Main avionics instrument of aircraft, mounting seat of main avionics instrument and aircraft

Abstract

This utility model relates to the field of aircraft technology, providing a main avionics instrument for an aircraft, a mounting base for the main avionics instrument, and an aircraft. The main avionics instrument includes: an instrument panel frame with a mounting cavity; a mounting base fixed to the mounting cavity, the mounting base including a base and a support base, the base being fixed to the mounting cavity, the bottom of the support base being hinged to the base, and the upper part of the support base being fixedly connected to the base via a thermal actuator. The thermal actuator is equipped with an electric heating element, and the length of the thermal actuator changes with the operation of the electric heating element to adjust the angle between the base and the support base; and a display fixed to the support base. According to the embodiment of this application, the pilot can choose to turn the electric heater on or off as needed to adjust the length of the connecting rod, thereby improving ergonomics and flight safety. This main avionics instrument fundamentally improves flight safety, operational efficiency, and operational comfort.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a main avionics instrument for an aircraft, a mounting base for the main avionics instrument, and the aircraft itself. Background Technology

[0002] In modern aircraft, the cockpit's main avionics instruments integrate a large number of electronic display devices, such as the Primary Flight Display (PFD), Navigation Display (ND), and Engine Indication and Crew Warning System (EICAS). These displays are the primary channels for pilots to obtain flight status, navigation information, engine parameters, and warning information. The clarity, readability, and ease of crew operation of these displays directly affect flight safety and operational efficiency.

[0003] Currently, the vast majority of primary avionics instrument displays use a fixed mounting design. This means that the angle and position of the display are permanently set and fixed to the instrument panel frame at the factory. While this design is simple in structure, highly reliable, and meets the equipment stability requirements for airworthiness certification, it has gradually revealed significant limitations in actual operation, mainly in the following aspects:

[0004] First, there are glare and reflection issues caused by ambient light interference: The cockpit is a complex optical environment where sunlight, cabin lighting, runway lights, and other light sources can enter from different directions. A fixed-angle display screen acts like a fixed reflective surface, and during certain flight phases (such as turns, takeoff, and landing that cause changes in the angle of sunlight) or at the aircraft's parking position, it is highly susceptible to severe glare or specular reflection, causing the displayed content to appear partially or completely "white," making critical data (such as airspeed and altitude) momentarily unreadable. Pilots must adjust their attitude to avoid glare, a process that is extremely dangerous and should not occur during critical flight phases such as approach and landing.

[0005] Secondly, there's the issue of perspective problems caused by individual differences: different pilots have physiological differences such as height and posture. For a monitor with a fixed angle, what one pilot finds a comfortable viewing angle may require another pilot to frequently tilt their head down or up to see, easily leading to neck fatigue. During long flights or under heavy workloads, this ergonomic deficiency can exacerbate pilots' physiological fatigue, distract their attention, and potentially affect flight safety. Utility Model Content

[0006] This utility model provides a main avionics instrument for an aircraft, a mounting base for the main avionics instrument, and an aircraft, in order to solve the problems of glare and reflection of the display caused by ambient light interference in the prior art, as well as the viewing angle problem caused by the main avionics instrument's inability to adapt to individual differences.

[0007] This utility model provides a main avionics instrument for an aircraft, including:

[0008] The dashboard frame has mounting cavities.

[0009] A mounting base is fixed to the mounting cavity. The mounting base includes a base and a support base. The base is fixed to the mounting cavity. The bottom of the support base is hinged to the base. The upper part of the support base is fixedly connected to the base via a thermal actuator. The thermal actuator is provided with an electric heating element. The length of the thermal actuator changes with the operation of the electric heating element to adjust the angle between the base and the support base.

[0010] The display is fixed to the support base.

[0011] According to an embodiment of the present invention, the thermal actuator is a connecting rod with a hollow channel, the electric heating element is a spiral heating wire, the spiral heating wire is fixedly installed in the hollow channel, and the spiral heating wire is in contact with the inner surface of the hollow channel.

[0012] According to an embodiment of the present invention, a flow cavity is formed inside the base, an air inlet communicating with the flow cavity is formed on the top plate of the base facing the support, and a fan is provided at the air inlet, and an air outlet communicating with the flow cavity is formed on the side plate of the base.

[0013] According to an embodiment of the present invention, the support base has heat dissipation holes, and the air-facing surface of the fan faces the heat dissipation holes.

