Helicopter emergency floating system buoy cabin safety analysis method and system
By employing systematic analysis methods, combined with CFD simulation, explicit dynamic simulation, and wind tunnel testing, the reliability and stability issues of rigid float pods during helicopter emergency floating processes were resolved, achieving a comprehensive assessment of the float pod's safety and reliability verification.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-09
- Publication Date
- 2026-03-27
AI Technical Summary
The lack of systematic analysis of the deformation characteristics and aerodynamic safety of rigid float pods in existing technologies makes it difficult to guarantee their reliability and stability during helicopter emergency floating.
By comprehensively considering various factors, including flight conditions, aerodynamic state, and structural deformation, and employing methods such as CFD simulation, explicit dynamic simulation, wind tunnel testing, and flight testing, the safety of the floatation pod is fully evaluated to ensure its reliability and stability under different operating conditions.
It enables comprehensive, accurate and reliable assessment of the pontoon cabin under different operating conditions, ensuring its safety during helicopter emergency floatation, reducing verification costs and improving design innovation.
Smart Images
Figure CN121744482A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of helicopter safety design technology, and discloses a systematic analysis method and system for the deformation characteristics and aerodynamic safety of the float cabin of an emergency flotation system. Background Technology
[0002] When helicopters are performing missions such as maritime patrol, search and rescue, and oil platform transport, they may encounter engine failure or other malfunctions that prevent them from returning to base, necessitating an emergency water landing. To improve the safety of helicopter operations at sea, countries typically equip helicopters with emergency flotation systems. These systems generally consist of inflatable floats surrounding the fuselage and corresponding inflatable components.
[0003] The inflatable floats are normally folded and stored inside the float compartment. The rigid float compartment design allows for more compact integration with the helicopter fuselage structure; its rigid canopy allows for a precise streamlined design, significantly reducing flight drag and thus optimizing the helicopter's speed, range, and fuel efficiency. Based on these advantages, rigid float compartments are widely used in practical applications. Summary of the Invention
[0004] Purpose of the invention: In view of the lack of systematic analysis on the deformation characteristics and aerodynamic safety of rigid float pods, this invention provides a method and system for analyzing the safety of float pods in helicopter emergency flotation systems. By comprehensively considering multiple factors, the safety of the float pod under different operating conditions is fully evaluated to ensure its reliability and stability during helicopter emergency flotation.
[0005] To address the above-mentioned technical issues, the present invention provides the following technical solution: In a first aspect, the present invention provides a method for safety analysis of the floatation chamber of a helicopter emergency flotation system, which includes the following steps: Based on the helicopter's flight conditions, accurately determine the harsh operating conditions and aerodynamic state at the float compartment; In response to the harsh working conditions and aerodynamic state at the pontoon hull, stress analysis and verification of the pontoon hull cover and its connection strength were conducted. The deformation of the pontoon hull was simulated and analyzed to obtain the deformation amount of the pontoon hull; Conduct wind and floathouse strength tests under harsh flight conditions; Conduct inflatable deployment tests of the pontoons and perform actual measurements on the deformation of the pontoon compartments; The helicopter was fitted with a floatation pod, and flight test systems were validated.
[0006] As a further technical solution of the present invention: based on the helicopter flight conditions, the harsh operating conditions and aerodynamic state at the float compartment are accurately determined, specifically as follows: The maximum aerodynamic pressure, suction force, lateral force distribution and corresponding working conditions of the surface of the pontoon cabin cover are extracted through CFD simulation by comprehensively considering the helicopter shape, geometric parameters of the pontoon cabin shape and installation position, and fully combining the helicopter flight conditions, so that the severe working conditions and aerodynamic force states at the pontoon cabin are accurately determined. The helicopter flight conditions are high-speed forward flight, high-power climbing and hovering.
[0007] As a further technical solution of the present application: for the severe working conditions and aerodynamic force states at the pontoon cabin, stress analysis and checking are performed on the pontoon cabin cover and its connection strength, specifically: For each determined aerodynamic force state, a stress model of the pontoon cabin cover and its connection structure is constructed; The anti-separation ability of the cabin cover under the limit aerodynamic load is checked to ensure that the cabin cover will not separate from the pontoon cabin base under the action of aerodynamic force, and the cabin cover and its fixing point can withstand the maximum aerodynamic pressure, suction force and lateral force under the severe working conditions; At the same time, according to the stress analysis and checking results, the severe working conditions that cause the minimum strength margin of the local connection of the cabin cover and the maximum load borne by the cabin cover are identified, which are taken as the core verification points of subsequent tests.
