Aircraft data acquisition device and method thereof

Abstract

The invention discloses an aircraft data acquisition device and method, and relates to the technical field of aircraft data acquisition, the aircraft data acquisition device comprises an aircraft body, an emergency disengagement assembly is arranged below the aircraft body, the emergency disengagement assembly comprises a butt joint frame and a sleeve plate, and the butt joint frame is fixedly connected below the aircraft body. According to the aircraft data acquisition device and method disclosed by the invention, when a monitor on an aircraft body monitors that the aircraft body is subjected to destructive strike, an electric telescopic rod II drives a butt joint column to be separated from a butt joint sleeve; the gravity of the data collector and other structures outside the data collector drives the suspension air bag to be separated from the butt joint frame, the suspension air bag is filled with hydrogen, the data collector and the aircraft body are separated, the suspension air bag drives the data collector to slowly float to the ground, and emergency separation is achieved. The data collector is prevented from being damaged along with the damage of the aircraft body, and the effect of the data collector is protected.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft data collection, and in particular to an aircraft data collection device and a method thereof. Background Art

[0002] The flight data acquisition system is an automatic test system that integrates UAV flight status monitoring and various ground test measurements and fault diagnosis functions. In order to collect various data during each flight of the aircraft, a data acquisition device needs to be installed on its outside.

[0003] During the use of existing aircraft data acquisition devices, if an aircraft encounters an accident during flight and causes the aircraft to crash, the data acquisition device installed thereon will also crash, which will result in the loss of data collected by the aircraft during this flight. At the same time, it is impossible to know the cause of the crash, which makes the installation of the data acquisition device too useless and reduces the use value of the data acquisition device. Summary of the invention

[0004] The present invention discloses an aircraft data acquisition device, which aims to solve the technical problem that when the existing aircraft data acquisition device is in use, if the aircraft encounters an accident during flight and causes the aircraft to crash, the data acquisition device installed thereon will also crash, which will cause the data collected by the aircraft during this flight to be lost. At the same time, it is impossible to know the cause of the crash, thereby causing the installation of the data acquisition device to be too useless.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] An aircraft data acquisition device includes an aircraft body, an emergency detachment assembly is provided below the aircraft body, and the emergency detachment assembly includes a docking frame and a sleeve plate, the docking frame is fixedly connected to the bottom of the aircraft body, the top of the sleeve plate is fixedly connected to mounting rods at equal distances, the top of the sleeve plate located at the periphery of each mounting rod is fixedly connected to a range baffle, and a suspension airbag is installed on the top of the sleeve plate, the suspension airbag is distributed between the docking frame and each range baffle, the bottom of the suspension airbag is provided with an air hole, and the inside of the air hole is fixedly connected to an air pipe, and the outer wall of the air pipe is connected to an air valve via a flange.

[0007] By providing an emergency separation component, when the monitor on the aircraft body detects that the aircraft body is suffering a devastating blow, the electric telescopic rod 2 drives the docking column to separate from the docking sleeve, and the gravity of the data collector and other structures outside it drives the suspension airbag to separate from the docking frame. The suspension airbag is filled with hydrogen to achieve separation between the data collector and the aircraft body. The suspension airbag drives the data collector to slowly float to the ground to achieve emergency separation, avoid damage to the data collector along with the damage of the aircraft body, and protect the data collector.

[0008] In a preferred embodiment, the bottom of the aircraft body located at the periphery of the docking frame is fixedly connected to an external ring rod, and the external ring rod is fixedly connected to two electric telescopic rods at equal distances facing the side wall of the docking frame, and the output end of each electric telescopic rod is fixedly connected to a docking column, and the end of each mounting rod is fixedly connected to an embedded card rod, and a docking sleeve is fixedly connected to the side of the embedded card rod facing the docking column, and the docking column is inserted into the docking sleeve.

