Light-weight full-flight simulator large-scale dome screen

Abstract

The utility model discloses a light-weight full-flight simulator large-scale dome screen which comprises a screen surface, a top cover, a projector support and a rear room body. A top cover is fixed above the screen surface; the projector supports are fixedly connected with the top cover, and the projector supports penetrate through the surface of the top cover, so that the projectors can project to the inner surface of the screen surface; the rear room body is fixedly connected to the rear part of the curtain surface and is mainly used for providing an access site for personnel and a cabin and providing a placement space for equipment; and the lower part of the curtain surface and the lower part of the rear room body are fixed on the motion platform. According to the utility model, the dome screen is installed and fixed above the motion platform of the full-flight simulator, and is mainly used for providing a visual scene with a large visual angle and high definition for a pilot, so that the driver in a simulation cabin can experience a more vivid flight effect.

Description

Technical Field

[0001] This utility model belongs to the field of dome structure design for full flight simulators, and in particular, it is a lightweight large dome structure for full flight simulators. Background Technology

[0002] A full flight simulator is a testing and training device used to simulate the flight state, flight environment, and flight conditions of an aircraft during a mission, providing pilots with similar control loads, visual, auditory, and kinematic sensations. The dome screen is a crucial component of a full flight simulator and has a significant impact on the pilot. The larger the field of view of the dome screen, the better the pilot's visual experience. Simultaneously, the lighter weight of the dome screen effectively reduces the load on the motion platform below, thus providing the pilot with a better kinematic experience.

[0003] Many traditional full-flight simulators use fiberglass, steel, sheet metal, or profiles as their main materials for their large dome screens. These materials have disadvantages such as being heavy and having complicated assembly processes. The dome screens of the same volume are relatively heavy, which leads to a higher overall weight of the simulator's upper cabin system, more complex installation, and a longer assembly cycle. This, in turn, limits the simulator's motion characteristics and results in higher assembly and maintenance costs. Utility Model Content

[0004] The purpose of this invention is to provide a lightweight large dome screen for a full flight simulator, so as to achieve the installation of the simulator dome screen more simply and quickly, and to achieve a larger field of view.

[0005] The technical solution to achieve the purpose of this utility model is as follows:

[0006] A lightweight full-flight simulator large dome screen includes: a screen surface, a top cover, a projector bracket, and a rear chamber.

[0007] A top cover is fixed above the screen; the projector bracket is fixed to the top cover, and multiple projector brackets are provided. The projector brackets pass through the surface of the top cover so that the projector can project onto the inner surface of the screen; the rear chamber is fixed to the rear of the screen and is mainly used to provide access for personnel and cabins, as well as space for equipment; the area below the screen and the area below the rear chamber are both fixed to the motion platform.

[0008] Compared with the prior art, the significant advantages of this utility model are:

[0009] (1) Low manufacturing cost, neatly segmented screen, and production can be completed with fewer molds. (3) Large field of view, the inner diameter of the dome in this utility model is up to 7 meters, the maximum field of view of the dome is 300 degrees in the horizontal direction and 100 degrees in the vertical direction. (2) Lightweight, the main structure is made of carbon fiber and PMI foam sandwich laminate structure, which greatly reduces the weight of the dome, and the weight can be controlled within 900 kg. (3) Large field of view, the inner diameter of the dome in this utility model is up to 7 meters, the maximum field of view of the dome is 300 degrees in the horizontal direction and 100 degrees in the vertical direction. (4) High rigidity, the top of the dome can support multiple large simulation projectors, and the dome image can be kept basically unchanged under extreme working conditions. Attached Figure Description

[0010] Figure 1 This is a schematic diagram of the dome structure composition of Embodiment 1 of this utility model.

[0011] Figure 2 This is a schematic diagram of the rear chamber structure of Embodiment 1 of this utility model.

[0012] Figure 3 This is a schematic diagram of the incident point on the surface of the sound field inside the dome structure, which is an embodiment of this utility model.

[0013] Figure 4 This is a static acoustic wave line analysis diagram inside the dome structure of Embodiment 1 of this utility model.

[0014] Figure 5 This is an example of the pilot's eye-point field of view analysis diagram inside the dome-shaped cockpit of this utility model, which is Embodiment 1.

[0015] Figure 6 This is a schematic diagram of the finite element analysis model of the dome structure in Embodiment 1 of this utility model.

[0016] Figure 7 This is a schematic diagram of the maximum deformation point calculated by finite element analysis of the dome structure in Embodiment 1 of this utility model. Detailed Implementation

[0017] To make the present invention clearer, the present invention will be further described below with reference to the accompanying drawings and specific embodiments. The specific embodiments here are only used to explain the present invention and are not intended to limit the present invention.

