High-stability autonomous safety control device for manned aircraft

Abstract

The invention relates to the technical field of manned aircrafts, in particular to a high-stability manned aircraft autonomous safety control device which comprises a controller body, the controller body is conveyed into the autonomous safety control device in an airflow mode, internal elements in the autonomous safety control device are heated, and the temperature of the internal elements in the autonomous safety control device is controlled. The influence of a low-temperature environment on internal elements in the autonomous safety control device can be reduced, when the inlet air temperature is too high, the air inlet communicated with the outside can be opened through the control valve arranged on the air inlet pipe, a proper amount of cold air is introduced from the outside, it is ensured that the internal elements in the autonomous safety control device are in a proper temperature environment, and the safety of the autonomous safety control device is improved. Hot air flow in the air inlet pipe and cold air flow entering from the air inlet are filtered through the filter screen, impurities and dust are prevented from entering the autonomous safety control device, the dustproof head can extrude and abut against the wiring plug, and therefore the wiring plug is not prone to loosening and falling off from the wiring jack, and the wiring stability is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of manned aircraft, and in particular to an autonomous safety control device for a manned aircraft with high stability. Background Art

[0002] The autonomous safety control device of manned aircraft is a key system to ensure the safe and stable operation of the aircraft during flight.

[0003] The autonomous safety control device of a manned aircraft refers to a device that can autonomously monitor the flight status, judge flight safety, and take corresponding measures to ensure flight safety when necessary during the flight. Its main functions include real-time monitoring: real-time monitoring of the flight parameters of the aircraft, such as speed, altitude, attitude, etc.; safety judgment: comparing the real-time monitored flight parameters with the preset safety threshold to determine whether the aircraft is in a safe state; emergency control: when the aircraft deviates from the safe state, the autonomous safety control device can quickly take measures, such as adjusting the flight attitude, decelerating, landing, etc., to ensure flight safety.

[0004] Generally speaking, the flight altitude of civil manned aircraft is below 3,000 meters, and some special applications may reach 4,000 to 5,000 meters. As the flight altitude increases, the air pressure gradually decreases and the temperature will gradually drop. At an altitude of 5,000 meters, the air temperature is about minus 15 degrees Celsius. When a manned aircraft flies at this temperature, the aerodynamic performance and sensor accuracy of the aircraft may be affected, thereby affecting the flight stability. Summary of the invention

[0005] In view of the above-mentioned shortcomings of the prior art, the present invention provides a highly stable autonomous safety control device for a manned aircraft, which can effectively solve the problem of the inconvenience of using the prior art.

[0006] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0007] The present invention provides a highly stable autonomous safety control device for a manned aircraft, comprising a controller body, wherein an air inlet is provided on the top of the controller body, and a plurality of wiring jacks are provided on the side wall, an air inlet temperature adjustment component comprises an air inlet seat installed on the top of the controller body and connected with the air inlet, a control valve is installed at the connection between the air inlet seat and the air inlet, an air inlet pipe is installed on the top of the air inlet seat, a temperature sensor is also installed in the air inlet pipe, a filter component is detachably installed at the connection between the control valve and the air inlet, a reinforced dustproof component comprises a reinforced seat fixedly installed at one end of the controller body, an active cavity is provided in the reinforced seat, a plurality of wiring holes are provided on both sides of the reinforced seat that penetrate the active cavity and are respectively opposite to the positions of the corresponding wiring jacks, two mounting strips that can be raised and lowered in reverse are arranged in the active cavity, and dustproof blocks that can be sealed in the corresponding wiring holes are elastically installed on the far side of the two mounting strips.

[0008] Furthermore, mounting blocks are vertically fixedly installed at the four corners of the controller body, screws are threadedly installed on the four mounting blocks, and a wiring cable extending into the interior is installed at one end of the controller body.

[0009] Furthermore, an air inlet cavity is provided at the bottom of the air inlet seat, and air inlets are provided around the air inlet seat and penetrate the air inlet cavity. Filters are embedded in several of the air inlets and are adaptively installed. The control valve is installed in the air inlet cavity and is designed to be adaptive to the inner wall of the air inlet cavity. Installation openings are provided on two opposite outer walls of the air inlet seat and penetrate the air inlet cavity.

[0010] Furthermore, the filter assembly includes a filter box that is adaptably inserted into the two mounting ports at the same time, a stopper is fixedly installed at one end of the filter box, and the outer wall of the air inlet seat is also installed with two magnetic sheets respectively arranged around the mounting port, and the stopper is magnetically adsorbed and fixed to the two magnetic sheets close to one side of the filter box.