[0009] In a preferred embodiment, the bottom of the sleeve plate is equidistantly connected to the expanding leaves via hinges, and the bottom of the sleeve plate is fixedly connected to an integrated ring rod, and each expanding leaf is equidistantly fixedly connected to a pulling spring rod on the downward side, one end of the pulling spring rod is fixedly connected to the outer side wall of the integrated ring rod, and an installation groove is provided on the outer side wall of the expanding leaf facing downward, and the inner walls on both sides of the installation groove are connected to a rotating shaft via bearings, and the outer side wall of the rotating shaft is fixedly connected to a rotating blade.

[0010] In a preferred embodiment, a landing frame is provided at the bottom of the aircraft body, and monitors are distributed in a ring on the landing frame, the bottom of the sleeve plate is fixedly connected with hanging columns at equal distances, the bottoms of multiple hanging columns are fixedly connected with the same suspended plate, the top of the suspended plate is fixedly connected with two mounting bent rods, and the bottom ends of the two mounting bent rods are provided with the same emergency protection component.

[0011] In a preferred solution, the emergency protection component includes a mounting base plate, and the mounting base plate is fixedly connected to the bottom of two mounting bent rods, the top of the mounting base plate located below the suspended plate is fixedly connected to a fixed column, two surrounding deflection plates are sleeved on the fixed shaft, the top of the mounting base plate located between the two surrounding deflection plates is fixedly connected to an intermediate column, both sides of the intermediate column are hingedly connected to electric telescopic rods one, and the output ends of the two electric telescopic rods one are respectively connected to the outer side walls of adjacent surrounding deflection plates through hinges.

[0012] In a preferred embodiment, telescopic links are fixedly connected to the opposite sides of the two surrounding deflection plates at equal distances, and one end of the multiple telescopic links located on the same surrounding deflection plate is fixedly connected to the same contact plate, and a pressure sensor 1 is fixedly connected to the outer wall of the surrounding deflection plate, and the pressure sensor 1 is located between the surrounding deflection plate and the contact plate.

[0013] By providing an emergency protection component, when the data collector is performing various data collection processes, if floating debris appears in the external environment and impacts the data collector, when the impurities impact the contact plates on both sides of the data collector, the contact plates squeeze the pressure sensor 1 on the surrounding deflection plate, and the electric telescopic rod 1 drives the surrounding deflection plate to deflect, and the two surrounding deflection plates squeeze the protective grid, so that the protective grid drives the data collector to move toward the inside of the two surrounding deflection plates, and the data collector is surrounded by the surrounding deflection plates, thereby providing emergency protection for the data collector. When the impurities impact the protective grid from the front, the sliding block slides in the sliding groove, the extrusion head squeezes the pressure sensor 2, and the electric telescopic rod 1 drives the surrounding deflection plate to rotate, and the data collector is surrounded again, thereby ensuring the safety of the data collector during use.

[0014] In a preferred solution, a sliding groove is provided on the top of the mounting base plate, and two sliding blocks are slidably connected inside the sliding groove, the tops of the two sliding blocks are fixedly connected to the same machine plate, the top of the machine plate is fixedly connected to a protective grid, the top of the machine plate between the protective grid and the two surrounding deflection plates is fixedly connected to a data collector, the top of the mounting base plate is fixedly connected to a rear abutment plate, the side of the rear abutment plate facing the data collector is fixedly connected to two connecting spring rods, one end of the two connecting spring rods is fixedly connected to the same connecting plate, the connecting plate is fixedly connected to one side of the machine plate, the side of the rear abutment plate close to the top is fixedly connected to a second pressure sensor, the side of the connecting plate facing the second pressure sensor is fixedly connected to an extension rod, and one end of the extension rod is fixedly connected to an extrusion head.

[0015] In a preferred solution, a landing buffer protection assembly is provided under the mounting base, and the landing buffer protection assembly includes a grounding seat, which is fixedly connected to the bottom of the mounting base, and two deflection grooves are provided at the bottom of the grounding seat, and the inner walls of the two deflection grooves near the middle position of the grounding seat are connected to the deflection shaft through bearings, and the outer walls of the two deflection shafts are fixedly connected to the deflection frame.