[0008] As a further technical solution of the present application: deformation simulation calculation analysis of the pontoon cabin is carried out to obtain the deformation amount of the pontoon cabin, specifically: The inflated pontoon will extrude the inner wall of the pontoon cabin cover and the pontoon cabin base at the inflation moment, and then cause the deformation of the pontoon cabin; when the extrusion force exceeds the connection force between the pontoon cabin cover and the pontoon cabin base, the pontoon cabin cover will quickly pop off from the pontoon cabin base; The process of pontoon cabin inflation deformation and cabin cover pop-off can be simulated by high-precision simulation using explicit dynamics combined with fluid-structure coupling to simulate the dynamic extrusion process of the cabin cover and cabin wall at the inflation moment of the folded pontoon. The deformation area of the cabin body is predicted through the simulation, and then it is judged whether the deformed pontoon cabin will interfere with the adjacent key systems.
[0009] As a further technical solution of the present application: blowing and pontoon cabin strength test under severe flight conditions are carried out, specifically: For various severe helicopter flight conditions, the working conditions of the determined minimum strength margin of the local connection of the pontoon cabin cover and the maximum load borne by the cabin cover are selected as the key points, and wind tunnel tests are carried out.
[0010] As a further technical solution of the present application: when designing the test bench, the pontoon cabin peripheral mounting structure and local skin are designed according to the 1:1 scale of the aircraft structure; the test bench is manufactured, and the attitude angle thereof can be adjusted; The wind tunnel adopts horizontal blowing mode, and the pitch, roll and yaw angles of the test bench can be adjusted to simulate the direction of the buoy cabin relative to the airflow under the flight condition. By setting the limit wind tunnel blowing state, the test and examination of the buoy cabin and its connecting strength are carried out.
[0011] As a further technical solution of the present application: the inflation and deployment test of the buoy is carried out, and the actual measurement of the deformation of the buoy cabin is carried out, specifically: Force sensors are arranged at the key positions of the deformation of the buoy cabin, which are used to measure the acting force when the buoy cabin deforms to a certain degree, and then the acting force of the buoy cabin on the key structure / system on the machine is obtained; The transmission force of the inflatable buoy cabin on the key structure / system on the machine is deduced reversely through the sensor; And whether the buoy cabin interferes with the key structure / system on the machine is judged; If there is no interference, it indicates that the buoy cabin meets the design requirements; If interference occurs, the interference collision force recorded by the force sensor is analyzed; If the key structure / system on the machine can withstand the acting force, the buoy cabin still meets the design requirements; at the same time, the deformation condition of the buoy cabin during the inflation and deployment process of the buoy is recorded by a camera.
[0012] As a further technical solution of the present application: the helicopter is installed with the buoy cabin, and the flight test system verification is carried out, specifically: The folded buoy and the buoy cabin in the installed state without inflation are tested for reliability under various extreme conditions of the whole machine; The inflation and deployment test of the buoy in the air is carried out, and the interference risk of the deformation of the buoy cabin on the key structure / system on the machine is monitored; The extreme conditions are high-speed forward flight, high-power climb and hovering.
[0013] In the second aspect, the present application provides a safety analysis system for a buoy cabin of a helicopter emergency floating system, which comprises: A working condition analysis module accurately determines the severe working condition and aerodynamic state at the buoy cabin according to the flight working condition of the helicopter; A strength analysis and checking module carries out stress analysis and checking of the buoy cabin cover and its connecting strength according to the severe working condition and aerodynamic state at the buoy cabin, and carries out blowing and buoy cabin strength test and examination under severe flight working condition; A deformation analysis and checking module carries out deformation simulation calculation and analysis of the buoy cabin to obtain the deformation amount of the buoy cabin; carries out the inflation and deployment test of the buoy, and actually measures the deformation condition of the buoy cabin; A flight verification module carries out flight test system verification by installing the buoy cabin on the helicopter.
