Emergency floating device and method for rotorcraft

Abstract

The invention provides a rotorcraft emergency floating device and method.The rotorcraft emergency floating device comprises a buoy assembly and an inflation assembly, and the buoy assembly comprises a right front buoy assembly, a left front buoy assembly and a rear buoy assembly and is used for providing buoyancy and floating stability for a rotorcraft; the inflation assembly comprises a cylinder valve assembly and a pipeline assembly, is used for inflating the buoy assembly and has a manual / dampening automatic starting function; a right front buoy assembly and a left front buoy assembly are symmetrically arranged on the left and right sides of the front machine body, and are cylindrical in packaging shape; the right front buoy assembly and the left front buoy assembly are in a capsule shape when being inflated and unfolded. The rear buoy assembly is of a flat box body structure in a packaging state and has a good aerodynamic configuration; the rear buoy assembly is of a three-buoy structure connected side by side in the inflated unfolding state.

Description

TECHNICAL FIELD

[0001] The application relates to the field of rotorcraft water emergency ditching, in particular to a rotorcraft emergency floating device and method. BACKGROUND

[0002] When a rotorcraft needs to be ditched on water due to failure, an emergency floating device is needed to provide buoyancy for the rotorcraft, thereby providing sufficient escape time for the pilot and creating conditions for the salvage recovery of the rotorcraft. At present, there is no application of rotorcraft emergency floating device. Unlike general helicopters, rotorcrafts have the characteristics of small size, light weight, high safety, stable low-altitude flight, etc. However, the fuselage width is narrow, the tail beam is low, the installation conditions are limited, and the conventional float configuration cannot provide sufficient righting moment. Under the influence of wind, waves, ditching water attitude and other factors, the rotorcraft may overturn, and the weight, floating stability and inflation time of the emergency floating device are required to be high. SUMMARY

[0003] The purpose of the application is to provide a rotorcraft emergency floating device, which adopts a triangular distribution configuration of three floats, uses a one-piece bottle valve assembly to inflate three float assemblies synchronously, can realize manual start / automatic start on water, has the advantages of large righting moment, good floating stability, short inflation time, light weight, etc., and can be applied to various small aircrafts, and has a wide application prospect.

[0004] Technical scheme: In a first aspect, the application provides a rotorcraft emergency floating device, comprising a float assembly and an inflation assembly, wherein: The float assembly comprises a right front float assembly 1, a left front float assembly 2 and a rear float assembly 3, and is used to provide buoyancy and floating stability for the rotorcraft; the inflation assembly comprises a bottle valve assembly 4 and a pipeline assembly 5, and is used to inflate the float assembly and has a manual / automatic start on water function; The right front float assembly 1 and the left front float assembly 2 are arranged symmetrically on the front fuselage, and the envelope shapes of the right front float assembly 1 and the left front float assembly 2 are both cylindrical; the inflated and expanded state of the right front float assembly 1 and the left front float assembly 2 is capsule-shaped; the envelope state of the rear float assembly 3 is a flat box structure, which has a good aerodynamic shape; the inflated and expanded state of the rear float assembly 3 is a three-float structure connected side by side.

[0005] Specifically, both the right front pontoon assembly 1 and the left front pontoon assembly 2 include a flexible skin 6 for the front pontoon assembly, a U-shaped connecting frame 7 for the front pontoon assembly, and an airbag 8 for the front pontoon assembly. The airbag 8 is connected to the U-shaped connecting frame 7 for the front pontoon assembly via adhesive. Two inflation / deflation valves 9 are arranged on the outer surface of the airbag 8 for inflating / deflating the pontoon and for constant pressure monitoring. The flexible skin 6 for the front pontoon assembly is connected to the U-shaped connecting frame 7 for the front pontoon assembly via several screws. At the same time, Velcro fasteners are arranged on the edge for folding and sealing the airbag 8 after vacuuming.

[0006] Specifically, the front float assembly airbag 8 is divided into a first compartment 59 and a second compartment 60 with independent airtightness by a partition plate. When any single compartment is damaged, the front float assembly airbag 8 can still provide sufficient buoyancy. The front float assembly U-shaped connecting frame 7 is connected to the fuselage crossbeam by an adapter 11 and bolts 10.

[0007] Specifically, the bottle valve assembly 4 includes a pull lock 24, a release valve 25, a three-way drum connector 26, and a bottle body 27, for storing and releasing high-pressure gas.

