuselage mid-section simulation compartment 201 along its width direction and the two side walls of the second fuselage mid-section simulation compartment 2 along its width direction are each provided with observation ports 6 corresponding to the two simulation testing stations 4 on both sides. That is to say, each of the two first mid-section sub-simulation testing compartments 2011 and the two second mid-section sub-simulation testing compartments is provided with at least one observation port 6. Of course, it is not limited to this.

[0046] Furthermore, preferably, the two side walls of the simulated cabin 3 at the rear of the fuselage, along its width direction, each have observation ports 6 corresponding to the two simulated testing stations 4 on both sides. Of course, this is not the only option.

[0047] It should be noted that the aforementioned observation port 6 may not be required; the choice should be made based on actual needs.

[0048] In this embodiment, preferably, as follows: Figure 2 and Figure 6 As shown, a first partition 10 is provided inside the front fuselage simulation cabin 1, and the first partition 10 is fixed to the cabin wall of the front fuselage simulation cabin 1; the first partition 10 is arranged along the length direction of the front fuselage simulation cabin 1, and divides the front fuselage simulation cabin 1 into two front sub-simulation testing cabins 101 along its width direction, and both front sub-simulation testing cabins 101 are provided with simulation testing stations 4. As can be seen from the structure described above, the first partition 10 divides the front simulation cabin 1 of the fuselage into two independent front sub-simulation test cabins 101. Thus, two testers can enter the two independent front sub-simulation test cabins 101 to carry out simulation test work. Moreover, the two operate independently and do not affect each other. Especially in the assessment operation, it is convenient to conduct independent testing on the simulated personnel and avoid the two referring to each other's work. In addition, the first partition 10 can be used as a supporting body, and some test components can be installed on both sides of it, which has a higher degree of integration and helps to save space.

[0049] It should be noted that this first partition 10 may not be required; the choice depends on the actual needs.

[0050] In this embodiment, preferably, as follows: Figure 6 As shown, the simulation testing stations 4 on both sides of the front fuselage simulation cabin 1 are symmetrically arranged about the center line extending along the length of the front fuselage simulation cabin 1. As can be seen from the structure described above, the symmetrical arrangement of the two simulation testing stations 4 within the front-end simulation cabin 1 facilitates the assembly of components at the corresponding stations and results in a more regular layout. Of course, this is not the only limitation; the two simulation testing stations 4 can also be arranged asymmetrically, according to their respective needs, in a reasonable layout. In this embodiment, preferably, as follows: Figure 6As shown, both sides of the simulation testing station 4 inside the front fuselage simulation cabin 1 are equipped with a support frame 11 and a computer 12. The support frame 11 is fixed to the cabin wall of the front fuselage simulation cabin 1, and the computer 12 is placed on the support frame 11. As can be seen from the structure described above, the support frame 11 serves to support equipment such as the computer 12. It is ergonomic, easy to simulate human operation, and more regular and aesthetically pleasing. The support frame 11 is fixed to the bulkhead, making the support frame 11 more robust and stable.

[0051] Of course, the support frame 11 may not be provided, and the computer 12 may be placed on the bulkhead instead. In this embodiment, preferably, as follows: Figure 7 and Figure 8 As shown, a second bulkhead 13 is provided inside the fuselage mid-section simulation cabin 2, and the second bulkhead 13 is fixed to the cabin wall of the fuselage mid-section simulation cabin 2; the second bulkhead 13 is arranged along the width direction of the fuselage mid-section simulation cabin 2, and divides the fuselage mid-section simulation cabin 2 into a first fuselage mid-section simulation cabin 201 and a second fuselage mid-section simulation cabin 2 along its length direction. A third partition 14 is provided in both the first fuselage mid-section simulation compartment 201 and the second fuselage mid-section simulation compartment 2, and any third partition 14 is fixed to the second partition 13 and / or the compartment wall; any third partition 14 is provided along the length direction of the fuselage mid-section simulation compartment 2, and one of the third partitions 14 divides the corresponding first fuselage mid-section simulation compartment 201 into two first mid-section sub-simulation testing compartments 2011 along its width direction, and the other third partition 14 divides the corresponding second fuselage mid-section simulation compartment 2 into two second mid-section sub-simulation testing compartments along its width direction, and simulation testing stations 4 are provided in both the two first mid-section sub-simulation testing compartments 2011 and the two second mid-section sub-simulation testing compartments.

[0052] As can be seen from the structure described above, the fuselage mid-section simulation cabin 2 is divided into two compartments by the second partition 13, namely the first fuselage mid-section simulation cabin 201 and the second fuselage mid-section simulation cabin 2. These two areas perform different simulation detection functions. One can be used to simulate the interior of the fuel tank, and the other can be used to simulate the exterior of the fuel tank. They are separated from each other and do not affect each other.

