Anti-crash buffer device for helicopter

Abstract

The invention relates to the technical field of aviation, in particular to a helicopter anti-crash buffer device which comprises a helicopter body. The mounting platform is fixed on the belly or the side surface of the helicopter body; one end of the supporting leg main rod is hinged to the mounting platform, and the other end of the supporting leg main rod is hinged to the inner end of an energy absorption module; one end of the auxiliary supporting leg is hinged to the mounting platform, and the other end of the auxiliary supporting leg is hinged to the supporting leg main rod; the outer end of the energy absorption module is connected with the inner end of the foot pad through a spherical hinge; one end of the pyrotechnic actuating cylinder is connected with the helicopter body through a spherical hinge, and the other end of the pyrotechnic actuating cylinder is connected with the outer end of the energy absorption module through a spherical hinge. When the helicopter works normally, the device is in a folded and compressed state and is arranged in the shell. When the helicopter crashes accidentally, the device shell falls off and is thrown away, impact energy is absorbed through the air bag after the helicopter touches the ground, safe landing of the helicopter is achieved, and life safety of flight crew is guaranteed.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and in particular to a helicopter crash protection device. Background Technology

[0002] Helicopters, with their vertical takeoff and landing, low-altitude hovering, and low site requirements, are widely used in both military and civilian fields. However, helicopters have complex structures, numerous moving parts, and mostly fly at low altitudes, making them highly susceptible to environmental influences and prone to crashes. Due to the influence of the helicopter rotor, pilots cannot eject in the event of a crash like fixed-wing aircraft pilots. Furthermore, helicopter crashes often occur at low altitudes, resulting in short reaction times and complex airflow, making it difficult for passengers to escape by parachute. All of these factors necessitate special consideration of crashworthiness in helicopter design. Current helicopter crashworthiness solutions mainly include landing gear with cushioning, energy-absorbing fuselages, and crash-safe seats. In addition, some helicopter models are equipped with ejection escape systems, but these are not widespread across all models, and the ejection process is complex and requires stringent conditions.

[0003] In the event of a crash, helicopter crash cushioning is a staged energy absorption process, typically consisting of three stages. The first stage is the landing gear, the second is the fuselage energy-absorbing floor, and the third is the crash seat. This three-stage system ensures that the impact energy transmitted to the occupants is within a safe range, protecting their lives. However, helicopter crashes involve large amounts of energy, and the three-stage system, due to its relatively short cushioning distance, absorbs only a small amount and cannot completely guarantee occupant safety. Current research focuses on optimizing these three stages, rather than developing new helicopter crash cushioning systems.

[0004] To address the aforementioned problems, this invention proposes a helicopter crash protection buffer device that significantly extends the buffer stroke and improves energy absorption. Summary of the Invention

[0005] The purpose of this invention is to overcome the shortcomings of existing technologies and provide a helicopter crash protection device. During normal helicopter operation, the device is in a retracted and compressed state, housed within a casing and fixed to the inside of a skid-type landing gear or the outside of a wheeled landing gear to meet the requirements of helicopter flight and landing. In the event of an accidental helicopter crash, the casing detaches and is jettisoned, the outriggers deploy to their working position and lock, and upon impact, the airbags within the outriggers absorb the impact energy, ensuring a safe landing and protecting the lives of the crew.

[0006] To achieve the objectives of this invention, the technical solution adopted is as follows: This invention discloses a helicopter crash protection buffer device, comprising a helicopter fuselage; a mounting platform fixed to the belly or side of the helicopter fuselage; a main outrigger rod, one end of which is hinged to the mounting platform and the other end of which is hinged to the inner end of an energy-absorbing module; an auxiliary outrigger, one end of which is hinged to the mounting platform and the other end of which is hinged to the main outrigger rod; an energy-absorbing module, the outer end of which is connected to the inner end of a foot pad via a ball joint; and a pyrotechnic actuator, one end of which is connected to the helicopter fuselage via a ball joint and the other end of which is connected to the outer end of the energy-absorbing module via a ball joint, for driving the energy-absorbing module to move and deploy; the main outrigger rod, auxiliary outrigger, energy-absorbing module, and foot pad together constitute a buffer outrigger, and the buffer device includes four outriggers.