[0008] Specifically, the piping assembly 5 includes 3 one-way drum joints 55, 3 air inlet valves 56, 3 two-way drum joints 57, and 3 flow-limiting air inlet valves 58, with each joint connected by a flexible hose.

[0009] Secondly, this application provides an emergency flotation method for a rotorcraft, wherein the method is applied to the emergency flotation device for a rotorcraft as described above, and the method includes: Step 1: In an emergency, when making a forced descent on water, pull the cable 24 on the cylinder valve assembly 4 before landing on the water. The cylinder valve assembly 4 will release high-pressure gas. If the pilot is unable to manually start the valve assembly, the cylinder valve assembly 4 can automatically release gas after entering the water by melting the internal water-sensitive element 41. Step 2: High-pressure gas passes through pipeline assembly 5, and after throttling and diversion, is supplied to the right front float assembly 1, left front float assembly 2, and rear float assembly 3; Step 3: During the inflation of the right front float assembly 1, left front float assembly 2, and rear float assembly 3, the sealing constraints are released simultaneously. After the final inflation and formation, they provide buoyancy and stable floating attitude for the rotorcraft that has been forced to land on the water, facilitating the timely and safe evacuation of the crew.

[0010] Specifically, step 1 includes two working modes: manual start and automatic start upon water immersion. When the pull lock 24 is pulled in manual mode, the ball at the end of the pull lock disengages from the pull lock seat 44. The steel ball 46 and the clamping column 45 move to the right under the squeezing action of the firing pin spring 29 and the firing pin 30. The firing pin spring 29 pushes the firing pin 30 to pierce the diaphragm 33. The gas in the secondary chamber 47 flows out quickly through the through hole on the secondary screw plug 28. The valve core 39 moves to the left until the first small diameter sealing ring 50 seals with the release valve housing 34. The high pressure gas is quickly released through the three-way drum joint 52. In the automatic start mode when wet, the water-sensitive element 41 melts upon contact with water. The steel ball 46 and the clamping column 45 move to the right under the squeezing action of the impact spring 29 and the impact needle 30. The impact spring 29 pushes the impact needle 30 to pierce the diaphragm 33. The gas in the secondary chamber 47 flows out quickly through the through hole on the secondary screw plug 28. Due to the large cross-sectional area of ​​the valve core 39, under the push of the high-pressure gas, the valve core 39 moves quickly to the left until the first small diameter sealing ring 50 seals with the release valve housing 34. The high-pressure gas is then quickly released through the three-way drum joint 26.

[0011] Specifically, step 2 includes: High-pressure gas flows out through the rear float vent 52, left front float vent 53, and right front float vent 54 on the three-way drum joint 26, flows into the second compartment 60 through the hose, two-way drum joint 57, and flow-limiting inlet valve 58, and then flows into the first compartment 59 through the hose, one-way drum joint 55, and inlet valve 56, thereby ensuring uniform flow in the six independent airtight compartments of the right front float assembly 1, left front float assembly 2, and rear float assembly 3.

[0012] Specifically, step 3 includes: Step 31: The right front float assembly 1 and the left front float assembly 2 are inflated to release the constraint of the flexible skin 6 of the front float assembly, and are inflated into a capsule shape, which helps to reduce the water load during the forced landing process. Step 32: The rear float assembly 3 is inflated to release the constraints of the upper skin 15 and the lower skin 18 of the rear float assembly, and inflates to form a three-float configuration that is connected side by side, which helps to reduce the floats from overturning during the forced landing process.

[0013] In summary, this invention provides an emergency flotation device and method for rotorcraft. The overall structure adopts a triangular configuration with three floats, offering advantages such as high righting moment and good floating stability. The valve assembly uses a mechanical actuation method and integrates a water-sensitive element, enabling manual or automatic activation upon water contact. A single piping assembly simultaneously inflates the three floats, totaling six sealed compartments, featuring lightweight construction, rapid inflation, and uniform flow distribution. This invention can be applied to various small aircraft and has broad application prospects. Attached Figure Description