[0014] In summary, the beneficial effects of the present application are as follows: The present application comprehensively evaluates the safety of the pontoon cabin under different working conditions through a systematic analysis method, ensuring its reliability and stability during the helicopter emergency floating process. The specific advantages include: 1. Comprehensive: Considering various factors such as flight conditions, aerodynamic state, and structural deformation, the safety of the pontoon cabin is comprehensively evaluated.
[0015] 2. Accuracy: With high-precision simulation technology and experimental verification, the accuracy of the analysis results is ensured.
[0016] 3. Reliability: Through flight test verification, the reliability of the pontoon cabin in actual use is ensured.
[0017] 4. Innovation: The method of the present application fills the gap in the safety analysis of the pontoon cabin in the prior art, and has significant innovation.
[0018] 5. The test verification covers the minimum strength margin working condition and the limit boundary of the cabin cover bearing the maximum load. The verification is sufficient and greatly reduces the verification cost.
[0019] The present application will be further described in detail in conjunction with the accompanying drawings of the embodiments. BRIEF DESCRIPTION OF DRAWINGS
[0020] Figure 1 The flow chart of the safety analysis of the pontoon cabin of the helicopter emergency floating system of the present application.
[0021] Figure 2 The installation schematic diagram of the force sensor for the pontoon inflation and deployment test of the present application.
[0022] Figure 3 The installation actual diagram of the force sensor for the pontoon inflation and deployment test of the present application.
[0023] Figure 4 The installation schematic diagram of the camera for the pontoon inflation and deployment test of the present application. DETAILED DESCRIPTION
[0024] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme of the embodiments of the present application will be described in more detail below in conjunction with the drawings of the embodiments of the present application.
[0025] In the drawings, the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all of the embodiments.
[0026] The embodiments described below with reference to the drawings are exemplary and are intended to be illustrative of the present application and are not to be construed as limiting the present application. All other embodiments which would be obtained by persons of ordinary skill in the art based on the embodiments of the present application, without making an inventive effort, are within the scope of the present application.
[0027] The embodiments of the present application are described below with reference to the drawings. Figures 1-4 The embodiments of the present application are described below with reference to the drawings.
[0028] Embodiment 1 The present application discloses a safety analysis method for a float tank cabin of a helicopter emergency floating system, comprising the following steps: Step 1: According to the flight conditions of the helicopter, the critical working conditions and aerodynamic force states at the float tank cabin are accurately determined.
[0029] The geometric parameters such as the shape of the helicopter and the shape of the float tank cabin and the installation position are comprehensively considered, and the flight conditions (such as high-speed forward flight, high-power climb, hovering, etc.) of the helicopter are fully combined, and through CFD simulation, the maximum aerodynamic pressure, suction force, and lateral force distribution of the float tank cabin cover surface and the corresponding working conditions are extracted, so as to accurately determine the critical working conditions and aerodynamic force states at the float tank cabin.
[0030] Step 2: According to the critical working conditions and aerodynamic force states at the float tank cabin, the stress analysis and checking of the float tank cover and its connection strength are carried out.
[0031] According to the aerodynamic force states determined in step 1, a stress model of the float tank cover and its connection structure is constructed. The anti-separation ability of the cabin cover under the limit aerodynamic load is checked to ensure that the cabin cover will not separate from the float tank bottom under the action of aerodynamic force, and the cabin cover and its fixed point need to be able to withstand the maximum aerodynamic pressure, suction force and lateral force under the above critical working conditions. At the same time, according to the stress analysis and checking results, the critical working conditions causing the minimum strength margin of the local connection of the cabin cover and the maximum load bearing of the cabin cover are identified, which are taken as the core verification points for subsequent tests.
[0032] Step 3: Deformation simulation calculation and analysis of the float tank The folded float in the float tank will extrude the inner wall of the float tank cover and the float tank bottom when inflated, and then cause the deformation of the float tank. When the extrusion force exceeds the connection force between the float tank cover and the float tank bottom, the float tank cover will quickly pop off from the float tank bottom.
[0033] The process of inflation deformation of the float tank and the cabin cover popping off can be simulated by using explicit dynamics combined with fluid-structure coupling (ALE / CEL) for high-precision simulation to simulate the dynamic extrusion process of the cabin cover and the cabin wall by the folded float at the inflation moment. Through the simulation, the deformation area of the cabin is predicted, and then it is judged whether the deformed float tank will interfere with the adjacent control rod system and other key systems.