[0014] According to an embodiment of the present invention, the support base is provided with a plurality of elastic columns, the display is fixed to the support base and abuts against the elastic columns to form a wind cavity on the back of the support base and the display, the wind cavity being connected to the heat dissipation hole.

[0015] According to an embodiment of the present invention, a wiring space is formed in the flow cavity, and a wiring hole is formed in the surrounding plate of the base to communicate with the wiring space.

[0016] According to an embodiment of the present invention, the support base includes a support plate and guide rails, the guide rails being distributed on opposite sides of the support plate.

[0017] According to an embodiment of this utility model, the guide rail is provided with a plurality of adjusting threaded holes.

[0018] And / or,

[0019] The support plate is provided with several adjusting threaded holes.

[0020] And / or,

[0021] The top end of the thermal actuator is fixed to the support base via a connecting plate, and the bottom end of the thermal actuator is fixed to the base via another connecting plate.

[0022] And / or,

[0023] The number of thermal actuators is multiple.

[0024] This utility model provides a mounting base for main avionics instruments, comprising:

[0025] A base for securing the instrument panel frame into the mounting cavity.

[0026] The support base is hinged to the base at its bottom, and the upper part of the support base is fixedly connected to the base via a thermal actuator. The thermal actuator is equipped with an electric heating element, and the length of the thermal actuator changes with the operation of the electric heating element to adjust the angle between the base and the support base.

[0027] This utility model provides an aircraft, including a cockpit, in which the main avionics instruments of the aircraft are installed.

[0028] The main avionics instrument for aircraft provided by this utility model allows pilots to choose to turn the electric heater on or off as needed, thereby adjusting the length of the connecting rod and improving ergonomics and flight safety. Specifically, firstly, it allows pilots to precisely adjust their viewing angle according to their height and posture preferences, ensuring the optimal angle between their line of sight and the display for best display clarity and color contrast, greatly reducing neck and visual fatigue during long flights. This main avionics instrument enhances individual adaptability, enabling pilots of different body types to quickly achieve their personalized optimal working environment, shortening adaptation time and improving operational comfort. Secondly, this main avionics instrument can be used to actively eliminate ambient light interference. Pilots can fine-tune the angle in real time to avoid glare and reflections caused by sunlight and cabin lighting, ensuring that critical flight data (such as airspeed and altitude) remain visible under complex lighting conditions, which is crucial for critical phases such as approach and landing. Therefore, the main avionics instrument of this application embodiment fundamentally improves flight safety, operational efficiency, and operational comfort. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0030] Figure 1 This is a structural schematic diagram of the aircraft provided by this utility model.

[0031] Figure 2 yes Figure 1 A magnified view of a portion of point A in the middle.

[0032] Figure 3 This is one of the structural schematic diagrams of the mounting base provided by this utility model.

[0033] Figure 4 This is the second structural schematic diagram of the mounting base provided by this utility model.

[0034] Figure 5 This is the third structural schematic diagram of the mounting base provided by this utility model.

[0035] Figure 6 This is the fourth structural schematic diagram of the mounting base provided by this utility model.

[0036] Figure label:

[0037] 100. Cockpit; 200. Main avionics instruments; 210. Instrument panel frame; 220. Mounting bracket; 221. Base; 2210. Flow chamber; 2211. Air inlet; 2212. Air outlet; 2213. Fan; 2214. Cable routing hole; 222. Support base; 2221. Heat dissipation hole; 2222. Elastic column; 2223. Guide rail; 2224. Support plate; 2225. Adjusting threaded hole; 2226. Adjusting bolt; 223. Thermal actuator; 224. Electric heating element; 225. Connecting plate; 2251. Connector; 230. Display. Detailed Implementation

[0038] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0039] The following is combined with Figures 1-6 This invention describes the main avionics instruments of an aircraft, the mounting base for the main avionics instruments, and the aircraft itself.

[0040] Please see Figure 1 and Figure 2The cockpit 100 of the aircraft is equipped with the main avionics instrument 200. The main avionics instrument 200 is the core area for flight information display and interaction, located directly in front of the pilot's line of sight. Its core function is to centrally integrate and present in real time the most critical flight parameters, such as attitude, airspeed, altitude, heading, and engine status, providing the pilot with a comprehensive flight situational awareness without significantly shifting their gaze. The clarity, reliability, and ergonomics of this area directly affect the accuracy of flight decisions and flight safety, making it the most crucial component of the cockpit 100's human-machine interface.