[0014] Figure 1This is a schematic diagram of the installation of the emergency flotation device of the present invention on a rotorcraft, in its packaged state; Figure 2 This is a schematic diagram of the emergency flotation device of the present invention installed on a rotorcraft in its unfolded state; Figure 3 This is an unfolded schematic diagram of the front float assembly structure of the present invention; Figure 4 This is a diagram showing the encapsulated state of the front float assembly and its connection structure with the fuselage of the present invention. Figure 5 This is an unfolded schematic diagram of the rear float assembly structure of the present invention; Figure 6 This is a schematic diagram of the skin of the rear float assembly of the present invention flipping up; Figure 7 This is an exploded view of the airbag assembly of the rear float of the present invention; Figure 8 This is a schematic diagram of the annular adhesive sheet of the rear float assembly of the present invention; Figure 9 This is a diagram showing the encapsulated state of the rear float assembly and its connection structure with the fuselage of the present invention. Figure 10 This is a structural diagram of the bottle valve assembly of the present invention; Figure 11 This is a schematic diagram of the internal structure of the release valve of the bottle valve assembly of the present invention; Figure 12 This is a schematic diagram of the manual start principle of the bottle valve assembly of the present invention; Figure 13 This is a schematic diagram of the automatic start-up principle of the bottle valve assembly of the present invention when it comes into contact with water; Figure 14 This is a schematic diagram of the three-way drum-shaped connector of the present invention; Figure 15 This is a schematic diagram of the piping assembly of the present invention; Figure 16 This is a schematic diagram of the working principle of the emergency flotation device of the present invention; Among them, 1-right front pontoon assembly, 2-left front pontoon assembly, 3-rear pontoon assembly, 4-valve assembly, 5-piping assembly, 6-front pontoon assembly flexible skin, 7-front pontoon assembly U-shaped connecting frame, 8-front pontoon assembly airbag, 9-inflation / deflation valve, 10-connecting bolt, 11-adapter, 12-first rear pontoon assembly airbag, 13-second rear pontoon assembly airbag, 14-third rear pontoon assembly airbag, 15-rear pontoon assembly upper skin, 16- 17-L-shaped support plate, 18-U-shaped connecting frame for rear float assembly, 19-lower skin of rear float assembly, 20-screw, 21-ring adhesive tape, 22-ring adhesive piece, 23-ring stitch, 24-zipper, 25-release valve, 26-three-way drum connector, 27-cylinder body, 28-secondary plug, 29-impact spring, 30-impact, 31-impact housing, 32-sealing block, 33-diaphragm, 34-release valve housing, 35-main plug, 36-valve core spring, 37-safety valve, 38-gas cylinder filling / draining valve, 39- - Valve core, 40- Pressure gauge, 41- Water-sensitive element, 42- Ejector column, 43- Water-sensitive housing, 44- Lock seat, 45- Tightening column, 46- Steel ball, 47- Secondary chamber, 48- Main chamber, 49- Large diameter sealing ring, 50- First small diameter sealing ring, 51- Second small diameter sealing ring, 52- Rear float vent, 53- Left front float vent, 54- Right front float vent, 55- One-way drum connector, 56- Intake valve, 57- Two-way drum connector, 58- Flow-limiting intake valve, 59- First compartment, 60- Second compartment. Detailed Implementation

[0015] This invention provides an emergency flotation device for rotorcraft. The overall structure adopts a triangular configuration with three floats, offering advantages such as high righting moment and good buoyancy stability. The valve assembly uses a mechanical actuation method and integrates a water-sensitive element, enabling manual or automatic activation upon water contact. A single piping assembly simultaneously inflates the three floats, totaling six sealed compartments, featuring lightweight construction, rapid inflation, and uniform flow distribution. This invention can be applied to various small aircraft and has broad application prospects.

[0016] The present invention will be further described in detail below through specific embodiments: Example 1 like Figures 1-2 As shown, this application provides an emergency flotation device for a rotorcraft, including a float assembly and an inflation assembly, wherein: The float assembly includes a right front float assembly 1, a left front float assembly 2, and a rear float assembly 3, which are used to provide buoyancy and floating stability for the rotorcraft; the inflation assembly includes a bottle valve assembly 4 and a pipeline assembly 5, which are used to inflate the float assembly and have manual / automatic start-up functions upon water contact. The right front float assembly 1 and left front float assembly 2 are symmetrically arranged on the left and right sides of the forward fuselage, both of which are cylindrical in shape. When inflated and deployed, the right front float assembly 1 and left front float assembly 2 are capsule-shaped. The rear float assembly 3 has a flat box-like structure in its inflated and deployed state, exhibiting excellent aerodynamic shape. When inflated and deployed, the rear float assembly 3 is a three-float structure connected side-by-side, characterized by its small vertical dimensions and resistance to tipping over.