[0011] Furthermore, the inner cavity of the air inlet pipe is connected to the air inlet cavity, a threaded joint is installed on the top of the air inlet pipe, the temperature sensor is installed on the outer wall of the air inlet pipe, and the internal detection probe extends into the inner cavity of the air inlet pipe.

[0012] Furthermore, a driving seat is fixedly installed at one end of the reinforcement seat, a knob is rotatably installed on the top of the driving seat, the driving seat is hollow in design, and a worm and worm wheel that mesh with each other are rotatably installed inside, wherein the top of the worm is fixedly connected to the bottom of the knob, and a first transmission wheel is fixedly installed on one side of the worm wheel.

[0013] Furthermore, a transmission assembly is also arranged in the movable cavity, and the transmission assembly comprises a second transmission wheel rotatably mounted in the movable cavity, and a transmission belt is arranged between the second transmission wheel and the first transmission wheel.

[0014] Furthermore, a gear is fixedly mounted on one side of the second transmission wheel, and two racks are meshingly mounted around the gear and are lifted and slidably mounted in the movable cavity. The two racks have the same specifications and are symmetrically distributed about the center of the gear.

[0015] Furthermore, the two mounting bars are respectively vertically fixedly connected to the corresponding racks, and the two mounting bars are both lifted and slidably installed in the movable cavity between the two rows of wiring holes.

[0016] Furthermore, several of the dust blocks are provided with an arc groove at one end away from the corresponding mounting strip, the curvature of the arc groove is consistent with the curvature of the wiring hole, and two symmetrically distributed springs are installed between several of the dust blocks and the corresponding mounting strips.

[0017] Compared with the known prior art, the technical solution provided by the present invention has the following beneficial effects:

[0018] 1. The present invention takes into account that the internal components of the autonomous safety control device may be affected by the low temperature and reduce power or even stop working when the manned aircraft is in a high-altitude low-temperature state. Therefore, under the premise that no independent insulation measures are set for the internal components of the autonomous safety control device, the heat generated by the drive motor that drives the propeller of the manned aircraft to rotate at high speed is transported to the autonomous safety control device through the air inlet pipe in the form of airflow, and the internal components of the autonomous safety control device are heated, which can reduce the impact of the low-temperature environment on the internal components of the autonomous safety control device, and has the characteristics of energy saving and environmental protection;

[0019] 2. At the same time, a temperature sensor is set in the air inlet pipe to detect the air inlet temperature in real time. When the air inlet temperature is too high, the air inlet connected to the outside world can be opened through the control valve set on the air inlet pipe to introduce a proper amount of cold air from the outside world. After mixing with the hot air in the air inlet pipe, the cold air enters the autonomous safety control device at a suitable temperature state, ensuring that the internal components in the autonomous safety control device are in a suitable temperature environment;

[0020] 3. A filter is set on the road connecting the air inlet pipe and the autonomous safety control device. The filter is used to filter the hot air flow in the air inlet pipe and the cold air flow entering the air inlet to prevent impurities and dust from entering the autonomous safety control device and affecting the normal operation of electronic components. At the same time, the filter adopts a magnetic detachable installation method, which can easily remove the filter to clean the dust and impurities filtered on the surface;

[0021] 4. A reinforcement seat is installed at the position of the wiring jack at one end of the autonomous safety control device. The reinforcement seat is provided with a plurality of wiring holes for convenient insertion of the wiring head, and a plurality of dust-proof blocks that can be telescopically slid are arranged in the wiring hole. When the wiring plug is inserted into the wiring hole and finally connected to the corresponding wiring jack, the dust-proof head can squeeze and resist the wiring plug, so that the wiring plug is not easy to loosen and fall off from the wiring jack, thereby improving the stability of the wiring. At the same time, for the wiring hole that has not yet been inserted with the wiring plug, the dust-proof head can directly cover most of the opening of the wiring hole, thereby preventing large particles of foreign matter from directly entering the corresponding wiring jack from the wiring hole, and also preventing the wiring plug from having poor contact the next time it is inserted into the wiring jack;

[0022] 5. The hot air flow entering the autonomous safety control device is finally discharged through the wiring jack into which the wiring plug has not been inserted. It can be discharged from the small gap between the dustproof head and the wiring port for a long time through the airflow, further preventing dust and impurities from contaminating the wiring jack. At the same time, due to the reduction of the wiring port opening, the flow rate of the airflow discharged from the small gap between the dustproof head and the wiring port will also increase, further improving the dustproof effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the prior art descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0024] Figure 1 It is a schematic diagram of the overall first-view structure of the present invention;