[0034] Step four: carry out the blowing and buoyancy cabin strength test under the severe flight condition.
[0035] For various severe helicopter flight conditions, the minimum strength margin of the local connection of the buoyancy cabin cover determined in step two and the condition of the cover bearing the maximum load are selected as the focus to carry out the wind tunnel test.
[0036] When designing the test bench, the peripheral installation structure and the local skin of the buoyancy cabin are designed according to the 1:1 ratio of the aircraft structure. The test bench is manufactured, and the attitude angle thereof can be adjusted.
[0037] The wind tunnel adopts horizontal blowing, and the pitch, roll and yaw angles of the test bench can be adjusted to simulate the direction of the buoyancy cabin relative to the airflow under the flight condition. By setting the limit wind blowing state, the test and examination of the strength of the buoyancy cabin and its connection are carried out.
[0038] Step five: carry out the buoyancy inflation and deployment test, and actually measure the deformation of the buoyancy cabin.
[0039] Force sensors are arranged at the key positions of the deformation of the buoyancy cabin, such as the adjacent control rod system, to measure the acting force when the buoyancy cabin deforms to a certain degree (i.e. touches the adjacent control rod system, etc.), so as to obtain the acting force of the buoyancy cabin on the key structure / system on the machine. The transmission force of the inflatable buoyancy cabin on the key structure / system on the machine is deduced reversely through the sensor. Whether the buoyancy cabin interferes with the key structure / system on the machine is judged. If there is no interference, it indicates that the buoyancy cabin meets the design requirements. If there is interference, the interference collision force recorded by the force sensor is analyzed. If the key structure / system on the machine can withstand the force, the buoyancy cabin still meets the design requirements. At the same time, the deformation of the buoyancy cabin during the inflation and deployment of the buoyancy is recorded by a camera.
[0040] Step six: the helicopter is installed with the buoyancy cabin, and the flight test system verification is carried out.
[0041] The folded buoyancy and the buoyancy cabin in the installed state without inflation are tested for reliability under various limit conditions (high-speed forward flight, high-power climb, hovering, etc.) of the whole machine. The inflation and deployment test of the buoyancy in the air is carried out to monitor the interference risk of the deformation of the buoyancy cabin on the key structure / system on the machine.
[0042] Embodiment 2 The application discloses a safety analysis method for a buoyancy cabin of a helicopter emergency floating system, which comprises the following steps: Step one: determine the severe condition and aerodynamic force state Input parameters: helicopter shape parameters, buoyancy cabin shape parameters, installation position, flight conditions (including speed, height, attitude, etc.).
[0043] Analysis tool: Computational Fluid Dynamics (CFD) software.
[0044] Flight conditions include: high-speed forward flight, high-power climb, hovering, etc.
[0045] Output results: severe conditions and aerodynamic state of the buoy cabin (including aerodynamic pressure, suction, lateral force, etc.).
[0046] Step two: force analysis and checking Input parameters: material parameters, size parameters, and force state of the buoy cabin cover and connecting parts.
[0047] Analysis tool: Establish a finite element model of the cabin cover and use finite element analysis (FEA) software. Analyze each strict condition.
[0048] Output results: strength checking results of the buoy cabin cover and connecting parts, determine the minimum strength margin and the severe condition of the cabin cover under maximum load.
[0049] Step three: deformation simulation calculation Input parameters: buoy inflation pressure, buoy cabin structure parameters.
[0050] Analysis tool: Explicit dynamic simulation software (such as ABAQUS / Explicit) combined with fluid-structure coupling (ALE / CEL).
[0051] Output results: simulation results of the buoy cabin inflation deformation process, including cabin deformation, stress distribution, etc.
[0052] Step four: wind blowing and strength test Manufacture a 1:1 test adjustable attitude test bench, install the real buoy cabin and surrounding skin.
[0053] Adjust the bench to the attitude of step two, simulate the flight conditions that the buoy cabin bears.
[0054] Apply wind speed to the design limit and consider safety margin, conduct wind blowing test on the buoy cabin, record the deformation strength performance of the buoy cabin under extreme conditions.