[0017] Specifically, such as Figure 3 As shown, both the right front pontoon assembly 1 and the left front pontoon assembly 2 include a flexible skin 6, a U-shaped connecting frame 7, and an airbag 8. The airbag 8 is connected to the U-shaped connecting frame 7 via adhesive. Two inflation / deflation valves 9 are arranged on the outer surface of the airbag 8 for inflating / deflating the pontoon and for pressure monitoring. The flexible skin 6 is connected to the U-shaped connecting frame 7 via several screws, and Velcro fasteners are provided along its edges for folding and sealing the airbag 8 after vacuuming.

[0018] like Figure 15 As shown, the front float assembly airbag 8 is divided into a first compartment 59 and a second compartment 60 with independent airtightness by a bulkhead. When any single compartment is damaged, the front float assembly airbag 8 can still provide sufficient buoyancy.

[0019] like Figure 4 As shown, the U-shaped connecting frame 7 of the front float assembly is connected to the body beam via an adapter 11 and bolts 10.

[0020] like Figure 5 As shown, the rear pontoon assembly 3 includes a first rear pontoon assembly airbag 12, a second rear pontoon assembly airbag 13, a third rear pontoon assembly airbag 14, a rear pontoon assembly upper skin 15, an L-shaped support plate 16, a rear pontoon assembly U-shaped connecting frame 17, and a rear pontoon assembly lower skin 18.

[0021] like Figure 6 As shown, the two upper skins 15 of the rear float assembly and the four L-shaped support plates 16 are connected to the U-shaped connecting frame 17 of the rear float assembly by 10 screws 19. When the rear float assembly 3 is in the folded and sealed state, the upper skin 15 of the rear float assembly is close to the L-shaped support plate 16. The inner side of the flange of the upper skin 15 of the rear float assembly is made of nylon Velcro, and the outer side of the flange of the lower skin 18 of the rear float assembly is made of nylon Velcro. The upper skin 15 and the lower skin 18 of the rear float assembly together form a flat box structure.

[0022] like Figure 5As shown, when the rear pontoon assembly 3 is in the inflated and deployed state, the skin 15 on the rear pontoon assembly is at a certain angle to the L-shaped support plate 16 under the expansion of the first rear pontoon assembly airbag 12, the second rear pontoon assembly airbag 13, and the third rear pontoon assembly airbag 14, which can avoid squeezing the first rear pontoon assembly airbag 12, the second rear pontoon assembly airbag 13, and the third rear pontoon assembly airbag 14.

[0023] like Figure 7 As shown, the first rear pontoon assembly airbag 12, the second rear pontoon assembly airbag 13, and the third rear pontoon assembly airbag 14 are bonded together by annular adhesive tape 20. Two air inlets are arranged between the first rear pontoon assembly airbag 12 and the second rear pontoon assembly airbag 13, and between the second rear pontoon assembly airbag 13 and the third rear pontoon assembly airbag 14. The edges of adjacent air inlets are bonded together by annular adhesive pieces 21. The second rear pontoon assembly airbag 13 is connected to the rear pontoon assembly U-shaped connecting frame 17 by adhesive.

[0024] like Figure 8 As shown, the annular adhesive piece 21 includes two circular ring pieces 22 and an annular seam 23. The small hole in the center of the two circular ring pieces 22 is bonded to the annular seam 23 with adhesive. Taking the first rear float assembly airbag 12 and the second rear float assembly airbag 13 as an example, the adjacent air inlets of the first rear float assembly airbag 12 and the second rear float assembly airbag 13 are connected to the circular ring pieces 22 by adhesive to ensure the sealing of the air inlets.

[0025] like Figure 15 As shown, the aft pontoon assembly 3 is divided into a first compartment 59 and a second compartment 60, each with independent airtightness, by internal bulkheads. Even if any single compartment is damaged, the aft pontoon assembly 3 can still provide sufficient buoyancy. Figure 9 As shown, the U-shaped connecting frame 17 of the rear float assembly is connected to the tail beam of the fuselage by two bolts 10.