[0016] By providing a landing buffer protection component, when the aircraft body finishes flying, during the landing process, first, the grounding roller on the deflection frame contacts the ground, and during the contact and extrusion process, the buffer spring rod is passively compressed, and the deflection frame is pressed into the deflection groove, thereby reducing the impact of the vibration generated when the aircraft body lands on the data collector. After the aircraft body is completely landed, the electric telescopic rod is adjusted to drive the lock column to be stuck in the lock cylinder to complete the locking of the deflection frame.

[0017] In a preferred solution, the inner walls on both sides of the deflection frame are equidistantly connected to grounding rollers through bearings, and the inner wall of the deflection groove located below the deflection frame is fixedly connected to a buffer spring rod, one end of the buffer spring rod is fixedly connected to one side of the deflection frame, both sides of the grounding seat are fixedly connected to side wall frames, the opposite sides of the two side frames are fixedly connected to electric telescopic rods three, the output ends of the two electric telescopic rods three are fixedly connected to lock cylinders, the tops of the two deflection frames are fixedly connected to lock cylinders, and the lock cylinders and lock cylinders are adapted to each other.

[0018] An aircraft data collection method, using an aircraft data collection device as described above, comprises the following steps:

[0019] Step 1: First, dock the docking frame and the sleeve, press the suspension airbag above the sleeve into the docking frame, and then adjust the electric telescopic rod 2 to drive the docking column to snap into the docking sleeve to complete the installation of the data collector under the sleeve;

[0020] Step 2: During the flight of the aircraft body, the data collector collects various data. During the data collection process, if floating debris appears in the external environment and impacts the direction of the data collector, when the impurities impact the contact plates on both sides of the data collector, the contact plates squeeze the pressure sensor 1 on the surrounding deflection plate, and the electric telescopic rod 1 drives the surrounding deflection plate to deflect, and the two surrounding deflection plates squeeze the protective grid, so that the protective grid drives the data collector to move inside the two surrounding deflection plates, and the data collector is surrounded by the surrounding deflection plates. When the impurities impact the protective grid from the front, the sliding block slides in the sliding groove, the extrusion head squeezes the pressure sensor 2, and the electric telescopic rod 1 drives the surrounding deflection plate to rotate, and the data collector is surrounded again;

[0021] Step 3: When the data collector is out of danger, the electric telescopic rod drives the range deflection plate to reset, and the connecting spring rod in the compressed state resets, and the data collector is pushed out again and continues to work.

[0022] From the above, it can be seen that an aircraft data acquisition device provided by the present invention has a monitor on the aircraft body that detects that the aircraft body is suffering a devastating blow. The electric telescopic rod 2 drives the docking column to detach from the docking sleeve, and the gravity of the data collector and other structures on its outside drives the suspension airbag to separate from the docking frame. The suspension airbag is filled with hydrogen to achieve separation between the data collector and the aircraft body. The suspension airbag drives the data collector to slowly float to the ground to achieve emergency separation, thereby avoiding damage to the data collector along with the damage to the aircraft body and protecting the data collector. Technical effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1The figure is a schematic diagram of the overall structure of an aircraft data acquisition device proposed by the present invention.

[0024] Figure 2 The figure is a front view of the overall structure of an aircraft data acquisition device proposed by the present invention.

[0025] Figure 3 This is a schematic structural diagram of an emergency detachment component of an aircraft data acquisition device proposed by the present invention.

[0026] Figure 4 for Figure 3 Bottom view of the overall structure.

[0027] Figure 5 This is a cross-sectional view of the docking frame and sleeve structure of an aircraft data acquisition device proposed by the present invention.

[0028] Figure 6 This is an enlarged view of the unfolded leaf structure of an aircraft data acquisition device proposed by the present invention.

[0029] Figure 7 This is a schematic structural diagram of an emergency protection component of an aircraft data acquisition device proposed by the present invention.

[0030] Figure 8 for Figure 7 The middle part of the structure is flipped.

[0031] Fig. 9 This is an enlarged view of the data acquisition device structure of an aircraft data acquisition device proposed by the present invention.

[0032] Fig.10 This is a schematic diagram of the structure of a landing cushioning protection component of an aircraft data acquisition device proposed by the present invention.

[0033] Fig.11 for Fig.10 Schematic diagram of the plan structure.

