On-board ground function verification method for helicopter emergency floating system

Abstract

The invention belongs to the field of helicopter lifesaving, and discloses a helicopter emergency floating system onboard ground function verification method which comprises the following steps: step 1, determining an emergency floating system onboard ground verification fixing mode; 2, designing a helicopter fixing scheme according to the fixing mode; 3, arranging a test scene; step 4, performing test verification; and 5, interpreting test data.

Description

Technical Field

[0001] The invention belongs to the field of helicopter lifesaving, and in particular relates to an onboard ground function verification method for a helicopter emergency flotation system. Background Art

[0002] The helicopter emergency flotation system is designed to provide buoyancy for the helicopter during an emergency landing on water, ensuring that personnel have enough time to escape the helicopter and board the lifeboat to save themselves.

[0003] During the development and verification of the helicopter emergency flotation system, onboard ground functional verification is an important test. Compared with laboratory verification, it can evaluate the coordinated working effect of the emergency flotation system and the onboard cross-linking equipment and the compatibility of the inflatable and deployable floats with the fuselage. Compared with aerial test verification, onboard ground verification has lower costs, can discover design defects at an early stage, and improve the system before aerial flight test verification, and is also crucial to reducing flight safety. Summary of the invention

[0004] Purpose of the invention: To propose a method for verifying the ground function of a helicopter emergency flotation system, so as to solve the problem that the ground laboratory test cannot verify the coordinated working effect with the onboard cross-linking equipment and the compatibility with the fuselage, and effectively reduce the risk of aerial flight tests.

[0005] Technical Solution

[0006] A method for verifying the ground function of a helicopter emergency flotation system on board, the steps are as follows:

[0007] Step 1: Determine the onboard ground verification and fixing method of the emergency flotation system;

[0008] Step 2: Design a helicopter fixing scheme based on the fixing method;

[0009] Step 3: Arrange the experimental test scene;

[0010] Step 4: Conduct test verification;

[0011] Step 5: Interpret the test data.

[0012] Further, in step 1, the specific process is as follows: determining the position of the lowest point of the buoy after the emergency flotation system is inflated and deployed;

[0013] If the lowest point of the floats after deployment is higher than the lowest point of the landing gear, the helicopter does not need additional fixing when parked on the ground;

[0014] If the lowest point of the floats after deployment is lower than the lowest point of the landing gear, lift the helicopter up and park it;

[0015] If there is interference between the float and the ground or the jack in the jacked-up parking position, the helicopter will be suspended.

[0016] Furthermore, for the ground parking status of the helicopter, the helicopter should be parked on a relatively flat and open ground, the equipment around the helicopter should be cleared, and no debris should be placed on or around the helicopter;

[0017] Remove optional equipment on board, drain fuel, and reduce helicopter weight;

[0018] Inflate the landing gear tire pressure to the maximum allowed value;

[0019] Add counterweight to adjust the helicopter's weight center of gravity and keep the helicopter in a level state.

[0020] Furthermore, for the helicopter jacked up and parked state,

[0021] Park the helicopter on a flat and open ground, clear the equipment around the helicopter, and do not allow any debris to be placed on or around the helicopter; use a jack to lift the helicopter, ensuring that the lowest point of the deployed float is no less than 100mm from the ground to ensure that there is a sufficient safety distance between the inflatable float and the jack and the ground; appropriately adjust the up and down positions of each jacking point to control the overall level of the helicopter.

[0022] Furthermore, for the helicopter in a hovering state, after removing the helicopter rotor, use the fuselage rotor hub or fuselage anchoring point, use a large-tonnage crane or a crane to lift the helicopter as a whole; remove the optional equipment on the aircraft, drain the fuel, and reduce the weight of the helicopter;

[0023] In the hoisted state, add lateral mooring and adopt multi-point suspension to prevent the helicopter from rotating; ensure that the helicopter is in a level state as a whole.