[0025] Figure 2 It is a schematic diagram of the overall second viewing angle structure of the present invention;

[0026] Figure 3 It is a schematic diagram of the overall installation structure of the air inlet seat of the present invention;

[0027] Figure 4 It is a schematic diagram of the disassembled structure of the air inlet seat parts of the present invention;

[0028] Figure 5 It is a schematic diagram of the reinforcement seat structure of the present invention;

[0029] Figure 6 It is a schematic diagram of the installation structure of the transmission assembly of the present invention;

[0030] Figure 7 It is a schematic diagram of the transmission assembly structure of the present invention;

[0031] Figure 8 For the present invention Figure 7Enlarged structural diagram at A in the middle.

[0032] The numbers in the figure represent:

[0033] 1. Controller body; 11. Mounting block; 12. Screws;

[0034] 2. Air inlet seat; 21. Air inlet; 22. Filter; 23. Control valve; 24. Mounting port; 25. Magnetic sheet; 26. Filter box; 27. Stopper; 28. Air inlet pipe; 29. ​​Threaded joint; 210. Temperature sensor;

[0035] 3. Reinforcement seat; 31. Movable cavity; 32. Wiring hole; 33. Drive seat; 34. Knob; 35. Worm; 36. Worm wheel; 37. First transmission wheel; 38. Second transmission wheel; 39. Transmission belt; 310. Gear; 311. Rack; 312. Mounting strip; 313. Dust block; 314. Spring. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0037] The present invention will be further described below in conjunction with the embodiments.

[0038] Embodiment 1:

[0039] Reference Figure 1-8 , which is the first embodiment of the present invention, a highly stable manned aircraft autonomous safety control device, including a controller body 1, which is usually composed of a flight control system, a navigation system, a sensor system, an actuator and a safety self-destruction device, wherein the flight control system is responsible for real-time acquisition of flight status data measured by various sensors, receiving control commands and data from a ground measurement and control station, and outputting control commands to the actuator after calculation and processing, so as to achieve stable flight and autonomous control of the aircraft, the flight control system can monitor key parameters such as the attitude, speed, and altitude of the aircraft, and automatically adjust the parameters when they deviate from a safe range, the navigation system provides accurate navigation information for the aircraft, including position, speed, heading, etc., the navigation system usually includes a GPS receiver, an inertial navigation system (I NS), etc., which can ensure that the aircraft flies accurately in a complex environment, the sensor system includes a gyroscope, an accelerometer, a barometer, a temperature sensor and other sensors, which are used to monitor various status parameters of the aircraft in real time, and these sensor data are important bases for the flight control system to make decisions and control;

[0040] An air inlet is provided at the top of the controller body 1, and a plurality of wiring jacks are provided on the side wall. The air inlet temperature adjustment component includes an air inlet seat 2 installed at the top of the controller body 1 and connected to the air inlet, a control valve 23 is installed at the connection between the air inlet seat 2 and the air inlet, an air inlet pipe 28 is installed at the top of the air inlet seat 2, a temperature sensor 210 is also installed in the air inlet pipe 28, and a filter component is detachably installed at the connection between the control valve 23 and the air inlet;

[0041] The reinforced dustproof component includes a reinforcement base 3 fixedly installed at one end of the controller body 1, and an active cavity 31 is opened in the reinforcement base 3. A plurality of wiring holes 32 corresponding to the corresponding wiring jacks are opened on both sides of the reinforcement base 3 through the active cavity 31. Two mounting strips 312 that can be raised and lowered in reverse are arranged in the active cavity 31. Dustproof blocks 313 that can be sealed in the corresponding wiring holes 32 are elastically installed on the far side of the two mounting strips 312. The end of the dustproof block 313 is designed to be arc-shaped, which is convenient for just clamping the wiring plug, increasing the contact area between the wiring plug and the wiring plug, and improving the plug-in stability of the wiring plug.