[0041] In most existing aircraft cockpits 100, the angle and position of the display 230 are permanently set and fixed to the instrument panel frame 210 of the main avionics instrument 200 at the factory. This results in glare and reflection problems caused by ambient light interference, as well as viewing angle problems due to individual differences. The display 230 here can be, but is not limited to, the main flight display, navigation display, engine indication and crew warning system, etc. It should be understood that the display in this embodiment can be any display included in the main avionics instruments of the prior art.

[0042] Based on this, this application proposes a main avionics instrument 200 for an aircraft (hereinafter referred to as the main avionics instrument 200), which includes an instrument panel frame 210 and a display 230, as well as a mounting base 220 specially designed in this application. The structure of the mounting base 220 is referenced. Figures 3 to 6 .

[0043] According to an embodiment of this application, the instrument panel frame 210 is the core load-bearing and mounting structure of the main avionics instrument 200, and can be made of high-strength lightweight alloy or composite material. Its main function is to accurately and securely mount various displays 230 and control switches, and to provide routing channels for their internal cables. The instrument panel frame 210 has mounting cavities for various displays 230, and any display 230 can be fixed to the mounting cavity by the mounting seat 220 of this embodiment.

[0044] The mounting base 220 in this embodiment of the application refers to... Figure 3 and Figure 4The system includes a base 221 and a support 222. The base 221 is fixed to the mounting cavity, and the bottom of the support 222 is hinged to the base 221, allowing the support 222 to rotate around the base 221. The upper part of the support 222 is fixedly connected to the base 221 via a thermal actuator 223. The thermal actuator 223 is equipped with an electric heating element 224, and the length of the thermal actuator 223 changes with the operation of the electric heating element 224 to adjust the angle between the base 221 and the support 222. Here, "the upper part of the support 222" is relative to "the bottom of the support 222," and it is sufficient that the connection position between the thermal actuator 223 and the support 222 is located at the hinge point between the support 222 and the base 221.

[0045] Therefore, when the electric heating element 224 is not turned on, the thermal actuator 223 has an initial length, and the angle between the base 221 and the support 222 is the initial angle. When the electric heating element 224 is turned on, the length of the thermal actuator 223 changes as the electric heating element 224 is turned on.

[0046] According to the main avionics instrument 200 of the aircraft in this application embodiment, the pilot can choose to turn the electric heater on or off as needed to adjust the length of the connecting rod, thereby improving ergonomics and flight safety. Specifically, firstly, it allows the pilot to precisely adjust the viewing angle according to their height and posture preference, ensuring that the line of sight is at the optimal angle with the display 230, obtaining the best display clarity and color contrast, and greatly reducing neck and visual fatigue during long-term flights. This main avionics instrument 200 enhances individual adaptability, enabling pilots of different body types to quickly obtain a personalized optimal working environment, shortening adaptation time and improving operational comfort. Secondly, this main avionics instrument 200 can be used to actively eliminate ambient light interference. The pilot can fine-tune the angle in real time to avoid glare and reflections caused by sunlight and cabin lighting, ensuring that critical flight data (such as airspeed and altitude) remain visible under complex lighting conditions, which is crucial for critical phases such as approach and landing. Therefore, the main avionics instrument 200 in this application embodiment fundamentally improves flight safety, operational efficiency, and operational comfort.

[0047] According to embodiments of this application, in conjunction with Figures 3 to 6The thermal actuator 223 can be a connecting rod made of a thermosensitive material. For example, the connecting rod can be made of shape memory alloy or other thermosensitive materials with a certain rigidity at room temperature. Utilizing the thermal expansion and contraction or phase change characteristics of the thermosensitive material, the length of the connecting rod will change when it is heated / cooled, thereby driving the support 222 to rotate relative to the base 221. Alternatively, the thermal actuator 223 can also be a brake piston made of thermosensitive wax. Specifically, the thermal actuator 223 includes a piston rod and a sealed cylinder. The sealed cylinder is filled with paraffin wax. One end of the piston rod extends into the sealed cylinder, and the other end is fixed to the support 222. The sealed cylinder is fixed to the base 221. The electric heating element 224 is used to heat the sealed cylinder to heat the paraffin wax. When the paraffin wax melts and expands due to heat, it pushes the piston rod to extend out of the sealed cylinder. There is a return spring between the piston rod and the sealed cylinder. When the electric heating element 224 is de-energized, the paraffin wax contracts and solidifies, and the return spring causes the piston rod to contract. Of course, the specific structure and type of the thermal actuator 223 are not limited. For example, it can be a wax actuator, a bimetallic actuator, or a shape memory alloy actuator, as long as it can drive the support 222 to adjust the angle.