[0053] Then, using two third partitions 14, the first fuselage mid-section simulation cabin 201 and the second fuselage mid-section simulation cabin 2 are further divided into two compartments along the width direction of the fuselage mid-section simulation cabin 2. That is, the interior of the fuselage mid-section simulation cabin 2 forms four independent compartments, each of which can perform independent simulation tests. The third partition 14 divides the front fuselage simulation cabin 1 into two independent mid-section sub-simulation test cabins, allowing two testers to enter the two independent front sub-simulation test cabins 101 to conduct simulation test work. Moreover, the two operate independently without affecting each other. Especially during assessment operations, it is convenient to conduct independent tests on the simulated personnel and avoid the two referring to each other's work.

[0054] It should be noted that this third partition 14 may not be required; the choice depends on the actual needs. In this embodiment, preferably, as follows: Figure 8 As shown, the simulation testing stations 4 on both sides of the first middle section simulation testing chamber 2011 are completely identical and arranged in the same direction. They are not symmetrically arranged about the center line extending along the length of the first middle section simulation testing chamber 2011. Of course, this is not the only possibility. The simulation testing stations 4 on both sides of the first middle section simulation testing chamber 2011 can also be symmetrically arranged about the center line extending along the length of the first middle section simulation testing chamber 2011, depending on the actual needs.

[0055] As can be seen from the structure described above, the simulation testing stations 4 on both sides of the first middle section simulation testing chamber 2011 are completely identical and arranged in the same direction, which facilitates training in the same orientation.

[0056] In this embodiment, preferably, the simulation testing stations 4 on both sides of the second middle section simulation testing chamber are completely identical and are symmetrically arranged about the center line extending along the length direction of the first middle section simulation testing chamber 2011 (not shown in the figure). Of course, it is not limited to this. The simulation testing stations 4 on both sides of the second middle section simulation testing chamber may not be symmetrically arranged about the center line extending along the length direction of the first middle section simulation testing chamber 2011. The specific arrangement depends on the actual needs.

[0057] As can be seen from the structure described above, the two simulated testing stations 4 within the second middle section's simulated testing chamber are symmetrically arranged, which facilitates the assembly of components at the corresponding stations and results in a more regular layout. In this embodiment, preferably, as shown... Figure 14 As shown, a fourth partition 15 is provided in the tail end simulation compartment 3 of the fuselage, and the fourth partition 15 extends along the length direction of the front end simulation compartment 1 of the fuselage, and divides the tail end simulation compartment 3 of the fuselage into two tail end sub-simulation inspection compartments 31, and each of the two tail end sub-simulation inspection compartments 31 is provided with a simulation inspection station 4.

[0058] As described above, the fourth partition 15 divides the tail-end simulation compartment 3 into two independent tail-end sub-simulation testing compartments 31. This allows two test personnel to enter the two independent tail-end sub-simulation testing compartments 31 to conduct simulation testing. Furthermore, both compartments operate independently without interfering with each other. This is particularly beneficial during assessment operations, facilitating independent testing of the simulated personnel and preventing them from referencing each other's work. Additionally, the fourth partition 15 can serve as a supporting structure, with testing components installed on both sides, resulting in higher integration and saving space. It should be noted that the fourth partition 15 can also be omitted, depending on actual needs.

[0059] Further, preferably, such as Figure 2 , Figure 7 and Figure 14 As shown, simulation testing components can be installed on the first partition 10, the second partition 13, the third partition 14, and the fourth partition 15, resulting in higher integration and full utilization of space. Of course, this is not the only benefit.

[0060] In this embodiment, preferably, as follows: Figure 14 As shown, the simulation testing stations 4 on both sides of the tail end simulation cabin 3 are symmetrically arranged about the center line extending along the length of the tail end simulation cabin 3. In other words, the simulation testing stations 4 in the two tail end simulation testing cabins 31 are symmetrically arranged about the center line extending along the length of the tail end simulation cabin 3. As can be seen from the structure described above, the symmetrical arrangement of the two simulation testing stations 4 within the simulation compartment 3 at the rear of the fuselage facilitates the assembly of components at the corresponding stations and results in a more regular layout. Of course, this is not the only limitation; the two simulation testing stations 4 can also be arranged asymmetrically, according to their respective needs, in a reasonable layout. In this embodiment, preferably, as follows: Figure 5 , Figure 12 and Figure 16 As shown, each detection port 5 is equipped with a hatch 16 that can be opened or closed. Based on the structure described above, once the simulation test is completed, the hatch 16 can be closed to prevent dust and water damage.