[0042] Embodiment 2:

[0043] Reference Figure 3-4 , which is the second embodiment of the present invention, and this embodiment is different from the first embodiment in that: mounting blocks 11 are vertically fixedly installed at the four corners of the controller body 1, and screws 12 are threadedly installed on the four mounting blocks 11, and a wiring cable extending into the interior is installed at one end of the controller body 1, and an air inlet cavity is opened at the bottom of the air inlet seat 2, and air inlets 21 are opened around the air inlet seat 2 to penetrate the air inlet cavity, and filters 22 are embedded in a plurality of air inlets 21 to be installed in a matching manner, and a control valve 23 is installed in the air inlet cavity and is designed to match the inner wall of the air inlet cavity, and an air inlet pipe 28 directly penetrates the control valve 23 and extends into the air inlet cavity, so the switch size of the control valve 23 only controls the capacity of cold air coming from the air inlet 21;

[0044] The two opposite outer walls of the air inlet seat 2 are both penetrated by the air inlet cavity to form installation openings 24. The filter assembly includes a filter box 26 that is adapted to be inserted into the two installation openings 24 at the same time. A block 27 is fixedly installed at one end of the filter box 26. The outer wall of the air inlet seat 2 is also equipped with two magnetic sheets 25 respectively arranged around the installation openings 24. The block 27 is magnetically adsorbed and fixed to the two magnetic sheets 25 near the side of the filter box 26. The inner cavity of the air inlet pipe 28 is connected to the air inlet cavity. A threaded joint 29 is installed on the top of the air inlet pipe 28. The temperature sensor 210 is installed on the outer wall of the air inlet pipe 28, and the internal detection probe extends into the inner cavity of the air inlet pipe 28. Therefore, the hot air temperature in the air inlet pipe 28 can be monitored in real time.

[0045] The remaining structures are the same as those of Example 1.

[0046] Embodiment 3:

[0047] Reference Figure 5-7 , which is the third embodiment of the present invention, and this embodiment is different from the second embodiment in that: a driving seat 33 is fixedly installed at one end of the reinforcement seat 3, a knob 34 is rotatably installed on the top of the driving seat 33, the driving seat 33 is hollow in design, and a worm 35 and a worm wheel 36 that mesh with each other are rotatably installed inside, wherein the top of the worm 35 is fixedly connected to the bottom of the knob 34, a first transmission wheel 37 is fixedly installed on one side of the worm wheel 36, and a transmission component is also arranged in the movable cavity 31;

[0048] The transmission assembly includes a second transmission wheel 38 rotatably mounted in the movable cavity 31, a transmission belt 39 is provided between the second transmission wheel 38 and the first transmission wheel 37, a gear 310 is fixedly mounted on one side of the second transmission wheel 38, two racks 311 are meshedly mounted around the gear 310 and are lifted and slidably mounted in the movable cavity 31, the two racks 311 have the same specifications and are centrally symmetrically distributed about the gear 310, and the upper and lower rows of dust blocks 313 are synchronously lifted and slid by the reverse movement of the racks 311, so that a plurality of wiring plugs can be squeezed and fixed at the same time, and a plurality of wiring holes 32 can also be partially blocked at the same time;

[0049] The remaining structure is the same as that of Example 2.

[0050] Embodiment 4:

[0051] Reference Figure 5-8 , which is the fourth embodiment of the present invention. This embodiment is different from the third embodiment in that: two mounting strips 312 are respectively vertically fixedly connected to the corresponding racks 311, and the two mounting strips 312 are both lifted and slidably installed in the movable cavity 31 between the two rows of wiring holes 32. A plurality of dust blocks 313 are provided with arc grooves at one end away from the corresponding mounting strips 312, and the curvature of the arc grooves is consistent with the curvature of the wiring holes 32. Two symmetrically distributed springs 314 are installed between the plurality of dust blocks 313 and the corresponding mounting strips 312. The design of the springs 314 is to make the dust blocks 313 have a telescopic characteristic, which can simultaneously meet the requirements of squeezing and fixing the wiring plug and partially blocking the wiring hole 32.

[0052] The remaining structure is the same as that of Example 3.

[0053] Working principle of the present invention:

[0054] In the first step, the mounting block 11 is first aligned with the threaded hole position on the manned aircraft mounting platform, and the mounting block 11 and the manned aircraft mounting platform are detachably assembled by screws 12, thereby completing the detachable installation of the controller body 1, and then the threaded joint 29 is connected to the housing of the manned aircraft drive motor;