[0048] When a shape memory alloy is used for the connecting rod, it can be made from an alloy with an austenitic transformation critical temperature between 30℃ and 40℃. Therefore, when the temperature of the connecting rod is below the critical temperature, it maintains its initial length. When the temperature of the connecting rod reaches the critical temperature, an austenitic transformation occurs, and the length of the connecting rod begins to change. However, the relationship between the length of the connecting rod and its temperature (the temperature after the austenitic transformation) is not necessarily linear.

[0049] In one embodiment, the thermal actuator 223 is made of Ti-Ni shape memory alloy, with an austenitic transformation temperature of 35℃±2℃ and a martensitic transformation temperature of 25℃±2℃. Within the temperature range of 20℃-50℃, the length change rate is 3%-5%, corresponding to an angle adjustment range of 0°-25°, so that the included angle between the support 222 and the horizontal base plate of the aircraft (the base 221 is generally horizontally positioned inside the aircraft; however, the base 221 can also be positioned at other angles) is between 60° and 85°. For example, at 20℃, the length of thermal actuator 223 is L0, corresponding to a display tilt angle (the display tilt angle is also the angle between the display and the horizontal base plate of the aircraft) of 60°; at 28℃, the length of thermal actuator 223 is L0×1.01, corresponding to a display tilt angle of 65°; at 35℃, the length of thermal actuator 223 is L0×1.025, corresponding to a display tilt angle of 70°; at 42℃, the length of thermal actuator 223 is L0×1.04, corresponding to a display tilt angle of 77°; at 50℃, the length of thermal actuator 223 is L0×1.05, corresponding to a display tilt angle of 85°. The value of L0 can range from 100mm to 150mm, depending on the installation space. For example, L0 can be selected as 100mm, 125mm, or 150mm. In other embodiments, the thermal actuator 223 may also be: Cu-Zn-Al shape memory alloy with a phase transition temperature range of 30°C-45°C; or Fe-Mn-Si shape memory alloy with a phase transition temperature range of 25°C-40°C.

[0050] In one embodiment, the response time of the thermal actuator 223 is less than 30 seconds. The electric heating element 224 precisely controls the heating power through a PWM (Pulse Width Modulation) controller, which automatically adjusts the angle of the support base 222 according to a preset temperature-angle correspondence table. The PWM controller can be configured with a working frequency of 1kHz-10kHz, a duty cycle adjustment range of 0-100%, and an adjustment accuracy of 1%. When rapid heating is required, the duty cycle is set to 80%-100%; when approaching the target temperature, the duty cycle is reduced to 20%-40% for fine adjustment. The electric heating element 224 or the thermal actuator 223 is equipped with a temperature sensor, which has a sampling frequency of 10Hz and a control accuracy of ±0.5℃.

[0051] The PWM controller described above may also include a safety protection module that automatically cuts off the power supply to the electric heating element 224 when the following conditions are detected: the temperature of the thermal actuator 223 exceeds 55°C; or the angle sensor detects that the tilt angle of the support 222 exceeds 88°; or the continuous heating time exceeds 5 minutes; or the temperature rise rate exceeds 5°C / minute. After the electric heating element 224 is de-energized, the thermal actuator 223 cools naturally, and the support 222 slowly recovers under gravity.

[0052] According to an embodiment of this application, the pilot can input the desired angle of the support 222 relative to the horizontal base of the aircraft via a display 230. The PWM controller controls the electric heating element 224 based on the desired angle to adjust the angle of the support 222.

[0053] Please see Figure 3 The connecting rod is hollow to form a hollow channel, and the electric heating element 224 is disposed within the hollow channel. In this case, the connecting rod itself encloses the heating element, which ensures heating efficiency and prevents the electric heating element 224 from affecting the temperature of other external components (e.g., preventing it from affecting the temperature of the display 230). Of course, to further prevent the electric heating element 224 from affecting other components besides the connecting rod, a heat insulation cover can also be installed on the outside of the connecting rod.