[0055] Step five: buoy inflation deployment test Use the test bench in step four, arrange force sensors at key positions of the cabin body (such as side walls, connecting parts). Use a camera (for example, 120fps) to record the buoy inflation deployment process. Record the deformation of the buoy cabin during the buoy inflation deployment process and measure the force of the buoy cabin wall. Output: key data of buoy cabin inflation deformation, including deformation, force, etc.
[0056] Step six: flight system test verification The float assembly is installed on the helicopter, flight tests under various extreme conditions are carried out, and the reliability of the float cabin is verified.
[0057] Air inflation instructions are executed, and the safety influence of the deformation of the float cabin on the operating system possibly interfering with the float after the float is unfolded is verified.
[0058] Up to now, the purpose of the application is achieved.
[0059] The above only is the preferred embodiment of the application, and does not limit the application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the application shall be included in the protection scope of the application.
Claims
1. A method for analyzing the safety of a float pod of a helicopter emergency flotation system, characterized in that, The method comprises the following steps: According to the helicopter flight conditions, the severe conditions and aerodynamic force state of the float chamber are accurately determined; According to the severe conditions and aerodynamic force state of the float chamber, stress analysis and checking of the float chamber cover and its connection strength are carried out; The deformation simulation calculation analysis of the float chamber is carried out to obtain the deformation amount of the float chamber; The blowing and float chamber strength test under severe flight conditions are carried out; The float inflation deployment test is carried out, and the actual measurement of the deformation of the float chamber is carried out; The helicopter is installed with the float chamber, and the flight test system verification is carried out.
2. The method for analyzing the safety of the buoyancy chamber of the emergency floatation system of a helicopter according to claim 1, characterized in that, According to the helicopter flight conditions, the severe conditions and aerodynamic force state of the float chamber are accurately determined, specifically: Considering the helicopter shape, the geometric parameters of the float chamber and the installation position, and fully combining the helicopter flight conditions, the maximum aerodynamic pressure, suction force, lateral force distribution and the corresponding working conditions of the float chamber cover surface are extracted through CFD simulation, so that the severe conditions and aerodynamic force state of the float chamber are accurately determined; Among them, the helicopter flight conditions are high-speed forward flight, high-power climb and hovering.
3. The method of claim 1, wherein, According to the severe conditions and aerodynamic force state of the float chamber, stress analysis and checking of the float chamber cover and its connection strength are carried out, specifically: For each aerodynamic state determined, a stress model of the float chamber cover and its connection structure is constructed; The separation resistance of the chamber cover under the limit aerodynamic load is checked to ensure that the chamber cover will not separate from the float chamber base under the action of aerodynamic force, and the chamber cover and its fixed point can withstand the maximum aerodynamic pressure, suction force and lateral force under the severe conditions; At the same time, according to the stress analysis and checking results, the severe conditions causing the minimum strength margin of the local connection of the chamber cover and the maximum load bearing of the chamber cover are identified, which are taken as the core verification points of the subsequent test.
4. The method of claim 1, wherein, The deformation simulation calculation analysis of the float chamber is carried out to obtain the deformation amount of the float chamber, specifically: The folded float in the float chamber will extrude the inner wall of the float chamber cover and the float chamber base when inflated, which will cause the deformation of the float chamber; when the extrusion force exceeds the connection force between the float chamber cover and the float chamber base, the float chamber cover will quickly pop off from the float chamber base; The process of float chamber inflation deformation and chamber cover pop-off can be simulated by using explicit dynamics combined with fluid-structure coupling to simulate the dynamic extrusion process of the chamber cover and chamber wall at the inflation moment of the folded float; Through the simulation, the deformation area of the chamber body is predicted, and it is judged whether the deformed float chamber will interfere with the adjacent key systems.
5. The method for analyzing the safety of the buoyancy chamber of the emergency floatation system of a helicopter according to claim 3, characterized in that, The blowing and float chamber strength test under severe flight conditions are carried out, specifically: For various severe helicopter flight conditions, the determined conditions of the minimum strength margin of the local connection of the float chamber cover and the maximum load bearing of the chamber cover are selected as the key points, and the wind tunnel test is carried out.
6. The method for safety analysis of the float pod of the helicopter emergency floatation system according to claim 5, characterized in that, When designing the test bench, the float chamber peripheral mounting structure and local skin are designed according to the 1:1 scale of the aircraft structure; the test bench is manufactured, and the attitude angle can be adjusted; The wind tunnel adopts horizontal blowing mode, and the pitch, roll and yaw angles of the test bench can be adjusted to simulate the direction of the float chamber relative to the airflow under flight conditions; Through setting the limit wind tunnel blowing state, the test of the float chamber and its connection strength is carried out.