[0061] It should be noted that the aforementioned hatch 16 may not be installed, depending on the actual needs. Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. An aircraft simulator testing system, characterized in that, It includes a front fuselage simulation cabin, a mid-fuselage simulation cabin, and a rear fuselage simulation cabin; wherein, simulation testing stations are formed on both sides along the width direction of the front fuselage simulation cabin, the mid-fuselage simulation cabin, and the rear fuselage simulation cabin, and the cabin walls of the front fuselage simulation cabin, the mid-fuselage simulation cabin, and the rear fuselage simulation cabin are all formed with testing ports corresponding to the simulation testing stations on both sides, so that simulated personnel can enter the two simulation testing stations on both sides through the testing ports on both sides.

2. The aircraft simulator testing system according to claim 1, characterized in that, Brackets are provided at the bottom of the front fuselage simulation cabin, the bottom of the mid-fuselage simulation cabin, and the bottom of the rear fuselage simulation cabin. The bottom walls of the front fuselage simulation cabin, the middle fuselage simulation cabin, and the rear fuselage simulation cabin all have inspection ports corresponding to the simulated inspection stations on both sides.

3. The aircraft simulator testing system according to claim 2, characterized in that, At least one of the brackets is provided with a telescopic support leg and rollers underneath; and / or The detection port on the bottom wall of the fuselage front simulation cabin extends to the side wall of the fuselage front simulation cabin; and / or The detection port on the bottom wall of the fuselage tail-end simulation cabin extends to the side wall of the fuselage tail-end simulation cabin.

4. The aircraft simulator testing system according to claim 1, characterized in that, The side walls of the front fuselage simulation cabin, the mid-fuselage simulation cabin, and the rear fuselage simulation cabin all have observation ports corresponding to the simulated testing stations on both sides.

5. The aircraft simulator testing system according to claim 4, characterized in that, Each of the observation ports is equipped with a closed door that can be opened or closed.

6. The aircraft simulator testing system according to claim 1, characterized in that, The front fuselage simulation compartment is provided with a first partition, which is fixed to the compartment wall of the front fuselage simulation compartment. The first partition is arranged along the length of the front fuselage simulation compartment and divides the front fuselage simulation compartment into two front sub-simulation testing compartments along its width. Both front sub-simulation testing compartments are provided with the simulation testing station.

7. The aircraft simulator testing system according to claim 1, characterized in that, The simulation testing stations on both sides of the front fuselage simulation cabin are equipped with support frames and computers, and the support frames are fixed to the cabin wall of the front fuselage simulation cabin, while the computers are placed on the support frames.

8. The aircraft simulator testing system according to claim 1, characterized in that, The mid-section fuselage simulation cabin is provided with a second partition, and the second partition is fixed to the cabin wall of the mid-section fuselage simulation cabin; the second partition is arranged along the width direction of the mid-section fuselage simulation cabin, and divides the mid-section fuselage simulation cabin into a first mid-section fuselage simulation cabin and a second mid-section fuselage simulation cabin along its length direction. A third partition is provided in both the first fuselage mid-section simulation compartment and the second fuselage mid-section simulation compartment, and any third partition is fixed to the second partition and / or the compartment wall; any third partition is arranged along the length direction of the fuselage mid-section simulation compartment, and one of the third partitions divides the corresponding first fuselage mid-section simulation compartment into two first mid-section sub-simulation testing compartments along its width direction, and the other third partition divides the corresponding second fuselage mid-section simulation compartment into two second mid-section sub-simulation testing compartments along its width direction, and the simulation testing station is provided in both the two first mid-section sub-simulation testing compartments and the two second mid-section sub-simulation testing compartments.

9. The aircraft simulator testing system according to claim 1, characterized in that, The tail end simulation compartment of the fuselage is provided with a fourth partition, and the fourth partition is fixed to the compartment wall of the tail end simulation compartment; the fourth partition is arranged along the length direction of the front end simulation compartment of the fuselage, and divides the tail end simulation compartment of the fuselage into two tail end sub-simulation and testing compartments along its width direction, and both tail end sub-simulation and testing compartments are provided with the simulation and testing station.

10. The aircraft simulator test system according to any one of claims 1 to 9, characterized in that, Each of the aforementioned detection ports is equipped with an openable or closable hatch; and / or The simulated testing stations on both sides of the fuselage front simulation cabin are symmetrically arranged about the centerline extending along the length of the fuselage front simulation cabin; and / or At least a portion of the simulated testing stations on both sides of the mid-section fuselage simulation chamber are symmetrically arranged about the centerline extending along the length of the mid-section fuselage simulation chamber; and / or The simulation testing stations on both sides of the fuselage tail end simulation cabin are symmetrically arranged about the centerline extending along the length of the fuselage tail end simulation cabin.

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