[0054] The electric heating element 224 can be a spiral heating wire, which is fixedly installed inside the hollow channel and fits snugly against the inner surface of the hollow channel. In this case, the contact area between the electric heating element 224 and the connecting rod is large, which can further ensure heating efficiency. Of course, the electric heating element 224 can also adopt other structural forms and fixing methods. For example, the electric heating element 224 can also be a heating wire wound around the outer surface of the connecting rod; or, for example, the electric heating element 224 can also be an electric heating plate fixed to the connecting rod, etc.

[0055] Please see Figure 5 The base 221 has a flow cavity 2210 inside, and the top plate of the base 221 facing the support 222 has an air inlet 2211 that communicates with the flow cavity 2210. A fan 2213 is installed at the air inlet 2211, and the side plate of the base 221 has an air outlet 2212 that communicates with the flow cavity 2210. In this case, the monitor 230 can be air-cooled by the fan 2213 and the flow cavity 2210 to ensure the heat dissipation effect of the monitor 230. Figure 5 In the middle, multiple side plates of the base 221 are formed with air outlets 2212. Of course, air outlets 2212 can also be formed on any one or more side plates.

[0056] Figure 3 and Figure 5 In the middle, the support base 222 has heat dissipation holes 2221, and the air-facing surface of the fan 2213 faces the heat dissipation holes 2221. Through the setting of the heat dissipation holes 2221, the airflow generated by the fan 2213 can directly act on the display 230 through the heat dissipation holes 2221 to enhance the heat dissipation effect.

[0057] Figure 4In this design, a plurality of elastic posts 2222 are provided on the support plate 2224. The display 230 is fixed to the support plate 2224 and abuts against the elastic posts 2222, so as to form an air cavity on the back of the support plate 2224 and the display 230. The air cavity is connected to the heat dissipation hole 2221. Obviously, the formation of the air cavity can further ensure that the airflow fully contacts the display 230.

[0058] Figure 5 In the middle, a wiring space is formed in the flow cavity 2210, and a wiring hole 2214 is formed in the surrounding plate of the base 221 to connect the wiring space. At this time, the cable is arranged in the base 221, which can effectively separate it from the electric heating element 224, and can also fully expose the cable to the cooling airflow of the fan 2213 to ensure that the cable is at a low temperature.

[0059] Combination Figure 4 The support base 222 includes a support plate 2224 and guide rails 2223, with the guide rails 2223 distributed on opposite sides of the support plate 2224. Therefore, this support base 222 can be adapted to various models of displays 230, as long as the display 230 can be installed between two guide rails 2223. The guide rails 2223 can be located on the upper and lower sides of the support base 222, or on the left and right sides of the support base 222.

[0060] Combination Figures 3 to 6 The guide rail 2223 has several adjusting threaded holes 2225. By adjusting the threaded holes 2225, the versatility of the mounting base 220 can be further improved. Specifically, even if the monitor 230 is slidably installed onto the support base 222 along the guide rail 2223 and there is a gap between the monitor 230 and the guide rail 2223, it will not affect the fixation of the monitor 230. Simply tighten the adjusting bolt 2226 to the monitor 230 through the adjusting bolt 2226 hole.

[0061] Similarly, the support plate 2224 has several adjusting threaded holes 2225, which can allow displays 230 of different thicknesses to be fixed to the mounting base 220. Specifically, when the display 230 is thinner, the adjusting bolts 2226 can be tightened to the back of the display 230 through the adjusting bolt holes 2226.

[0062] According to the embodiments of this application, please refer to Figure 3 and Figure 6 The top end of the thermal actuator 223 is fixed to the support base 222 via a connecting plate 225, and the bottom end of the thermal actuator 223 is fixed to the base 221 via another connecting plate 225, thereby improving the structural stability of the connection position. (Refer to...) Figure 6When the thermal actuator 223 is a connecting rod, considering that the cross-sectional dimensions of the connecting rod may also change, a connector 2251 can be provided on the connecting plate 225, and both ends of the connecting rod are inserted into the connector 2251. The diameter of the insertion hole of the connector 2251 is larger than the diameter of the connecting rod to ensure that the connector 2251 will not be expanded by the connecting rod when the connecting rod is heated.