[0024] Further, in step three, the experimental test scenarios include:

[0025] A high-definition camera is installed in front and behind the helicopter, with an accuracy of no less than 20 frames per second; the front camera range includes the buoys on both sides in front of the helicopter, and the rear camera range includes the buoys on both sides behind the helicopter. The camera range is ensured to be symmetrical with respect to the middle of the helicopter;

[0026] The height direction of the high-definition camera is consistent with the height direction of the buoy assembly;

[0027] During the test, a high-speed camera is set up on the front and rear sides of the helicopter, with an accuracy of at least 1000 frames per second. The camera range of each camera includes the buoy on the same side of the helicopter and the 10m range of the buoy's side in the horizontal direction, and the buoy on the same side of the helicopter and the position of the rotor tail rotor in the vertical direction;

[0028] Before the test, position labels are glued to the fuselage structure around the floats and numbered; the position labels include a series of labels arranged along the upper and lower defense lines, which are arranged at equal distances; a series of labels arranged longitudinally of the helicopter, which are arranged at equal distances; and typical extreme positions of the fit between the inflated and deployed floats and the fuselage;

[0029] Before the test, position strip labels are glued on the ground around the buoy. The strip labels need to be arranged in the horizontal direction, and the scales are set symmetrically along the left and right sides of the fuselage.

[0030] Further, in step 4, the test verification includes:

[0031] ① Carry out a check on the output judgment logic function of the flooding sensor of the emergency flotation system control box;

[0032] ② Carry out manual start output function check of emergency flotation system control box;

[0033] ③ Carry out output performance inspection of the flooding sensor of the emergency flotation system control box;

[0034] ④ Carry out manual start output performance inspection of the emergency flotation system control box;

[0035] ⑤ Carry out performance verification of the inflation and deployment function of the buoy assembly of the emergency flotation system.

[0036] Further, in step 5, the data interpretation process is as follows:

[0037] Within 5 to 10 minutes after the buoy is inflated and deployed, use a pressure gauge to measure and record the pressure value of each inflated buoy;

[0038] After the test, the video data collected by the high-definition camera is interpreted to determine whether the buoy inflation time meets the design requirements; the buoy inflation time is calculated from the time when the buoy starts to inflate and the buoy compartment fairing skin moves, until the buoy is fully deployed and formed;

[0039] After the test, the video data collected by the high-definition camera is interpreted to check whether the left and right buoys are inflated simultaneously and symmetrically; check frame by frame whether the inflation process of the four buoys is balanced and whether the movement start time of the buoy compartment fairing skin is the same; and read the scale values ​​of the lateral extreme positions of the left and right buoys at the same time at a time interval of 0.5s, comparing them with the scales on the ground strip labels. If they are the same, it means that the left and right buoys are inflated simultaneously and symmetrically;

[0040] After the test, the video data collected by the high-speed camera is interpreted to check whether the jettisoned objects interfere with the rotor and tail rotor. If no interference occurs, the position label attached to the fuselage structure can be referred to to determine whether a certain safety distance is maintained;

[0041] After the test, the video data collected by the high-definition camera was interpreted and it was found that the protrusions on the fuselage structure or skin did not affect the inflation and forming of the pontoons, and there was no phenomenon of protrusions puncturing the pontoons. The spatial position and interference of the inflatable pontoons were verified to be consistent with the design status through quantitative comparison between the labels on the fuselage and the design status.

[0042] In summary, the beneficial effects of the present invention are as follows:

[0043] The present application provides a method for verifying the ground function of a helicopter emergency flotation system on board. The method adopts a step-by-step verification method and provides three verification test states according to the layout position of the inflatable float assembly. The method has the characteristics of diverse verification methods, low cost, and sufficient verification, and can provide guidance for the verification of the ground function of a helicopter emergency flotation system on board. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 Schematic diagram of the emergency flotation system;

[0045] Figure 2 Emergency flotation system onboard ground function verification flow chart. DETAILED DESCRIPTION

[0046] A method for verifying the onboard ground function of a helicopter emergency flotation system, the verification contents mainly include:

[0047] a) Verify the output judgment logic function of the flood sensor of the emergency flotation system control box

[0048] b) Verify the output performance of the water sensor of the emergency flotation system control box;

[0049] c) Verify the manual start output function of the emergency flotation system control box;

[0050] d) Verify the manual start output performance of the emergency flotation system control box;

[0051] e) Verify the inflation and deployment performance of the emergency flotation system buoy assembly;

[0052] (1) Check and record whether the inflation pressure of the buoy meets the design requirements;

[0053] (2) Verify whether the buoy inflation time meets the design requirements;

[0054] (3) Verify that the four buoys are inflated simultaneously and symmetrically;

[0055] (4) Check whether the jettisoned object maintains a certain safe distance from the rotor / tail rotor.

[0056] f) Verify the compatibility of the emergency flotation system buoy assembly after inflation and deployment

[0057] (1) Check the spatial position and interference between the inflatable float and the protrusions on the fuselage or skin, which should be consistent with the design status;

[0058] (2) Record the accessibility of the float compartment deflation operation by ground personnel.