[0034] In the figure: 1. Aircraft body; 2. Landing frame; 3. Emergency protection assembly; 301. Mounting base plate; 302. Protection grid; 303. Surrounding deflection plate; 304. Data collector; 305. Fixed column; 306. Telescopic connecting rod; 307. Contact plate; 308. Sliding groove; 309. Intermediate column; 310. Electric telescopic rod 1; 311. Rear plate; 312. Extension rod; 313. Machine board; 314. Sliding block; 315. Connecting plate; 316. Connecting spring rod; 317. Pressure sensor 1; 318. Pressure sensor 2; 319. Extrusion head; 4. Monitor; 5. Hanging column; 6. Emergency detachment assembly; 601. Docking frame; 602. Electric telescopic rod 2; 603, range baffle; 604, external ring rod; 605, suspension airbag; 606, unfolding leaves; 607, mounting groove; 608, rotating blades; 609, sleeve plate; 610, air pipe; 611, integrated ring rod; 612, pulling spring rod; 613, docking sleeve; 614, embedded card rod; 615, docking column; 616, mounting rod; 617, rotating shaft; 7, landing buffer protection assembly; 701, grounding seat; 702, deflection frame; 703, grounding roller; 704, side frame; 705, electric telescopic rod three; 706, deflection groove; 707, lock cylinder; 708, lock column; 709, buffer spring rod; 710, deflection shaft; 8, suspended plate; 9, installation bent rod. DETAILED DESCRIPTION

[0035] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0036] An aircraft data acquisition device disclosed in the present invention is mainly applied to the use of existing aircraft data acquisition devices. If an aircraft encounters an accident during flight, causing the aircraft to crash, the data acquisition device installed thereon will also crash, which will cause the data collected by the aircraft during this flight to be lost. At the same time, it is impossible to know the cause of the crash, resulting in a scenario where the installation of the data acquisition device is too useless.

[0037] Reference Figure 1-Figure 11A data acquisition device for an aircraft comprises an aircraft body 1, an emergency detachment assembly 6 is arranged below the aircraft body 1, and the emergency detachment assembly 6 comprises a docking frame 601 and a sleeve plate 609, the docking frame 601 is fixedly connected to the bottom of the aircraft body 1, the top of the sleeve plate 609 is fixedly connected with mounting rods 616 at equal distances, the top of the sleeve plate 609 located at the periphery of each mounting rod 616 is fixedly connected with a range baffle 603, and a suspension airbag 605 is installed on the top of the sleeve plate 609, the suspension airbag 605 is distributed between the docking frame 601 and each range baffle 603, an air hole is opened at the bottom of the suspension airbag 605, and an air pipe 610 is fixedly connected to the inside of the air hole, and an air valve is connected to the outer wall of the air pipe 610 through a flange.

[0038] In a specific application scenario, when the monitor 4 on the aircraft body 1 detects that the aircraft body 1 is suffering a devastating blow, the electric telescopic rod 602 drives the docking column 615 to detach from the docking sleeve 613, and the gravity of the data collector 304 and other structures on its outside drives the suspension airbag 605 to separate from the docking frame 601. The suspension airbag 605 is filled with hydrogen to achieve the separation between the data collector 304 and the aircraft body 1. The suspension airbag 605 drives the data collector 304 to slowly float to the ground to achieve emergency separation, thereby avoiding damage to the data collector 304 along with the damage to the aircraft body 1 and protecting the data collector 304.

[0039] Specifically, after the suspension airbag 605 is separated from the docking frame 601, as the data collector 304 descends, the deployment leaves 606 are deflected and deployed upward under the action of wind force, and the deployment leaves 606 play a further buffering role, further increasing the probability of the data collector 304 landing safely.

[0040] It should be noted that when docking the docking frame 601 and the sleeve plate 609, the suspension airbag 605 is pressed into the docking frame 601, and the inflated suspension airbag 605 fits tightly against the inner wall of the docking frame 601, thereby improving the firmness of the docking between the sleeve plate 609 and the docking frame 601.