[0026] like Figure 10 As shown, the bottle valve assembly 4 includes a pull lock 24, a release valve 25, a three-way drum connector 26, and a bottle body 27, for storing and releasing high-pressure gas.

[0027] like Figure 11 As shown, the release valve includes a secondary screw plug 28, a striker spring 29, a striker 30, a striker housing 31, a sealing block 32, a diaphragm 33, a release valve housing 34, a main screw plug 35, a valve core spring 36, a safety valve 37, a gas cylinder filling / releasing valve 38, a valve core 39, a pressure gauge 40, a water-sensitive element 41, an ejector column 42, a water-sensitive housing 43, a pull lock seat 44, a tightening column 45, and a steel ball 46.

[0028] like Figure 11As shown, the firing pin 30 is a hollow needle tube structure made of stainless steel. The large-diameter section at the upper end of the firing pin 30 is used to constrain the firing pin spring 29. The water-sensitive element 41 is a cylinder with a groove in the center. The water-sensitive element 41 is solid in its non-tooling state and melts within 3 seconds upon contact with water. The water-sensitive housing 43 is a box structure with a square outer shape and a round inner shape. A round hole is provided on the right side. In the assembled state, the round hole allows water to come into contact with the water-sensitive element 41. The right side of the firing pin housing 31 is provided with a tapered hole. The inner wall of the firing pin housing 31 is the small diameter of the tapered hole. The small diameter of the tapered hole is slightly smaller than the diameter of the steel ball 46, and the large diameter of the tapered hole is slightly larger than the diameter of the steel ball 46. In the assembled state, the steel ball 46 is pressed against the tapered hole of the firing pin housing 31 and protrudes from the inner wall of the firing pin housing 31 under the combined action of the clamping column 45, the pull lock 24, the pull lock seat 44, the ejector column 42, the water sensitive element 41, and the water sensitive housing 43. The firing pin 30 is located above the steel ball 46 and is constrained in the firing pin housing 31 under the action of the auxiliary screw plug 28 and the firing pin spring 29. The auxiliary screw plug 28 is provided with several through holes that communicate with the atmosphere.

[0029] The valve core 39 has a three-section variable diameter structure. The small diameter section on the left is used to constrain the valve core spring 36. The large diameter section in the middle bears the thrust of the valve core spring 36 and can fit with the release valve housing 34. The large diameter section is provided with a large diameter sealing ring 49 to achieve sealing with the release valve housing 34. The small diameter section on the right is provided with a through hole leading to the secondary chamber 47. On the right side of the through hole, there is a first small diameter sealing ring 50 and two second small diameter sealing rings 51.

[0030] When the cylinder 27 is filled with high-pressure gas, the large-diameter stepped surface of the valve core 39 fits against the release valve housing 34 under the thrust of the valve core spring 36. The gas in the cylinder 27, the main chamber 48 and the auxiliary chamber 47 are connected through the through hole of the valve core 39 and maintain pressure balance. The main screw plug 35, diaphragm 33, safety valve 37, gas cylinder filling and releasing valve 38, pressure gauge 40, valve core 39 and second small-diameter sealing ring 51 work together to seal the main chamber 48 and the auxiliary chamber 47. The cylinder valve assembly 4 realizes the functions of high-pressure gas storage, overpressure protection and pressure detection.

[0031] like Figure 12 As shown, when the pull lock 24 is pulled in manual operation mode, the ball at the end of the pull lock disengages from the pull lock seat 44. The steel ball 46 and the clamping column 45 move to the right under the squeezing action of the firing pin spring 29 and the firing pin 30. The firing pin spring 29 pushes the firing pin 30 to pierce the diaphragm 33. The gas in the secondary chamber 47 flows out quickly through the through hole on the secondary screw plug 28. Because the valve core 39 has a large cross-sectional area, under the push of the high-pressure gas, the valve core 39 moves quickly to the left until the first small diameter sealing ring 50 seals with the release valve housing 34. The high-pressure gas is then quickly released through the three-way drum joint 52.