[0059] The verification content can fully verify the coordinated working effect of the emergency flotation system and the onboard cross-linking equipment, as well as the compatibility of the inflatable and deployable buoys with the fuselage.

[0060] A method for verifying the ground function of a helicopter emergency flotation system comprises the following steps: Figure 2 shown):

[0061] Step 1: Determine the fixing method of the emergency flotation system onboard ground verification test piece

[0062] The emergency flotation system onboard ground verification test piece includes a helicopter and an emergency flotation system installed thereon. Since the emergency flotation system is mainly fixed on the helicopter fuselage structure, to determine the fixing state of the emergency flotation system onboard ground verification test piece, it is only necessary to determine the fixing state of the helicopter.

[0063] According to the state of the inflated and deployed buoys after the design is completed (including the layout position, shape, size and other factors of the inflated buoys on the aircraft), the helicopter fixing method for verifying the emergency flotation system on-board ground test is determined.

[0064] In order to verify the onboard ground function of the emergency flotation system, it is necessary to check the position of the lowest point relative to the landing gear according to the state of the inflated and deployed float, and obtain the helicopter fixing method for the onboard ground function verification of the emergency flotation system: if the lowest point of the inflated and deployed float is higher than the lowest point of the landing gear, the helicopter can be parked directly on the ground without additional fixing measures; if it is lower than the lowest point of the landing gear, the helicopter can be parked by jacking up and using a jack to lift the helicopter off the ground; in the case of jacking up and parking by helicopter, if interference is found between the float and the jack / ground, it is necessary to choose the helicopter hovering and hanging method to complete the test.

[0065] Step 3: Design a helicopter fixing solution based on the helicopter fixing method

[0066] For helicopter ground parking status:

[0067] Park the helicopter on a relatively flat and open ground, clear the equipment around the helicopter, and do not allow any debris to be placed on or around the helicopter.

[0068] To ensure that the helicopter inflatable buoy has sufficient test space, the following measures are adopted:

[0069] When the helicopter is parked, remove the optional equipment on board as much as possible, drain the fuel, and reduce the weight of the helicopter;

[0070] When the helicopter is in a stopped state, the tire pressure of the landing gear is inflated to the maximum allowed value;

[0071] When the helicopter is in a stopped state, the counterweight is appropriately added to adjust the weight center of gravity of the helicopter to ensure that the helicopter is in a horizontal state.

[0072] For the helicopter jacked up and parked:

[0073] Park the helicopter on a relatively flat and open ground, clear the equipment around the helicopter, and do not allow any debris to be placed on or around the helicopter. Use a jack to lift the helicopter, and ensure that the lowest point of the deployed float is no less than 100mm from the ground to ensure that there is a sufficient safety distance between the inflatable float and the jack and the ground.

[0074] When the helicopter is jacked up and parked, the upper and lower positions of each jacking point are appropriately adjusted to ensure that the helicopter is in a level state as a whole.

[0075] Consider increasing the fuselage counterweight to ensure that accidental asymmetric inflation of the floats does not cause an asymmetric lateral moment effect on the helicopter, and add rigging to both sides of the fuselage to secure it.

[0076] The empirical formula for fuselage counterweight design is as follows:

[0077] a(m1+m2)≥b(m3×V / t)c

[0078] in:

[0079] t is the time it takes for the float skin to separate from the fuselage;

[0080] The speed at which the V-float skin is completely separated from the fuselage;

[0081] m1 body weight;

[0082] m2 body weight;

[0083] m3 single pontoon skin weight;

[0084] a The fuselage lateral overturning moment coefficient is taken as 0.15;

[0085] b. Number of floats on one side of the fuselage;

[0086] c Safety factor, take 3.

[0087] The "helicopter jack-up parking" helicopter securing method provides a fuselage counterweight design formula and measures to increase lateral stability using mooring rigging on both sides of the fuselage, which can effectively prevent the helicopter from tipping over laterally and ensure the safety of the test.

[0088] For helicopter hovering suspension method:

[0089] After removing the helicopter rotor, use the fuselage rotor hub or fuselage anchoring points and a large-tonnage crane or hoist to lift the helicopter as a whole.

[0090] Before the helicopter is hoisted, it is necessary to remove the optional equipment on board, drain the fuel, and reduce the weight of the helicopter.

[0091] The hoisting state requires the addition of lateral mooring and the adoption of multi-point suspension to prevent the helicopter from rotating so as to maintain a stable state.