[0041] Reference Figure 1-Figure 6In a preferred embodiment, the bottom of the aircraft body 1 located at the periphery of the docking frame 601 is fixedly connected to an external ring rod 604, and the external ring rod 604 is fixedly connected to the side wall of the docking frame 601 at an equal distance, and the output end of each electric telescopic rod 602 is fixedly connected to a docking column 615, and the end of each mounting rod 616 is fixedly connected to an embedded card rod 614, and the side of the embedded card rod 614 facing the docking column 615 is fixedly connected to a docking sleeve 613, and the docking column 615 is inserted into the docking sleeve 61 3, the bottom of the sleeve plate 609 is equidistantly connected with expansion leaves 606 through hinges, and the bottom of the sleeve plate 609 is fixedly connected with an integration ring rod 611, and a pulling spring rod 612 is fixedly connected to the side of each expansion leaf 606 facing downward at an equidistant distance, and one end of the pulling spring rod 612 is fixedly connected to the outer side wall of the integration ring rod 611, and an installation groove 607 is opened on the outer side wall of the expansion leaf 606 that is biased downward, and the inner walls on both sides of the installation groove 607 are connected with a rotating shaft 617 through bearings, and the outer side wall of the rotating shaft 617 is fixedly connected with a rotating blade 608.

[0042] Reference Figure 1 and Figure 2 In a preferred embodiment, a landing frame 2 is provided at the bottom of the aircraft body 1, and monitors 4 are distributed in a ring on the landing frame 2, and the bottom of the sleeve plate 609 is fixedly connected with suspension columns 5 at equal distances, and the bottoms of multiple suspension columns 5 are fixedly connected with the same suspended plate 8, and the top of the suspended plate 8 is fixedly connected with two mounting bent rods 9, and the bottom ends of the two mounting bent rods 9 are provided with the same emergency protection component 3.

[0043] Reference Figure 1 , Figure 2 , Figure 7 , Figure 8 and Fig. 9In a preferred embodiment, the emergency protection component 3 includes a mounting base plate 301, and the mounting base plate 301 is fixedly connected to the bottom of the two mounting bent rods 9, the top of the mounting base plate 301 located below the suspended plate 8 is fixedly connected to a fixed column 305, two surrounding deflection plates 303 are sleeved on the fixed shaft, the top of the mounting base plate 301 located between the two surrounding deflection plates 303 is fixedly connected to an intermediate column 309, both sides of the intermediate column 309 are hingedly connected to an electric telescopic rod 310, the output ends of the two electric telescopic rods 310 are respectively connected to the outer side walls of the adjacent surrounding deflection plates 303 through hinges, the opposite sides of the two surrounding deflection plates 303 are fixedly connected with telescopic connecting rods 306 at equal distances, and one end of the multiple telescopic connecting rods 306 located on the same surrounding deflection plate 303 is fixedly connected to the same contact plate 307, and the outer side wall of the surrounding deflection plate 303 is fixedly connected to a pressure sensor 317, and the pressure sensor 317 is located between the surrounding deflection plate 303 and Between the contact plates 307, a sliding groove 308 is opened on the top of the installation base plate 301, and two sliding blocks 314 are slidably connected inside the sliding groove 308. The tops of the two sliding blocks 314 are fixedly connected to the same machine board 313, and the top of the machine board 313 is fixedly connected to the protection grid 302. The top of the machine board 313 located between the protection grid 302 and the two surrounding deflection plates 303 is fixedly connected to the data collector 304, and the top of the installation base plate 301 is fixedly connected to the rear plate 311. Two connecting spring rods 316 are fixedly connected to the side of the rear support plate 311 facing the data collector 304, one end of the two connecting spring rods 316 is fixedly connected to the same connecting plate 315, the connecting plate 315 is fixedly connected to one side of the machine plate 313, the side of the rear support plate 311 close to the top is fixedly connected to the second pressure sensor 318, the side of the connecting plate 315 facing the second pressure sensor 318 is fixedly connected to the extension rod 312, and one end of the extension rod 312 is fixedly connected to the extrusion head 319.