[0055] In the second step, the required wiring plug is then passed through the corresponding wiring hole 32 and finally inserted into the wiring jack at the end of the controller body 1 to complete the signal control of the controller body 1 and other control structures, such as signal sensors, etc. At the same time, the knob 34 is rotated to drive the worm 35 to rotate, thereby engaging and driving the worm wheel 36 to rotate, and then driving the first transmission wheel 37 to rotate synchronously, and the second transmission wheel 38 on the other side is driven to rotate through the transmission belt 39, which also drives the gear 310 to rotate, and the two centrally symmetrically distributed racks 311 meshed and installed outside the gear 310 are forced to slide up and down in opposite directions, thereby driving the corresponding installation strips 312 and several corresponding dust blocks 313 to slide up and down in opposite directions respectively, and finally the arc-shaped notches at the ends of several dust blocks 313 are just stuck on the wiring plug, squeezing and resisting the wiring plug, which can prevent the wiring plug from loosening and falling out of the wiring jack;

[0056] Since the wiring jack for inserting the wiring plug is connected to the controller body 1, the hot air flow in the controller body 1 will be discharged from the gap between the wiring plug and the dust block 313 at a relatively high flow rate, which can prevent dust and impurities in the air from adhering to the wiring jack through the gap during the flight of the manned aircraft, thereby affecting the contact between the wiring plug and the wiring jack. At the same time, the dust and impurities that have been attached to the wiring jack when the manned aircraft is not in operation can be discharged from the inside to the outside.

[0057] Step 3: During the flight of the manned aircraft, the driving motor continuously works for a long time, which will generate a lot of heat. The heat dissipation fan on the driving motor continuously delivers hot air to the air inlet pipe 28. After the hot air enters the air inlet pipe 28, it finally enters the controller body 1 through the air inlet seat 2 to heat the electronic components in the controller body 1, so as to avoid the electronic components being affected by the high-altitude and low-temperature environment and being low-power or even unable to work normally. Finally, the hot air is discharged from the wiring jack to maintain the pressure balance in the controller body 1.

[0058] In the fourth step, the sensing probe of the temperature sensor 210 is extended into the air inlet pipe 28 to detect the temperature of the hot air flow in the air inlet pipe 28 in real time. Due to the different flight missions of the manned aircraft, the driving load of the driving motor also needs to be adjusted accordingly, so the heat generated will also be different. When the generated heat is too high and is directly discharged into the controller body 1, it will affect the electronic components in the controller body 1. At this time, the controller body 1 can control the control valve 23 to open the communication path between the air inlet 21 and the inner cavity of the air inlet seat 2, thereby allowing the outside low-temperature cold air to enter from the air inlet 21 and enter the inner cavity of the air inlet seat 2. After mixing with the hot air flow in the air inlet pipe 28, the hot air flow temperature is adjusted to a suitable temperature and then transported to the controller body 1 to ensure that the electronic components in the controller body 1 are at a suitable temperature for operation;

[0059] Step 5: Since the outside air contains dust and impurities, these dust and impurities will enter from the air inlet 21 along with the cold air. However, since the air inlet 21 is provided with a filter 22, the filter 22 can prevent dust and impurities from entering the cold air, thereby achieving preliminary filtration. Since the hot air coming from the driving motor housing may also contain dust and impurities, a secondary filtration is performed through a detachably installed filter box 26, thereby further preventing dust and impurities from entering the controller body 1.

[0060] In the sixth step, the filter box 26 is periodically extracted from the installation port 24 through the block 27 to clean the dust and impurities in the filter box 26. During this process, the inner side of the block 27 is separated from the magnetic sheet 25 on the surface of the air inlet seat 2, and the magnetic adsorption relationship is temporarily lost. When the cleaned filter box 26 is fully inserted into the installation port 24 again, the block 27 fits the surface of the air inlet seat 2, and the inner side of the block 27 is magnetically adsorbed with the magnetic sheet 25 on the surface of the air inlet seat 2 again, ensuring that the filter box 26 will not slide or even fall off from the installation port 24 during the flight of the cargo-carrying aircraft. The above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them. Although the present invention is described in detail with reference to the above embodiments, ordinary technicians in this field should understand that they can still modify the technical solutions recorded in the above embodiments, or replace some of the technical features therein with equivalents; and these modifications or replacements will not make the essence of the corresponding technical solutions deviate from the protection scope of the technical solutions of the embodiments of the present invention.