[0007] The energy-absorbing module is composed of multiple energy-absorbing units, each including an upper plate, a lower plate, branches, an airbag, an airbag protective layer, and an inflation module. The bottom corner of the upper plate and the top corner of the lower plate are connected by several branches. The airbag is fixed in the middle of the lower plate, and the bottom of the airbag has an air hole. The inflation module is located inside the lower plate and communicates with the air hole of the airbag to inflate the airbag. The lower plate is also designed with a one-way exhaust valve and an air passage to release air and buffer when the airbag is compressed. The airbag protective layer is a ring structure made of flexible material, with its top and bottom ends connected to the bottom of the upper plate and the top of the lower plate, respectively. The airbag is located inside the airbag protective layer.

[0008] At least three branches are provided between the upper plate and the lower plate. Each branch includes an upper branch and a lower branch. The top end of the upper branch and the bottom end of the lower branch are respectively hinged to the bottom corner of the upper plate and the top corner of the lower plate via a revolute joint. The upper branch and the lower branch are hinged together by an intermediate revolute joint. The axes of the revolute joints at the top and bottom ends of adjacent branches are perpendicular. The direction of movement of the intermediate revolute joint is away from the angle connecting the branch to the upper and lower plates. When folded, the upper branch and the lower branch are located between the upper plate and the lower plate. The upper branch and the lower branch have equal lengths. The upper plate and the lower plate are square structures with equal widths. The length of the upper branch is less than the width of the upper plate.

[0009] The main support leg is hinged to the energy-absorbing module via a hinge drive mechanism. This mechanism includes a yoke block, a hinge block, a base, a hinge spring, a rack, a gear, and a pin. The yoke block has a U-shaped structure, with its inner wall connected to one end of the main support leg. Pin holes for the pin to pass through are located at the center of both ends of the yoke block, and a gap for the hinge block to be inserted is provided between the two ends. A connecting hole for connection with the pin is located at the center of the side wall of the hinge block. The base has a square structure and is fixed to the outer end of one side wall of the yoke block. The base contains... There is a spring groove for placing two of the hinge springs, and a slider that can slide along the spring groove is connected between the two hinge springs. The outer wall of the base is provided with a slide groove for communicating with the spring groove. The outer end of the slider passes through the slide groove and is connected to the inner wall of the rack. The gear meshes with the rack, and the gear is circumferentially fixedly connected to the outer end of the pin. The length of the rack is greater than the length of the slide groove, and the length of the slider is less than the length of the slide groove. In the retracted state, the axial direction of the pin is perpendicular to the plane formed by the center line of the energy absorption module in the retracted and unfolded states.

[0010] A hinge deployment locking mechanism is provided between the yoke block and the hinge block. The hinge deployment locking mechanism includes a locking spring, a locking pin, and a limiting block. A locking pin groove is provided on the outer side of the connecting hole of the hinge block, which is arranged horizontally. The cross-sectional shape of the locking pin groove matches the cross-sectional shape of the locking pin. The locking spring is connected between the inner wall of the locking pin groove and the inner wall of the locking pin. The depth of the locking pin groove is greater than the length of the locking pin. A locking pin hole for the insertion of the locking pin is provided on one side of the pin hole of the yoke block. The angle between the locking pin hole and the horizontal direction is determined by the extended state of the support leg. A limiting block is provided on the top of the yoke block. The outer end of the limiting block forms a limiting inclined surface. When the support leg is extended to the position, the top of the hinge block contacts the limiting inclined surface, at which time the locking pin can be inserted into the locking pin hole.

[0011] The installation platform includes platform branches, a platform ignition cylinder, a branch locking mechanism, a platform main board, support rods, and a platform top plate. The platform top plate is connected to the belly of the helicopter fuselage. The four bottom corners of the platform top plate are fixedly connected to the top of the support rods. The bottom end of the support rod is hinged to the top of the platform branches. The bottom end of the platform branches is hinged to the four top corners of the platform main board. The platform ignition cylinder is connected between the middle of the upper surface of the platform main board and the middle of the lower surface of the platform top plate. The platform branches include an upper platform branch rod, a lower platform branch rod, an upper rod connecting ring, and a lower rod connecting ring. The top of the upper platform branch rod is hinged to the bottom of the support rod. The bottom of the upper platform branch rod is provided with the upper rod connecting ring. The bottom of the lower platform branch rod is hinged to the four top corners of the platform main board. The platform support chain has lower rod connecting rings on both sides of its top end. A gap exists between the two lower rod connecting rings for the insertion of the upper rod connecting ring. The upper and lower rod connecting rings are axially hinged via a connecting ring shaft. A support chain locking mechanism is provided between the upper and lower rod connecting rings. The support chain locking mechanism includes a support chain locking spring, a support chain locking pin, a support chain locking pin groove, and a support chain locking pin hole. A support chain locking pin groove with the same cross-sectional shape as the support chain locking pin is located directly above the inner front wall of the upper rod connecting ring. The inner wall of the support chain locking pin groove is connected to the inner wall of the support chain locking pin via the support chain locking spring. The depth of the support chain locking pin groove is greater than the length of the support chain locking pin. A support chain locking pin hole for the insertion of the support chain locking pin is located directly above the inner ring of the lower rod connecting ring.