[0044] Specifically, when the data collector 304 is collecting various data, if floating debris appears in the external environment and impacts the data collector 304, when the impurities impact the contact plates 307 on both sides of the data collector 304, the contact plates 307 squeeze the pressure sensor 317 on the surrounding deflection plate 303, and the electric telescopic rod 310 drives the surrounding deflection plate 303 to deflect, and the two surrounding deflection plates 303 squeeze the protective grid 302, so that the protective grid 302 drives the data collector 304 to move. The data collector 304 moves toward the inside of the two surrounding deflection plates 303, and the data collector 304 is surrounded by the surrounding deflection plates 303, so as to provide emergency protection for it. When impurities impact the protection grid 302 from the front, the sliding block 314 slides in the sliding groove 308, the extrusion head 319 squeezes the pressure sensor 2 318, and the electric telescopic rod 1 310 drives the surrounding deflection plates 303 to rotate, and the data collector 304 is surrounded again to ensure the safety of the data collector 304 during use.

[0045] Reference Figure 1 , Figure 2 , Fig.10 and Fig.11 In a preferred embodiment, a landing buffer protection component 7 is provided below the mounting base, and the landing buffer protection component 7 includes a grounding seat 701, the grounding seat 701 is fixedly connected to the bottom of the mounting base, and two deflection grooves 706 are provided at the bottom of the grounding seat 701, and the inner walls of the two deflection grooves 706 near the middle position of the grounding seat 701 are connected to the deflection shaft 710 through bearings, and the outer walls of the two deflection shafts 710 are fixedly connected to the deflection frames 702, and the inner walls on both sides of the deflection frames 702 are equidistantly connected to the grounding sliding Roller 703, and the deflection groove 706 is located on the inner wall below the deflection frame 702, and is fixedly connected with a buffer spring rod 709. One end of the buffer spring rod 709 is fixedly connected to one side of the deflection frame 702. Side wall frames are fixedly connected to both sides of the grounding seat 701. The opposite sides of the two side frames 704 are fixedly connected with electric telescopic rod three 705. The output ends of the two electric telescopic rods three 705 are fixedly connected with lock cylinders 708. The tops of the two deflection frames 702 are fixedly connected with lock cylinders 707, and the lock cylinders 708 and lock cylinders 707 are adapted to each other.

[0046] It should be noted that when the aircraft body 1 finishes flying, during the landing process, first, the ground sliding roller 703 on the deflection frame 702 contacts the ground. During the contact and extrusion process, the buffer spring rod 709 is passively compressed, and the deflection frame 702 is pressed into the deflection groove 706, thereby reducing the impact of the vibration generated when the aircraft body 1 lands on the data collector 304. After the aircraft body 1 is completely landed, the electric telescopic rod three 705 is adjusted to drive the lock column 708 to be stuck in the lock cylinder 707, thereby completing the locking of the deflection frame 702.

[0047] An aircraft data collection method, using an aircraft data collection device as described above, comprises the following steps:

[0048] Step 1: First, dock the docking frame 601 with the sleeve plate 609, press the suspension airbag 605 above the sleeve plate 609 into the docking frame 601, and then adjust the electric telescopic rod 2 602 to drive the docking column 615 to snap into the docking sleeve 613, and complete the installation of the data collector 304 below the sleeve plate 609;

[0049] Step 2: During the flight of the aircraft body 1, the data collector 304 collects various data. During the data collection process, if floating debris appears in the external environment and impacts the direction of the data collector 304, when the impurities impact the contact plates 307 on both sides of the data collector 304, the contact plates 307 squeeze the pressure sensor 317 on the surrounding deflection plate 303, and the electric telescopic rod 310 drives the surrounding deflection plate 303 to deflect, and the two surrounding deflection plates 303 are pressed against the protective net. The protective grid 302 is squeezed, so that the protective grid 302 drives the data collector 304 to move toward the inside of the two surrounding deflection plates 303, and the data collector 304 is surrounded by the surrounding deflection plates 303. When impurities impact the protective grid 302 from the front, the sliding block 314 slides in the sliding groove 308, the squeezing head 319 squeezes the pressure sensor 2 318, and the electric telescopic rod 1 310 drives the surrounding deflection plates 303 to rotate, and the data collector 304 is surrounded again;

[0050] Step 3: When the data collector 304 is out of danger, the electric telescopic rod 1 310 drives the range deflection plate to reset, and then the connecting spring rod 316 in the compressed state is reset, and the data collector 304 is pushed out again to continue working.