[0032] like Figure 13As shown, in the automatic water-sensitive working mode, the water-sensitive element 41 melts upon contact with water. The steel ball 46 and the clamping column 45 move to the right under the squeezing action of the impact spring 29 and the impact needle 30. The impact spring 29 pushes the impact needle 30 to pierce the diaphragm 33. The gas in the secondary chamber 47 flows out quickly through the through hole on the secondary screw plug 28. Due to the large cross-sectional area of ​​the valve core 39, under the push of the high-pressure gas, the valve core 39 moves quickly to the left until the first small diameter sealing ring 50 seals with the release valve housing 34. The high-pressure gas is then quickly released through the three-way drum joint 26.

[0033] Specifically, such as Figure 14 As shown, the three-way drum-shaped connector 26 has three M12 threaded interfaces that are 120° apart, with a circular through hole in the center for installation with the release valve housing 34. The inner diameter of the rear float vent 52 is 5.2 mm, the inner diameter of the left front float vent 53 is 4 mm, and the inner diameter of the right front float vent 54 is 3.8 mm, thereby ensuring that the gas flow through the pipeline assembly 5 to the right front float assembly 1, the left front float assembly 2, and the rear float assembly 3 is the same.

[0034] Specifically, such as Figure 15 As shown in the figure, only one pipeline is shown due to the similarity of the structure. The pipeline assembly 5 includes 3 one-way drum joints 55, 3 air intake valves 56, 3 two-way drum joints 57, and 3 flow-limiting air intake valves 58. The joints are connected by hoses of different lengths.

[0035] Specifically, the one-way drum connector 55 has an M12 threaded interface and a circular through hole in the center, which is used to mate with the intake valve 56 for installation.

[0036] Specifically, the upper section of the intake valve 56 is a cylinder with an end-face seal, and the cylinder has four air inlet holes on its side wall. The middle section is a hexagonal structure for easy installation, and the lower section is an externally threaded structure for installation with the right front float assembly 1, the left front float assembly 2, and the rear float assembly 3. The intake valve 56 has a spring-loaded plug inside, which can achieve one-way sealing of the gas.

[0037] Specifically, the bidirectional drum-shaped connector 57 has two M12 threaded interfaces at 180° angles, with a circular through hole in the center for installation with the flow-limiting intake valve 58.

[0038] Specifically, the four air inlets on the cylindrical sidewall of the flow-limiting intake valve 58 are smaller than those of the intake valve 56, while the remaining dimensions and structure are the same. For example... Figure 15 As shown, when gas flows in from the right side of the bidirectional drum connector 57, it flows into the second compartment 60 through the flow-limiting inlet valve 58, and then flows into the first compartment 59 through the one-way drum connector 55 and the inlet valve 56. The flow rate of the first compartment 59 and the second compartment 60 is the same by controlling the size of the inlet hole.

[0039] In summary, this invention provides an emergency flotation device for rotorcraft, which uses a single bottle valve assembly to simultaneously inflate and form three floats and six compartments. The bottle valve assembly integrates mechanical manual start and automatic start upon water contact, improving the safety of the emergency flotation device. It features lightweight, high righting torque, and good floating stability.

[0040] Example 2 like Figure 9 As shown, this application provides an emergency flotation method for a rotorcraft, implemented using the emergency flotation device for rotorcraft provided in the above embodiments. The method includes: Step 1: In an emergency, if a water landing is required, pull the cable 24 on the cylinder valve assembly 4 before landing on the water. The cylinder valve assembly 4 will release high-pressure gas. If the pilot is unable to manually start the valve assembly, the cylinder valve assembly 4 can automatically release gas by melting the internal water-sensitive element 41 after entering the water.

[0041] Specifically, step 1 includes two working modes: manual start and automatic start when water is applied.

[0042] Step 11: As Figure 12 As shown, when the pull lock 24 is pulled in manual operation mode, the ball at the end of the pull lock disengages from the pull lock seat 44. The steel ball 46 and the clamping pin 45 move to the right under the squeezing action of the firing pin spring 29 and the firing pin 30. The firing pin spring 29 pushes the firing pin 30 to pierce the diaphragm 33. The gas in the secondary chamber 47 flows out quickly through the through hole on the secondary screw plug 28. Due to the large cross-sectional area of ​​the valve core 39, under the push of the high-pressure gas, the valve core 39 moves quickly to the left until the first small diameter sealing ring 50 seals with the release valve housing 34. The high-pressure gas is then quickly released through the three-way drum joint 52. Step 12: As Figure 13 As shown, in the automatic start-up mode when wet, the water-sensitive element 41 melts upon contact with water. The steel ball 46 and the clamping column 45 move to the right under the squeezing action of the striker spring 29 and the striker 30. The striker spring 29 pushes the striker 30 to pierce the diaphragm 33. The gas in the secondary chamber 47 flows out quickly through the through hole on the secondary screw plug 28. Because the valve core 39 has a large cross-sectional area, under the push of the high-pressure gas, the valve core 39 moves quickly to the left until the first small-diameter sealing ring 50 seals with the release valve housing 34. The high-pressure gas is then quickly released through the three-way drum joint 26.