7. The method of claim 1, wherein, The float inflation deployment test is carried out, and the deformation of the float cabin is actually measured, specifically: Force sensors are arranged at key positions of the float cabin deformation to measure the force borne by the float cabin when it deforms to a certain extent, and then the force of the float cabin on the key structure / system on the machine is obtained; The force of the inflatable float cabin on the key structure / system on the machine is deduced reversely through the sensor; And whether the float cabin interferes with the key structure / system on the machine is judged; If there is no interference, it means that the float cabin meets the design requirements; If there is interference, the interference collision force recorded by the force sensor is analyzed; If the key structure / system on the machine can bear the force, the float cabin still meets the design requirements; at the same time, the deformation of the float cabin during the inflation deployment of the float is recorded by the camera.
8. The method of safety analysis of the buoyancy cabin of the emergency floatation system of a helicopter according to claim 1, characterized in that, The helicopter installs the float cabin, and carries out flight test system verification, specifically: The folded float and the float cabin in the un-inflated state are tested for reliability under various extreme conditions of the whole machine; The float inflation deployment test is carried out, and the deformation of the float cabin is actually measured, specifically: The force sensors are arranged at key positions of the float cabin deformation to measure the force borne by the float cabin when it deforms to a certain extent, and then the force of the float cabin on the key structure / system on the machine is obtained; 9. A safety analysis system for a float pod of a helicopter emergency flotation system, characterized in that, The force of the inflatable float cabin on the key structure / system on the machine is deduced reversely through the sensor; And whether the float cabin interferes with the key structure / system on the machine is judged; If there is no interference, it means that the float cabin meets the design requirements; If there is interference, the interference collision force recorded by the force sensor is analyzed; If the key structure / system on the machine can bear the force, the float cabin still meets the design requirements; at the same time, the deformation of the float cabin during the inflation deployment of the float is recorded by the camera. The helicopter installs the float cabin, and carries out flight test system verification, specifically: The folded float and the float cabin in the un-inflated state are tested for reliability under various extreme conditions of the whole machine; The float inflation deployment test is carried out, and the deformation of the float cabin is actually measured, specifically: The force sensors are arranged at key positions of the float cabin deformation to measure the force borne by the float cabin when it deforms to a certain extent, and then the force of the float cabin on the key structure / system on the machine is obtained; The force of the inflatable float cabin on the key structure / system on the machine is deduced reversely through the sensor; And whether the float cabin interferes with the key structure / system on the machine is judged; If there is no interference, it means that the float cabin meets the design requirements; If there is interference, the interference collision force recorded by the force sensor is analyzed; If the key structure / system on the machine can bear the force, the float cabin still meets the design requirements; at the same time, the deformation of the float cabin during the inflation deployment of the float is recorded by the camera. The helicopter installs the float cabin, and carries out flight test system verification, specifically: The folded float and the float cabin in the un-inflated state are tested for reliability under various extreme conditions of the whole machine; The float inflation deployment test is carried out, and the deformation of the float cabin is actually measured, specifically: The force sensors are arranged at key positions of the float cabin deformation to measure the force borne by the float cabin when it deforms to a certain extent, and then the force of the float cabin on the key structure / system on the machine is obtained; The force of the inflatable float cabin on the key structure / system on the machine is deduced reversely through the sensor; And whether the float cabin interferes with the key structure / system on the machine is judged; If there is no interference, it means that the float cabin meets the design requirements; If there is interference, the interference collision force recorded by the force sensor is analyzed; If the key structure / system on the machine can bear the force, the float cabin still meets the design requirements; at the same time, the deformation of the float cabin during the inflation deployment of the float is recorded by the camera. The helicopter installs the float cabin, and carries out flight test system verification, specifically: The folded float and the float cabin in the un-inflated state are tested for reliability under various extreme conditions of the whole machine; The float inflation deployment test is carried out, and the deformation of the float cabin is actually measured, specifically: The force sensors are arranged at key positions of the float cabin deformation to measure the force borne by the float cabin when it deforms to a certain