[0012] The upper two sides of the front wall of the platform main board are hinged to the inner ends of the main support legs, and the outer ends of each main support leg are hinged to an energy-absorbing module. The lower two sides of the front wall of the platform main board are hinged to the inner ends of the auxiliary support legs, and the outer ends of the auxiliary support legs are hinged to the inner walls of the outer ends of the main support legs. The auxiliary support legs include a first cylinder, a first telescopic shaft, a first energy-absorbing block, and a circular cutter head platform. The closed end of the first cylinder and the outer end of the first telescopic shaft are provided with square connecting blocks. The outer ends of the square connecting blocks are provided with ear plates. The inner end of the first telescopic shaft can slide with the inner wall of the first cylinder. The inner end of the first telescopic shaft is provided with the circular cutter head platform, and the inner end of the circular cutter head platform is provided with the first energy-absorbing block. A fixing rod is connected between one side wall of the two square connecting blocks, and the fixing rod is connected to the square connecting blocks by connecting block expansion bolts.

[0013] The mounting platform, outrigger mains, auxiliary outriggers, and energy-absorbing module are housed within the outer casing. The outer casing includes a first fixed outer casing, a first movable outer casing, and a first outer casing locking mechanism. The first fixed outer casing, being square in shape, is fixed to the belly of the helicopter fuselage. The platform top plate is fixed to the upper part of the first fixed outer casing and connected to the belly of the helicopter fuselage. The first movable outer casing is a hollow square structure with an open top. A first outer casing locking mechanism is provided between the upper inner wall of the first movable outer casing and the first fixed outer casing. The first outer casing locking mechanism includes a first outer casing locking explosion bolt, a first outer casing drive spring, and a connecting... The first movable housing consists of a lower connecting block and a lower connecting block. The lower connecting block is fixed to the upper inner wall of the first movable housing. One side of the top of the lower connecting block has a threaded hole that matches the external thread of the locking explosion bolt of the first housing. The other side of the top of the lower connecting block has a housing locking spring groove for placing the driving spring of the first housing. The first fixed housing has a lower connecting block hole through which the lower connecting block passes. The upper connecting block is fixed to the top of the lower connecting block hole. The upper connecting block has a bolt hole through which the locking explosion bolt of the first housing passes. The screw of the locking explosion bolt passes through the bolt hole and is threadedly connected to the threaded hole.

[0014] The installation platform includes a U-shaped rod and a moving cylinder connecting rod. The two inner ends of the U-shaped rod and the inner end of the moving cylinder connecting rod are connected to the front and rear sides of the lower side walls of the helicopter fuselage. The upper and lower parts of the outer end of the U-shaped rod are hinged to the inner ends of the main support leg and the auxiliary support leg, respectively. The outer end of the main support leg is hinged to the inner end of the energy absorption module through the hinge drive mechanism. The hinge drive mechanism is equipped with the hinge deployment and locking mechanism. The inner end of the platform fire-working moving cylinder is connected to the outer end of the moving cylinder connecting rod through a ball joint. The outer end of the platform fire-working moving cylinder is connected to the top of the outer end of the energy absorption module through a ball joint. The outer end of the auxiliary support leg is hinged to the inner wall of the outer end of the main support leg. The outrigger includes a second cylinder, a second telescopic shaft, a second energy-absorbing block, a conical protrusion, and a helical internal thread. The closed end of the second cylinder and the outer end of the second telescopic shaft are connected to an auxiliary yoke block in the shape of a U. The inner end of the second telescopic shaft can slide with the inner wall of the second cylinder. The outer end of the inner wall of the second cylinder is provided with a helical internal thread. The inner end of the second telescopic shaft is provided with a conical protrusion that is threadedly connected to the helical internal thread. The inner end of the conical protrusion is provided with a second energy-absorbing block with the same inner diameter as the second cylinder. A second fixing rod is connected between one side wall of the two auxiliary yoke blocks. The second fixing rod is connected to the auxiliary yoke blocks by an explosion bolt.