[0051] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aircraft data acquisition device, comprising an aircraft body (1), characterized in that: An emergency detachment assembly (6) is provided below the aircraft body (1), and the emergency detachment assembly (6) comprises a docking frame (601) and a sleeve (609), the docking frame (601) is fixedly connected to the bottom of the aircraft body (1), the top of the sleeve (609) is fixedly connected to mounting rods (616) at equal distances, the top of the sleeve (609) located at the periphery of each mounting rod (616) is fixedly connected to a range baffle (603), and a suspension airbag (605) is installed on the top of the sleeve (609), the suspension airbag (605) is distributed between the docking frame (601) and each range baffle (603), the bottom of the suspension airbag (605) is provided with an air hole, and the inside of the air hole is fixedly connected to an air pipe (610), and the outer wall of the air pipe (610) is connected to an air valve via a flange.

2. The aircraft data acquisition device according to claim 1, characterized in that: The bottom of the aircraft body (1) located at the periphery of the docking frame (601) is fixedly connected to an external connecting ring rod (604), and the external connecting ring rod (604) is fixedly connected to an electric telescopic rod 2 (602) at an equal distance from the side wall facing the docking frame (601), and the output end of each electric telescopic rod 2 (602) is fixedly connected to a docking column (615), and the end of each mounting rod (616) is fixedly connected to an embedded clamping rod (614), and a docking sleeve (613) is fixedly connected to the side of the embedded clamping rod (614) facing the docking column (615), and the docking column (615) is inserted into the docking sleeve (613).

3. The aircraft data acquisition device according to claim 2, characterized in that: The bottom of the sleeve plate (609) is equidistantly connected to the expansion leaves (606) via hinges, and the bottom of the sleeve plate (609) is fixedly connected to an integrated ring rod (611), and a pulling spring rod (612) is fixedly connected to the side of each expansion leaf (606) facing downward at an equidistant distance, and one end of the pulling spring rod (612) is fixedly connected to the outer side wall of the integrated ring rod (611), and an installation groove (607) is formed on the outer side wall of the expansion leaf (606) facing downward, and the inner walls on both sides of the installation groove (607) are connected to a rotating shaft (617) via bearings, and the outer side wall of the rotating shaft (617) is fixedly connected to a rotating blade (608).

4. The aircraft data acquisition device according to claim 1, characterized in that: The bottom of the aircraft body (1) is provided with a landing frame (2), and monitors (4) are distributed in a ring on the landing frame (2), the bottom of the sleeve plate (609) is fixedly connected with suspension columns (5) at equal distances, the bottoms of multiple suspension columns (5) are fixedly connected with the same suspended plate (8), the top of the suspended plate (8) is fixedly connected with two installation bent rods (9), and the bottom ends of the two installation bent rods (9) are provided with the same emergency protection component (3).

5. The aircraft data acquisition device according to claim 4, characterized in that: The emergency protection component (3) comprises a mounting base plate (301), and the mounting base plate (301) is fixedly connected to the bottom of two mounting bent rods (9), the top of the mounting base plate (301) located below the suspended plate (8) is fixedly connected to a fixing column (305), two surrounding deflection plates (303) are sleeved on the fixed shaft, the top of the mounting base plate (301) located between the two surrounding deflection plates (303) is fixedly connected to an intermediate column (309), both sides of the intermediate column (309) are connected to electric telescopic rods (310) through hinges, and the output ends of the two electric telescopic rods (310) are respectively connected to the outer side walls of the adjacent surrounding deflection plates (303) through hinges.

6. The aircraft data acquisition device according to claim 5, characterized in that: Telescopic connecting rods (306) are fixedly connected at equal distances on opposite sides of the two surrounding deflection plates (303), and one end of a plurality of telescopic connecting rods (306) located on the same surrounding deflection plate (303) is fixedly connected to the same contact plate (307), and a pressure sensor 1 (317) is fixedly connected to the outer wall of the surrounding deflection plate (303), and the pressure sensor 1 (317) is located between the surrounding deflection plate (303) and the contact plate (307).