[0018] In the description of this utility model, it should be noted that the terms "front", "back", "left", "right", "up", "down", "vertical", "horizontal", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of description, and are not intended to be implemented in a specific orientation.

[0019] Combination Figure 1As shown, this utility model discloses a lightweight full flight simulator large dome structure based on carbon fiber composite material. The structure includes a screen 1, a top cover 2, a projector bracket 3, a rear chamber 4, and an outer aesthetic component 5.

[0020] The screen 1 is fixedly connected to the top cover 2 at the top and to the rear chamber 4 at the rear. The bottom of the screen 1 and the bottom of the rear chamber 4 are both fixed to the motion platform. The projector bracket 3 is fixedly connected to the top cover 2. There are four projector brackets in total, arranged symmetrically in pairs. The projector brackets 3 pass through the surface of the top cover 2 so that the projector can project normally onto the inner surface of the screen 1. The rear chamber 4 is fixedly connected to the screen 1 and is mainly used to provide access for personnel and cabins, as well as space for the placement of equipment such as instructors' platforms and seats. The outer aesthetic component 5 is fixedly connected to the outer surfaces of the screen 1 and the top cover 2 and is mainly used to cover the segmented flange joints of the screen 1 and the top cover 2, as well as the installation interfaces between the screen 1, the rear chamber 4 and the motion platform below.

[0021] The inner and outer layers of both the screen 1 and the top cover 2 are made of carbon fiber cloth, with a PMI foam interlayer in between. The inner surface of the screen 1 is clean and smooth, sprayed with water-based reflective paint, with a step difference and flatness of no more than two millimeters, and no visible dents or protrusions. The projector bracket 3 is assembled from an aluminum alloy angle frame and a carbon fiber skin, and the projector can be mounted on the projector bracket 3 with bolts through the mounting holes around the perimeter. The rear chamber 4 adopts a structure in which an aluminum alloy frame is connected to a carbon fiber skin, effectively reducing the weight of the structure. The skin of the outer aesthetic component 5 adopts a carbon fiber honeycomb interlayer structure, and the connectors are made of machined aluminum alloy angles.

[0022] The projector bracket 3 supports four large projectors. The structure ensures that the maximum displacement of the projector bracket 3 is no more than one millimeter under a maximum overload of 2.5g in each direction of the moving platform below.

[0023] In one implementation, the screen 1 and the top cover 2 are each composed of ten arc-shaped spherical blocks, each with a longitude angle of 36°, an inner diameter of seven meters, and a thickness of seven millimeters. They all adopt a four-sided flanged skin structure. The height from the center of the top cover 2 to the lower motion platform reaches six meters. With the eye point (center of the sphere) as the reference center, the field of view can reach a maximum of 300 degrees to the left and right and 100 degrees to the top and bottom. The large field of view can meet the needs of pilots to conduct more training courses.

[0024] Combination Figure 2As shown, the rear chamber 4 consists of seven parts: a left rear chamber frame assembly 6, a right rear chamber frame assembly 7, a main rear chamber frame assembly 8, a dome screen connecting angle assembly 9, a door assembly 10, an equipment door assembly 11, and a step 12. The left rear chamber frame assembly 6 is fixed to the left side of the main rear chamber frame assembly 8, and the right rear chamber frame assembly 7 is fixed to the right side of the main rear chamber frame assembly 8. Both the door assembly 10 and the equipment door assembly 11 are rotatably connected to the rear side of the main rear chamber frame assembly 8. The door assembly 10 is used for daily training personnel and small equipment to enter and exit the simulation chamber, while the equipment door assembly 11 is used for large equipment such as the cockpit to enter and exit the simulation chamber. The two dome screen connecting angle assemblies 9 are connected to the left rear chamber frame assembly 6 and the right rear chamber frame assembly 7, respectively, and are also connected to the main rear chamber frame assembly 8, for the fixation of the rear chamber 4 to the screen 1. The step 12 is located directly below the door assembly and is used to connect to the boarding bridge deck. All of the above components are composed of metal frames and composite material skins.

[0025] The outer aesthetic component 5 has a skin made of carbon fiber honeycomb sandwich structure or glass fiber laminate structure, and the connectors are made of machined aluminum alloy angle rods. It is mainly used to shield the joints of the flanges of the curtain 1 and the top cover 2, as well as to shield the installation connectors between the dome structure components and the platform below, making the appearance smoother and more beautiful.

[0026] The dome screen in this invention will be installed and fixed above the motion platform of the full flight simulator, mainly to provide pilots with a high-definition visual scene, so that the pilots in the simulator can experience a more realistic flight effect.