[0015] The installation platform, main support legs, auxiliary support legs, and energy absorption module are housed within the outer casing. The outer casing includes a second fixed outer casing, a second movable outer casing, and a second outer casing locking mechanism. The second fixed outer casing and the second movable outer casing are hollow structures with equilateral right-angled triangles and inclined openings. The open ends of the second fixed outer casing and the second movable outer casing are combined to form a hollow square structure. The outer ends of the U-shaped rod and the moving cylinder connecting rod are connected to both sides of an outer wall of the second fixed outer casing. The inner ends of the main support legs and the auxiliary support legs pass through the outer wall of the second fixed outer casing and are hinged to the outer ends of the U-shaped rod. The inner end of the platform fire-working moving cylinder passes through the outer wall of the second fixed outer casing and is connected to the outer end of the moving cylinder connecting rod via a ball joint.

[0016] The second outer shell locking mechanism includes a second outer shell locking explosion bolt, a second outer shell driving spring, an outer shell locking explosion nut, and a spring sleeve. The screw of the second outer shell locking explosion bolt passes through the connection between the second fixed outer shell and the second movable outer shell and is connected to the outer shell locking explosion nut. The spring sleeve has a hollow cylindrical structure with an open outer end. Its closed end is fixed to the top front end of the inner wall of the second fixed outer shell. The front end of the spring sleeve can be in close contact with the upper part of the inner wall of the second movable outer shell. The second outer shell driving spring is fitted inside the spring sleeve.

[0017] The beneficial effects of this invention are as follows: (1) This invention can improve the crashworthiness of helicopters. Currently, most helicopters use three-stage energy absorption devices, namely landing gear, fuselage, and crash-resistant seats. This invention increases the energy absorption of helicopters to four stages through energy absorption modules, thereby enhancing the crashworthiness of helicopters. This invention uses a one-dimensional deployment mechanism to strengthen the stiffness of airbags and divides the long buffer stroke into multiple segments. The airbags in different segments are independent of each other, thereby extending the overall buffer stroke.

[0018] (2) The present invention combines the airbag and the mechanism to form an energy-absorbing unit. During the storage stage, the airbag is not inflated and occupies very little space. The buffer device is folded up and installed on the side of the helicopter fuselage or inside the landing gear, without affecting the normal operation of the helicopter and making full use of the helicopter space. When the helicopter crashes, the buffer device is deployed again, making use of the helicopter's empty space and increasing the buffer travel of the buffer device, thereby improving the helicopter's crashworthiness.

[0019] (3) This invention mainly uses a pyrotechnic cylinder as the locking and driving mechanism, which has the advantages of high locking rigidity, short unlocking time, and large thrust. The working time of the pyrotechnic cylinder is generally in the millisecond range, and the inflation time of the airbag is also in the millisecond range. Therefore, the entire buffer device can be unlocked and deployed in a very short time to perform the buffering function. Helicopter accidents often occur at low altitudes, and time is very tight. The solution adopted in this invention is very suitable for such sudden and time-sensitive situations. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the retracted state of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0021] Figure 2 This is a schematic diagram of the deployed state of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0022] Figure 3 This is a schematic diagram of the buffer state of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0023] Figure 4 This is a schematic diagram of the skid-type landing gear helicopter crash protection device after the movable outer shell has been jettisoned in Embodiment 1 of the present invention.

[0024] Figure 5 This is a schematic diagram of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention with the outer shell removed.

[0025] Figure 6 This is a schematic diagram of the retracted state of the skid-type landing gear helicopter crash protection device mounting platform in Embodiment 1 of the present invention.

[0026] Figure 7 This is a schematic diagram of the unfolded state of the skid-type landing gear helicopter crash protection device installation platform in Embodiment 1 of the present invention.

[0027] Figure 8a This is a schematic diagram of the first outer shell locking mechanism between the outer shells of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0028] Figure 8b This is a schematic diagram of the installation method of the first outer shell locking mechanism between the outer shells of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0029] Figure 8c for Figure 8b A partially enlarged cross-sectional view of the locking mechanism between the middle and outer shells.

[0030] Figure 9a This is a schematic diagram of the platform support structure of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0031] Figure 9b This is an exploded view of the skid-type landing gear helicopter crashworthiness device support chain locking mechanism and the platform support chain upper rod in Embodiment 1 of the present invention.