[0043] Step 2: High-pressure gas passes through pipeline assembly 5, and after throttling and diversion, is supplied to the right front float assembly 1, left front float assembly 2, and rear float assembly 3; Specifically, step 2 includes: Step 21: High-pressure gas flows out through the rear float vent 52, left front float vent 53, and right front float vent 54 on the three-way drum joint 26, flows into the second compartment 60 through the hose, two-way drum joint 57, and flow-limiting inlet valve 58, and then flows into the first compartment 59 through the hose, one-way drum joint 55, and inlet valve 56, thereby ensuring uniform flow in the six independent airtight compartments of the right front float assembly 1, left front float assembly 2, and rear float assembly 3.

[0044] Step 3: During the inflation of the right front float assembly 1, left front float assembly 2, and rear float assembly 3, the sealing constraints are released simultaneously. After the final inflation and formation, they provide buoyancy and stable floating attitude for the rotorcraft that has been forced to land on the water, facilitating the timely and safe evacuation of the crew.

[0045] Specifically, step 3 includes: Step 31: The right front pontoon assembly 1 and the left front pontoon assembly 2 are inflated to release the constraint of the flexible skin 6 of the front pontoon assembly. They are inflated into a capsule shape within 3 seconds, which helps to reduce the water load during the forced landing process.

[0046] Step 32: The rear float assembly 3 is inflated to release the constraints of the upper skin 15 and the lower skin 18 of the rear float assembly. Within 3 seconds, it is inflated into a three-float configuration that is connected side by side, which helps to reduce the floats from overturning during the forced landing process.

[0047] In summary, this invention proposes an emergency flotation device for a rotorcraft, mainly composed of float assemblies and an inflation assembly. The float assemblies provide buoyancy for a rotorcraft that has made an emergency landing on the water surface. Each float assembly has two independent airtight compartments, and can still provide sufficient buoyancy even if any single compartment is damaged. The inflation assembly mainly consists of a cylinder valve assembly and a pipeline assembly. The cylinder valve assembly is used to store / release high-pressure gas and has manual start / automatic start upon water landing functions. The pipeline assembly has diversion and throttling functions, and the gas is used to synchronously and evenly inflate and deploy the six compartments of the three float assemblies through the pipeline assembly.

Claims

1. An emergency flotation device for a rotorcraft, characterized in that... This includes float assemblies and inflatable assemblies, wherein: The float assembly includes a right front float assembly (1), a left front float assembly (2) and a rear float assembly (3), which are used to provide buoyancy and floating stability for the rotorcraft; the inflation assembly includes a bottle valve assembly (4) and a pipeline assembly (5), which are used to inflate the float assembly and have manual / automatic start-up functions upon water contact. The right front float assembly (1) and the left front float assembly (2) are symmetrically arranged on the left and right sides of the front fuselage, and their encapsulation shape is cylindrical. The right front float assembly (1) and the left front float assembly (2) are capsule-shaped when inflated and deployed. The rear float assembly (3) is a flat box structure with a good aerodynamic shape when encapsulated. The rear float assembly (3) is a three-float structure connected side by side when inflated and deployed.

2. The rotorcraft emergency flotation device according to claim 1, characterized in that... Both the right front float assembly (1) and the left front float assembly (2) include a front float assembly flexible skin (6), a front float assembly U-shaped connecting frame (7), and a front float assembly airbag (8). The front float assembly airbag (8) is connected to the front float assembly U-shaped connecting frame (7) by adhesive. Two inflation / deflation valves (9) are arranged on the outer surface of the front float assembly airbag (8) for inflation / deflation of the float and constant pressure detection. The front float assembly flexible skin (6) is connected to the front float assembly U-shaped connecting frame (7) by several screws. At the same time, nylon fasteners are arranged on the edge for folding and sealing the front float assembly airbag (8) after vacuuming.