[0092] When the helicopter is hoisted, the upper and lower positions of each hanging point are appropriately adjusted to ensure that the helicopter is in a horizontal state as a whole.

[0093] The test verifies the fixed status of the helicopter. Under the condition of ensuring safety, ground parking or jack-up parking of the helicopter can be given priority, which can effectively reduce the test cost.

[0094] Step 4: Experimental test layout design

[0095] The experimental test equipment is equipped with a high-definition camera with an accuracy of at least 20 frames per second to film the test conditions.

[0096] During the test, a high-definition camera is installed in front and behind the helicopter respectively. The front camera range must include the floats on both sides in front of the helicopter, and the rear camera range must include the floats on both sides behind the helicopter. The camera range must be symmetrical with respect to the middle of the helicopter.

[0097] Appropriate front and rear adjustments can be made according to actual conditions to ensure that the high-definition camera can capture the buoys deployed on the left and right sides.

[0098] The height direction of the high-definition camera is consistent with the height direction of the buoy assembly.

[0099] The experimental test equipment is equipped with a high-speed camera with an accuracy of at least 1000 frames per second to film the jettisoning of the buoy inflatable buoy assembly.

[0100] During the test, a high-speed camera is installed on the front and rear sides of the helicopter respectively. The shooting range of each camera must include the pontoon on the same side of the helicopter and the 10m range of the side of the pontoon in the horizontal direction, and the pontoon on the same side of the helicopter and the rotor tail rotor position in the vertical direction.

[0101] Before the test, position labels shall be glued on the fuselage structure around the floats and numbered. The position labels shall include a series of labels arranged along the upper and lower defense lines, which are arranged at equal distances; a series of labels arranged longitudinally of the helicopter, which are arranged at equal distances; and the typical extreme positions of the inflated and deployed floats and the fuselage.

[0102] Before the test, position strip labels need to be glued on the ground around the buoy. The strip labels need to be arranged horizontally, and the scales are set symmetrically along the left and right of the fuselage.

[0103] Step 5: Test verification

[0104] ① Carry out the function check of the flood sensor output judgment logic of the emergency flotation system control box:

[0105] A. Disconnect the air source device from the control box and use an air source device simulator instead.

[0106] B. Use the control board to power the floating control box, and use a single cup filled with water to immerse the water sensors one by one. At this time, the air source device simulator does not light up. Use two cups filled with water to immerse the water sensors at the same time, and the air source device simulator lights up. This proves that the output judgment logic of the water sensor of the emergency floating system control box is normal.

[0107] The gas source device simulator includes a transfer cable (including a connector), an electromagnetic relay, an indicator light, a simulator connector, a reset switch, etc. One end of the transfer cable (including a connector) is connected to the floating control box, and the other end is connected to the simulator connector. After the electromagnetic relay receives the ignition signal output by the floating control box, the indicator light can be lit. Pressing the reset switch can turn off the indicator light. The indicator light and the simulator connector can be determined according to the number of gas source devices. The simulator is simple and reliable in design. It can replace the gas source device and effectively detect whether the floating control box outputs an ignition output signal.

[0108] The air source device simulator is provided with multiple indicator lights according to the number of air source devices. If there is a fault, the fault location and water sensor output judgment logic fault troubleshooting can be performed according to the on and off status of the indicator lights during the water sensor output judgment logic check of the emergency floating system control box. If a fault occurs, troubleshooting and system improvement design need to be carried out.

[0109] ② Carry out manual start output function check of emergency flotation system control box:

[0110] A. Disconnect the air source device from the control box and use an air source device simulator instead.

[0111] B. Use the control panel to power the floating control box, press the "manual inflation switch", and the air source device simulator lights up. This proves that the manual start output function of the emergency floating system control box is normal.

[0112] The air source device simulator can locate faults and troubleshoot manual start output faults according to the on and off status of the indicator light when the manual start output function of the emergency floating system control box is in operation. If a fault occurs, troubleshooting and system improvement design are required.

[0113] ③ Carry out the output performance inspection of the water sensor of the emergency floating system control box:

[0114] A. After the output judgment logic function of the flood sensor of the emergency floating system control box is checked to be normal, the output performance check of the flood sensor of the emergency floating system control box is continued.

[0115] B. Disconnect the gas source device simulator and use the gas source device bottle valve assembly instead.

[0116] C. Use the control board to power the floating control box, and use a cup filled with water to immerse the water sensor (at least two). If the bottle valve assembly of the gas source device starts normally, it proves that the output performance of the water sensor of the emergency floating system control box is normal.