Claims

1. A highly stable autonomous safety control device for a manned aircraft, comprising a controller body (1), wherein the top of the controller body (1) is provided with an air inlet, and the side wall is provided with a plurality of wiring jacks, wherein: Also includes: An air inlet temperature adjustment component comprises an air inlet seat (2) mounted on the top of a controller body (1) and connected to an air inlet, a control valve (23) being mounted at the connection point between the air inlet seat (2) and the air inlet, an air inlet pipe (28) being mounted on the top of the air inlet seat (2), a temperature sensor (210) being also mounted in the air inlet pipe (28), and a filter component being detachably mounted at the connection point between the control valve (23) and the air inlet; A reinforced dustproof component comprises a reinforced seat (3) fixedly mounted on one end of a controller body (1), wherein an active cavity (31) is provided in the reinforced seat (3), and a plurality of wiring holes (32) are provided on both sides of the reinforced seat (3) through the active cavity (31) and are respectively opposite to the positions of corresponding wiring jacks, wherein two mounting strips (312) capable of being raised and lowered in opposite directions are arranged in the active cavity (31), and dustproof blocks (313) capable of being sealed in the corresponding wiring holes (32) are elastically mounted on the far sides of the two mounting strips (312).

2. The highly stable autonomous safety control device for manned aircraft according to claim 1, characterized in that: Mounting blocks (11) are vertically fixedly installed at the four corners of the controller body (1), and screws (12) are threadedly penetrated and installed on the four mounting blocks (11). A wiring cable extending into the interior is installed at one end of the controller body (1).

3. The highly stable autonomous safety control device for manned aircraft according to claim 1, characterized in that: An air inlet cavity is provided at the bottom of the air inlet seat (2), air inlet ports (21) are provided around the air inlet seat (2) and penetrate the air inlet cavity, a plurality of air inlet ports (21) are embedded with filter screens (22) that are installed in a matching manner, the control valve (23) is installed in the air inlet cavity and is designed to match the inner wall of the air inlet cavity, and installation ports (24) are provided on two opposite outer walls of the air inlet seat (2) and penetrate the air inlet cavity.

4. The highly stable autonomous safety control device for manned aircraft according to claim 3, characterized in that: The filter assembly comprises a filter box (26) which is inserted into the two mounting openings (24) in a matching manner at the same time, a stopper (27) is fixedly mounted on one end of the filter box (26), and two magnetic sheets (25) are respectively mounted on the outer side wall of the air inlet seat (2), and the stopper (27) is magnetically adsorbed and fixed to the two magnetic sheets (25) on a side close to the filter box (26).

5. The highly stable autonomous safety control device for manned aircraft according to claim 4, characterized in that: The inner cavity of the air inlet pipe (28) is connected to the air inlet cavity, a threaded joint (29) is installed on the top of the air inlet pipe (28), the temperature sensor (210) is installed on the outer wall of the air inlet pipe (28), and the internal detection probe extends into the inner cavity of the air inlet pipe (28).

6. The highly stable autonomous safety control device for manned aircraft according to claim 1, characterized in that: A driving seat (33) is fixedly mounted on one end of the reinforcement seat (3), a knob (34) is rotatably mounted on the top of the driving seat (33), the driving seat (33) is hollow in design, and a worm (35) and a worm wheel (36) are rotatably mounted inside the driving seat (33), wherein the top of the worm (35) is fixedly connected to the bottom of the knob (34), and a first transmission wheel (37) is fixedly mounted on one side of the worm wheel (36).

7. The highly stable autonomous safety control device for manned aircraft according to claim 6, characterized in that: A transmission assembly is also arranged in the movable cavity (31), and the transmission assembly comprises a second transmission wheel (38) rotatably mounted in the movable cavity (31), and a transmission belt (39) is arranged between the second transmission wheel (38) and the first transmission wheel (37).

8. The highly stable autonomous safety control device for manned aircraft according to claim 7, characterized in that: A gear (310) is fixedly mounted on one side of the second transmission wheel (38), and two racks (311) are meshedly mounted around the gear (310) and are installed in a lifting and sliding manner in the movable cavity (31). The two racks (311) have the same specifications and are symmetrically distributed about the gear (310).

9. The highly stable autonomous safety control device for manned aircraft according to claim 8, characterized in that: The two mounting bars (312) are respectively vertically fixedly connected to the corresponding racks (311), and the two mounting bars (312) are both lifted and slidably mounted in the movable cavity (31) between the two rows of wiring holes (32).

10. The highly stable autonomous safety control device for manned aircraft according to claim 1, characterized in that: A plurality of the dust blocks (313) are provided with an arcuate groove at one end away from the corresponding mounting strip (312), the arcuate groove has the same arcuate groove as the wiring hole (32), and two symmetrically distributed springs (314) are installed between the plurality of the dust blocks (313) and the corresponding mounting strip (312).

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