3. The rotorcraft emergency flotation device according to claim 2, characterized in that... The front float assembly airbag (8) is divided into a first compartment (59) and a second compartment (60) with independent airtightness by a bulkhead. When any single compartment is damaged, the front float assembly airbag (8) can still provide sufficient buoyancy. The front float assembly U-shaped connecting frame (7) is connected to the fuselage beam by an adapter (11) and bolts (10).

4. The rotorcraft emergency flotation device according to claim 1, characterized in that... The bottle valve assembly (4) includes a pull lock (24), a release valve (25), a three-way drum connector (26), and a bottle body (27) for storing and releasing high-pressure gas.

5. The rotorcraft emergency flotation device according to claim 1, characterized in that... The piping assembly (5) includes three one-way drum joints (55), three air inlet valves (56), three two-way drum joints (57), and three flow-limiting air inlet valves (58), with each joint connected by a hose.

6. An emergency flotation method for a rotorcraft, characterized in that... The method is applied to the rotorcraft emergency flotation device according to any one of claims 1 to 5, and the method includes: Step 1: In an emergency, when making a forced descent on water, pull the cable (24) on the cylinder valve assembly (4) before landing on the water. The cylinder valve assembly (4) will release high-pressure gas. If the pilot is unable to manually start the valve assembly, the cylinder valve assembly (4) can automatically release gas after entering the water by melting the internal water-sensitive element (41). Step 2: High-pressure gas passes through the pipeline assembly (5), and after throttling and diversion, is supplied to the right front float assembly (1), the left front float assembly (2), and the rear float assembly (3); Step 3: During the inflation process of the right front float assembly (1), left front float assembly (2), and rear float assembly (3), the sealing constraints are released simultaneously. After the final inflation and formation, it provides buoyancy and stable floating attitude for the rotorcraft that is forced to land on the water, so as to facilitate the timely and safe evacuation of the crew.

7. The emergency flotation method for a rotorcraft according to claim 6, characterized in that... Specifically, step 1 includes two operating modes: manual start and automatic start upon water immersion. When the zipper (24) is pulled in manual mode, the ball at the end of the zipper comes off the zipper seat (44), and the steel ball (46) and the clamping column (45) move to the right under the squeezing action of the striker spring (29) and the striker (30). The striker spring (29) pushes the striker (30) to puncture the diaphragm (33), and the gas in the secondary chamber (47) flows out quickly through the through hole on the secondary screw plug (28). The valve core (39) moves to the left until the first small diameter sealing ring (50) seals with the release valve housing (34), and the high pressure gas is quickly released through the three-way drum joint (52). In the automatic start mode when wet, the water-sensitive element (41) melts when it comes into contact with water. The steel ball (46) and the clamping column (45) move to the right under the squeezing action of the striker spring (29) and the striker (30). The striker spring (29) pushes the striker (30) to puncture the diaphragm (33). The gas in the secondary chamber (47) flows out quickly through the through hole on the secondary screw plug (28). Because the valve core (39) has a large cross-sectional area, under the push of the high-pressure gas, the valve core (39) moves quickly to the left until the first small diameter sealing ring (50) seals with the release valve housing (34). The high-pressure gas is released quickly through the three-way drum joint (26).

8. The emergency flotation method for a rotorcraft according to claim 6, characterized in that... Step 2 includes: High-pressure gas flows out through the rear float vent (52), left front float vent (53), and right front float vent (54) on the three-way drum joint (26), flows into the second compartment (60) through the hose, two-way drum joint (57), and flow-limiting air inlet valve (58), and flows into the first compartment (59) through the hose, one-way drum joint (55), and air inlet valve (56), thereby ensuring uniform flow in the six independent airtight compartments of the right front float assembly (1), left front float assembly (2), and rear float assembly (3).

9. The emergency flotation method for a rotorcraft according to claim 6, characterized in that... Step 3 includes: Step 31: The right front float assembly (1) and the left front float assembly (2) are inflated to release the constraint of the flexible skin (6) of the front float assembly and inflate into a capsule shape, which helps to reduce the water load during the forced landing process. Step 32: The rear float assembly (3) is inflated to release the constraints of the upper skin (15) and lower skin (18) of the rear float assembly, and inflates to form a three-float configuration that is connected side by side, which helps to reduce the float overturning during the forced landing process.

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