[0117] The output performance inspection of the submerged sensor of the emergency floating system control box adopts the gas source device bottle valve assembly instead of the gas source device, which can effectively reduce the verification cost.

[0118] ④ Carry out manual start output performance inspection of the emergency flotation system control box:

[0119] A. After the manual start output function check of the emergency floating system control box is normal, continue to carry out the manual start output performance check of the emergency floating system control box.

[0120] B. Disconnect the gas source device simulator and use the gas source device bottle valve assembly instead.

[0121] C. Use the control panel to power the floating control box, press the "manual inflation switch", and the gas source device bottle valve assembly starts normally, which proves that the manual start output performance of the emergency floating system control box is normal.

[0122] The manual start output performance inspection of the emergency floating system control box adopts the gas source device bottle valve assembly instead of the gas source device, which can effectively reduce the verification cost.

[0123] ⑤ Carry out the performance verification of the inflation and deployment of the buoy assembly of the emergency floating system:

[0124] Disconnect the connection between the gas source device bottle valve assembly and the control box, and restore the connection on the gas source device machine.

[0125] Use the control panel to power the control box, press the "manual inflation switch", then the gas source device starts, and the high-pressure gas enters the folding buoy through the inflation pipeline, and the buoy assembly is inflated and expanded.

[0126] During the test, high-definition cameras and high-speed cameras were used to film the buoy inflation and test process.

[0127] Compared with aerial test verification, on-board ground verification is less expensive and is carried out gradually. It can discover design defects in the early stages of the test and improve the system before aerial flight test verification. It is also crucial to reducing flight safety.

[0128] Step 5: Test data interpretation

[0129] Within 5 to 10 minutes after the buoy is inflated and deployed, use a pressure gauge to measure and record the pressure value of the inflated buoy one by one. The buoy pressure value should meet the design value requirements.

[0130] After the test, the video data collected by the high-definition camera is interpreted to determine whether the buoy inflation time meets the design requirements. The inflation time is calculated from the time when the buoy starts to inflate and the buoy compartment fairing skin moves, until the buoy is fully deployed (reaching the designed shape).

[0131] After the test, the video data collected by the high-definition camera is interpreted to check whether the left and right buoys are inflated simultaneously and symmetrically. Check frame by frame whether the inflation process of the four buoys is roughly balanced and whether the movement of the buoy compartment fairing skin starts at the same time; and at a time interval of 0.5s, read the scale values ​​of the lateral extreme positions of the left and right buoys at the same time against the scales on the ground strip labels to see if they are the same. If they are the same, it means that the left and right buoys are inflated simultaneously and symmetrically.

[0132] After the test, the video data collected by the high-speed camera is interpreted to check whether the jettisoned objects interfere with the rotor and tail rotor. If no interference occurs, the position labels adhered to the fuselage structure can be used as a reference to determine whether a certain safety distance is maintained.

[0133] After the test, the video data collected by the high-definition camera was interpreted and it was found that the protrusions on the fuselage structure or skin did not affect the inflation and forming of the pontoons, and there was no phenomenon of protrusions puncturing the pontoons. The spatial position and interference of the inflatable pontoons were verified to be consistent with the design status through quantitative comparison between the labels on the fuselage and the design status.

[0134] During the test verification, high-definition cameras and high-speed cameras were set up to record the inflation and forming process of the buoy, and the video was compared and interpreted in combination with the set labels. This method is simple and practical.

Claims

1. A method for verifying the ground function of a helicopter emergency flotation system, characterized in that: Here are the steps: Step 1: Determine the onboard ground verification and fixing method of the emergency flotation system; Step 2: Design a helicopter fixing scheme based on the fixing method; Step 3: Arrange the experimental test scene; Step 4: Conduct test verification; Step 5: Interpret the test data.

2. The method according to claim 1, characterized in that: In step 1, the specific process is as follows: determine the position of the lowest point of the buoy after the emergency flotation system is inflated and deployed; If the lowest point of the floats after deployment is higher than the lowest point of the landing gear, the helicopter does not need additional fixing when parked on the ground; If the lowest point of the floats after deployment is lower than the lowest point of the landing gear, lift the helicopter up and park it; If there is interference between the float and the ground or the jack in the jacked-up parking position, the helicopter will be suspended.