7. The aircraft data acquisition device according to claim 6, characterized in that: The top of the installation base plate (301) is provided with a sliding groove (308), and two sliding blocks (314) are slidably connected inside the sliding groove (308), the tops of the two sliding blocks (314) are fixedly connected to the same machine board (313), the top of the machine board (313) is fixedly connected to a protection grid frame (302), the top of the machine board (313) located between the protection grid frame (302) and the two surrounding deflection plates (303) is fixedly connected to a data collector (304), the top of the installation base plate (301) is fixedly connected to a rear abutment plate (311), and the rear abutment plate Two connecting spring rods (316) are fixedly connected to the side (311) facing the data acquisition device (304), one end of the two connecting spring rods (316) is fixedly connected to the same connecting plate (315), the connecting plate (315) is fixedly connected to one side of the machine plate (313), the side of the rear abutment plate (311) close to the upper side is fixedly connected to the second pressure sensor (318), the side of the connecting plate (315) facing the second pressure sensor (318) is fixedly connected to the extension rod (312), and one end of the extension rod (312) is fixedly connected to the extrusion head (319).

8. The aircraft data acquisition device according to claim 5, characterized in that: A landing buffer protection component (7) is provided below the mounting base, and the landing buffer protection component (7) comprises a grounding seat (701), the grounding seat (701) is fixedly connected to the bottom of the mounting base, two deflection grooves (706) are provided at the bottom of the grounding seat (701), the inner walls of the two deflection grooves (706) near the middle of the grounding seat (701) are connected to deflection shafts (710) via bearings, and the outer side walls of the two deflection shafts (710) are fixedly connected to deflection frames (702).

9. The aircraft data acquisition device according to claim 8, characterized in that: The inner walls of both sides of the deflection frame (702) are equidistantly connected to grounding rollers (703) through bearings, and the inner wall of the deflection groove (706) located below the deflection frame (702) is fixedly connected to a buffer spring rod (709), one end of the buffer spring rod (709) is fixedly connected to one side of the deflection frame (702), both sides of the grounding seat (701) are fixedly connected to side wall frames, the opposite sides of the two side frames (704) are fixedly connected to electric telescopic rods three (705), the output ends of the two electric telescopic rods three (705) are fixedly connected to lock cylinders (708), and the tops of the two deflection frames (702) are fixedly connected to lock cylinders (707), and the lock cylinders (708) and the lock cylinders (707) are adapted to each other.

10. An aircraft data collection method, using an aircraft data collection device as claimed in claim 9, characterized in that: The following steps are involved: Step 1: First, dock the docking frame (601) and the sleeve (609), press the suspension airbag (605) above the sleeve (609) into the docking frame (601), and then adjust the electric telescopic rod 2 (602) to drive the docking column (615) to snap into the docking sleeve (613), and complete the installation of the data collector (304) below the sleeve (609); Step 2: During the flight of the aircraft body (1), the data collector (304) collects various data. During the data collection process, if floating debris appears in the external environment and impacts the data collector (304), when the debris impacts the contact plates (307) on both sides of the data collector (304), the contact plates (307) squeeze the pressure sensor 1 (317) on the surrounding deflection plate (303), and the electric telescopic rod 1 (310) drives the surrounding deflection plate (303) to deflect, and the two surrounding deflection plates (303) press the protective grid (3 02) is squeezed, so that the protection grid (302) drives the data collector (304) to move toward the inside of the two surrounding deflection plates (303), and the data collector (304) is surrounded by the surrounding deflection plates (303). When impurities impact the protection grid (302) from the front, the sliding block (314) slides in the sliding groove (308), the squeezing head (319) squeezes the pressure sensor 2 (318), and the electric telescopic rod 1 (310) drives the surrounding deflection plates (303) to rotate, and the data collector (304) is surrounded again; Step 3: When the data collector (304) is out of danger, the electric telescopic rod 1 (310) drives the range deflection plate to reset, and the connecting spring rod (316) in the compressed state is reset, and the data collector (304) is pushed out again to continue working.

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