[0063] Figure 6 In order to prevent the temperature of the electric heating element 224 from affecting the temperature of the display 230, the electric heating element 224 can be installed only on the lower half of the connecting rod. Alternatively, in order to prevent the temperature of the electric heating element 224 from affecting the temperature of the display 230 and the temperature of the base 221, the electric heating element 224 can be installed only at the middle of the connecting rod.

[0064] According to an embodiment of this application, a mounting base 220 for a main avionics instrument is provided, including a base 221 and a support 222. The base 221 is fixed to a mounting cavity formed by an instrument panel frame 210; the bottom of the support 222 is hinged to the base 221, and the upper part of the support 222 is fixedly connected to the base 221 via a thermal actuator 223. The thermal actuator 223 is provided with an electric heating element 224, and the length of the thermal actuator 223 changes with the operation of the electric heating element 224 to adjust the angle between the base 221 and the support 222.

[0065] According to an embodiment of this application, an aircraft is provided, including a cockpit 100, in which the main avionics instruments 200 of the ascending aircraft are disposed.

[0066] It should be noted that the contents of the main avionics instrument 200 of the aircraft in the above embodiments can be used to explain the mounting base 220 of the main avionics instrument 200 and the aircraft in the embodiments of this application, so the same contents will not be repeated.

[0067] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model 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 of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A primary flight instrument for an aircraft, characterized in that, include: The instrument panel frame (210) has a mounting cavity; Mounting base (220) is fixed in the mounting cavity. Mounting base (220) includes base (221) and support base (222). Base (221) is fixed in the mounting cavity. The bottom of support base (222) is hinged to base (221). The upper part of support base (222) is fixedly connected to base (221) through thermal actuator (223). Thermal actuator (223) is provided with electric heating element (224). The length of thermal actuator (223) changes with the operation of electric heating element (224) to adjust the angle between base (221) and support base (222). The display (230) is fixed to the support base (222).

2. The primary flight instrument of claim 1, wherein, The thermal actuator (223) is a connecting rod with a hollow channel, and the electric heating element (224) is a spiral heating wire. The spiral heating wire is fixedly installed in the hollow channel, and the spiral heating wire is in contact with the inner surface of the hollow channel.

3. The primary flight instrument of claim 1, wherein, The base (221) has a flow cavity (2210) inside. The top plate of the base (221) facing the support (222) has an air inlet (2211) that communicates with the flow cavity (2210). A fan (2213) is provided at the air inlet (2211). The side plate of the base (221) has an air outlet (2212) that communicates with the flow cavity (2210).

4. The primary flight instruments of claim 3, wherein, The support base (222) has heat dissipation holes (2221), and the windward side of the fan (2213) faces the heat dissipation holes (2221).

5. The primary flight instrument of claim 4, wherein, The support base (222) is provided with a plurality of elastic columns (2222). The display (230) is fixed to the support base (222) and abuts against the elastic columns (2222) to form a wind cavity on the back of the support base (222) and the display (230). The wind cavity is connected to the heat dissipation hole (2221).

6. The primary flight instrument of claim 3, wherein, A wiring space is formed inside the flow cavity (2210), and a wiring hole (2214) is formed in the surrounding plate of the base (221) to connect the wiring space.

7. Master avionics instrument of an aircraft according to any one of claims 1 to 6, characterized in that The support base (222) includes a support plate (2224) and a guide rail (2223), the guide rail (2223) being distributed on opposite sides of the support plate (2224).

8. The primary flight instrument of claim 7, wherein, The guide rail (2223) is provided with several adjusting threaded holes (2225). And / or, The support plate (2224) is provided with several adjusting threaded holes (2225). And / or, The top end of the thermal actuator (223) is fixed to the support base (222) by a connecting plate (225), and the bottom end of the thermal actuator (223) is fixed to the base (221) by another connecting plate (225). And / or, The number of thermal actuators (223) is multiple.

9. A mounting for a primary flight instrument, characterised in that, include: A base (221) is used to secure the instrument panel frame (210) into the mounting cavity; The support base (222) is hinged at the bottom to the base (221). The upper part of the support base (222) is fixedly connected to the base (221) by a thermal actuator (223). The thermal actuator (223) is provided with an electric heating element (224). The length of the thermal actuator (223) changes with the operation of the electric heating element (224) to adjust the angle between the base (221) and the support base (222).

10. An aircraft, characterized in that Includes a cockpit (100), wherein the cockpit (100) is provided with the main avionics instruments (200) of the aircraft as described in any one of claims 1 to 9.

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