3. The method according to claim 2, characterized in that: For the ground parking status of the helicopter, park the helicopter on a relatively flat and open ground, clear the equipment around the helicopter, and do not allow any debris to be placed on or around the helicopter; Remove optional equipment on board, drain fuel, and reduce helicopter weight; Inflate the landing gear tire pressure to the maximum allowed value; Add counterweight to adjust the helicopter's weight center of gravity and keep the helicopter in a level state.

4. The method according to claim 3, characterized in that: For the helicopter jacked up and parked, Park the helicopter on a flat and open ground, clear the equipment around the helicopter, and do not allow any debris to be placed on or around the helicopter; Use a jack to lift up the helicopter, making sure that the lowest point of the deployed float is no less than 100mm from the ground to ensure that there is a sufficient safety distance between the inflatable float and the jack and the ground; appropriately adjust the up and down positions of each jacking point to control the overall level of the helicopter.

5. The method according to claim 4, characterized in that: For the helicopter in a hovering state, after removing the helicopter rotor, use the fuselage rotor hub or fuselage anchoring point, use a large-tonnage crane or a crane to lift the helicopter as a whole; remove the optional equipment on the aircraft, drain the fuel, and reduce the weight of the helicopter; In the hoisted state, add lateral mooring and adopt multi-point suspension to prevent the helicopter from rotating; ensure that the helicopter is in a level state as a whole.

6. The method according to claim 5, characterized in that: In step 3, the experimental test scenarios include: A high-definition camera is installed in front and behind the helicopter, with an accuracy of no less than 20 frames per second; the front camera range includes the buoys on both sides in front of the helicopter, and the rear camera range includes the buoys on both sides behind the helicopter. The camera range is ensured to be symmetrical with respect to the middle of the helicopter; The height direction of the high-definition camera is consistent with the height direction of the buoy assembly; During the test, a high-speed camera is set up on the front and rear sides of the helicopter, with an accuracy of at least 1000 frames per second. The camera range of each camera includes the buoy on the same side of the helicopter and the 10m range of the buoy's side in the horizontal direction, and the buoy on the same side of the helicopter and the position of the rotor tail rotor in the vertical direction; Before the test, position labels are glued to the fuselage structure around the floats and numbered; the position labels include a series of labels arranged along the upper and lower defense lines, which are arranged at equal distances; a series of labels arranged longitudinally of the helicopter, which are arranged at equal distances; and typical extreme positions of the fit between the inflated and deployed floats and the fuselage; Before the test, position strip labels are glued on the ground around the buoy. The strip labels need to be arranged in the horizontal direction, and the scales are set symmetrically along the left and right sides of the fuselage.

7. The method according to claim 6, characterized in that: In step 4, the test verification includes: ① Carry out a check on the output judgment logic function of the flooding sensor of the emergency flotation system control box; ② Carry out manual start output function check of emergency flotation system control box; ③ Carry out output performance inspection of the flooding sensor of the emergency flotation system control box; ④ Carry out manual start output performance inspection of the emergency flotation system control box; ⑤ Carry out performance verification of the inflation and deployment function of the buoy assembly of the emergency flotation system.

8. The method according to claim 7, characterized in that: In step 5, the data interpretation process is as follows: Within 5 to 10 minutes after the buoy is inflated and deployed, use a pressure gauge to measure and record the pressure value of each inflated buoy; After the test, the video data collected by the high-definition camera is interpreted to determine whether the buoy inflation time meets the design requirements; the buoy inflation time is calculated from the time when the buoy starts to inflate and the buoy compartment fairing skin moves, until the buoy is fully deployed and formed; After the test, the video data collected by the high-definition camera is interpreted to check whether the left and right buoys are inflated simultaneously and symmetrically; check frame by frame whether the inflation process of the four buoys is balanced and whether the movement start time of the buoy compartment fairing skin is the same; and read the scale values ​​of the lateral extreme positions of the left and right buoys at the same time at a time interval of 0.5s, comparing them with the scales on the ground strip labels. If they are the same, it means that the left and right buoys are inflated simultaneously and symmetrically; After the test, the video data collected by the high-speed camera is interpreted to check whether the jettisoned objects interfere with the rotor and tail rotor. If no interference occurs, the position label attached to the fuselage structure can be referred to to determine whether a certain safety distance is maintained; After the test, the video data collected by the high-definition camera was interpreted and it was found that the protrusions on the fuselage structure or skin did not affect the inflation and formation of the buoys, and there was no phenomenon of protrusions puncturing the buoys; And through quantitative comparison between the labels on the fuselage and the design status, it is verified whether the spatial position and interference of the inflatable buoys are consistent with the design status.

Images