[0027] See Figure 1 The diagram shown is a schematic representation of the dome screen structure according to Embodiment 1 of this utility model. It includes five main components: screen surface 1, top cover 2, projector bracket 3, rear chamber 4, and external aesthetic components 5.

[0028] See Figure 2 This is a schematic diagram of the rear chamber structure of Embodiment 1 of this utility model. It includes seven parts: the left side frame assembly 6, the right side frame assembly 7, the main frame assembly 8, the dome screen connecting angle assembly 9, the cabin door assembly 10, the equipment door assembly 11, and the pedal 12.

[0029] See Figure 3 , Figure 4 The figure shows the incident point diagram of the sound field surface and the static sound wave line characteristic analysis diagram of Embodiment 1 of this utility model. The figure shows that the sound field has good uniformity under a single reflection.

[0030] See Figure 5The diagram shown is an analysis of the pilot's eye-point field of view inside the dome-shaped cockpit of Embodiment 1 of this utility model. As can be seen from the diagram, the field of view angle of the dome structure's inner surface is not less than 300° horizontally and not less than 100° vertically.

[0031] See Figure 6 The diagram shown is a schematic of the finite element analysis model of the dome structure in Embodiment 1 of this utility model. Shell elements were used for finite element modeling and calculation of the structure, and cweld elements were used to simulate the fastener connections. The degrees of freedom of the dome and the bottom surface of the rear chamber were constrained. The strength, stability, stiffness, fatigue, and natural frequency under different load conditions (2.5g in each independent direction) were calculated and analyzed, all of which met the motion characteristic requirements of the simulator.

[0032] See Figure 7 The diagram shown is a schematic representation of the maximum deformation point of the dome structure in Embodiment 1 of this invention, calculated using finite element analysis. Under a longitudinal force of 2.5g, the maximum deformation at the projector bracket is approximately 0.95 mm, which meets the requirement of not exceeding 1 mm.

[0033] 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. Any design solution that is essentially formed by equivalent substitution should fall within the protection scope claimed by this application.

Claims

1. A lightweight full-flight simulator large dome screen, characterized in that, include: Screen, roof, projector bracket, rear building; A top cover is fixed above the screen; the projector bracket is fixed to the top cover, and multiple projector brackets are provided. The projector brackets pass through the surface of the top cover so that the projector can project onto the inner surface of the screen; the rear chamber is fixed to the rear of the screen and is mainly used to provide access for personnel and cabins, as well as space for equipment; the area below the screen and the area below the rear chamber are both fixed to the motion platform.

2. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, The rear chamber consists of a left-side frame assembly, a right-side frame assembly, a main frame assembly, dome-shaped connecting angle members, a door assembly, an equipment door assembly, and a step. The left and right-side frame assemblies are fixed to the left and right sides of the main frame assembly, respectively. The door assembly and the equipment door assembly are rotatably connected to the rear of the main frame assembly. The door assembly is used for trainees and equipment to enter and exit the simulation chamber, and the equipment door assembly is used for equipment to enter and exit the simulation chamber. The two dome-shaped connecting angle members are connected to the left-side and right-side frame assemblies, respectively, and are also connected to the main frame assembly, for the fixation of the rear chamber to the screen. The step is located directly below the door assembly and is used to connect to the boarding bridge deck.

3. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, The inner surface of the curtain is sprayed with water-based reflective paint, and the step difference and flatness are no more than two millimeters.

4. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, The curtain wall and the top cover are each composed of ten arc-shaped spherical pieces, each with a longitude angle of 36°, and all adopt a four-sided flanged skin structure.

5. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, There are four projector stands in total, arranged in pairs symmetrically on the left and right.

6. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, The inner and outer layers of the curtain and top cover are made of carbon fiber cloth, with a PMI foam interlayer in the middle.

7. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, The projector bracket is assembled from an aluminum alloy angle frame and carbon fiber skin.

8. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, The rear chamber adopts a structure in which an aluminum alloy frame is connected to a carbon fiber skin.

9. The lightweight full-flight simulator large dome screen according to claim 1, characterized in that, The height from the center of the top cover to the lower motion platform is six meters, with a field of view of 300 degrees horizontally and 100 degrees vertically.

10. The lightweight full-flight simulator large dome screen according to any one of claims 1-9, characterized in that, It also includes an outer aesthetic component, which is fixed to the outer surface of the curtain and the top cover. It is mainly used to cover the segmented flange joints of the curtain and the top cover, as well as the installation interface between the curtain, the rear chamber and the lower motion platform.

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