[0032] Figure 10 This is a schematic diagram showing the relationship between the skid-type landing gear helicopter crash protection device installation platform and the main outriggers and auxiliary outriggers in Embodiment 1 of the present invention.

[0033] Figure 11 This is a schematic diagram of the energy absorption module drive locking mechanism of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0034] Figure 12 This is a schematic diagram showing the installation position of the hinge drive mechanism of the energy absorption module of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0035] Figure 13a This is a schematic diagram of the hinge drive mechanism of the energy absorption module of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0036] Figure 13b This is a top view of the hinge drive mechanism of the energy absorption module of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0037] Figure 13c for Figure 13b A cross-sectional view along AA.

[0038] Figure 14a This is a schematic diagram of the yoke block of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0039] Figure 14b This is a schematic diagram of the hinge block of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0040] Figure 14c This is a schematic diagram of the state when the hinge deployment locking mechanism of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention is not locked.

[0041] Figure 14d This is a schematic diagram of the state when the hinge deployment and locking mechanism of the skid-type landing gear helicopter crash protection device is locked in Embodiment 1 of the present invention.

[0042] Figure 14e This is an exploded view of the hinge deployment and locking mechanism of the skid-type landing gear helicopter crashworthiness device in Embodiment 1 of the present invention.

[0043] Figure 15a This is a schematic diagram of the main strut of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention. Figure 1 .

[0044] Figure 15b This is a schematic diagram of the main strut of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention. Figure 2 .

[0045] Figure 16a This is an exploded view of the auxiliary outriggers of the skid-type landing gear helicopter crashworthiness protection device in Embodiment 1 of the present invention.

[0046] Figure 16bThis is a schematic diagram of the auxiliary support leg of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0047] Figure 16c for Figure 16b A cross-sectional view along AA.

[0048] Figure 16d for Figure 16c A magnified view of a portion of the image.

[0049] Figure 17 This is a schematic diagram of the auxiliary outrigger locking state of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0050] Figure 18 This is a schematic diagram of the locking mechanism of the energy-absorbing module of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0051] Figure 19a This is a schematic diagram of the energy-absorbing module of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention. Figure 1 .

[0052] Figure 19b This is a schematic diagram of the energy-absorbing module of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention. Figure 2 .

[0053] Figure 20 This is a schematic diagram of the energy-absorbing unit structure of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0054] Figure 21 This is a schematic diagram of the internal structure of the airbag in the energy-absorbing unit of the skid-type landing gear helicopter crash protection device in Embodiment 1 of the present invention.

[0055] Figure 22a This is a schematic diagram of the retracted state of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0056] Figure 22b This is a front view of the retracted state of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0057] Figure 23 This is a schematic diagram of the deployed state of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0058] Figure 24 This is a schematic diagram of the buffer state of the anti-crash device for a wheeled landing gear helicopter in Embodiment 2 of the present invention.

[0059] Figure 25 This is a schematic diagram of the outriggers of the wheeled landing gear helicopter crash protection device installed inside the outer shell in Embodiment 2 of the present invention.

[0060] Figure 26 This is a schematic diagram of the wheeled landing gear helicopter crash protection device after the movable outer shell has been jettisoned in Embodiment 2 of the present invention.

[0061] Figure 27a This is a schematic diagram of the outriggers of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention with the outer shell removed. Figure 1 .

[0062] Figure 27b This is a schematic diagram of the outriggers of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention with the outer shell removed. Figure 2 .

[0063] Figure 28a This is a schematic diagram of the installation of the second outer shell locking mechanism on the outer shell of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0064] Figure 28b This is a schematic diagram of the installation of the second outer shell locking explosive bolts of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0065] Figure 28c This is a schematic diagram of the installation of the second outer shell drive spring of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0066] Figure 29 This is a schematic diagram of the energy absorption module drive locking mechanism of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0067] Figure 30 This is a schematic diagram of the installation of the hinge drive mechanism and hinge deployment and locking mechanism of the energy absorption module of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0068] Figure 31 This is a schematic diagram of the main strut of the outrigger of the helicopter anti-crash device for wheeled landing gear in Embodiment 2 of the present invention.

[0069] Figure 32a This is an exploded view of the auxiliary outriggers of the helicopter anti-crash device for wheeled landing gear in Embodiment 2 of the present invention.

[0070] Figure 32b This is a schematic diagram of the auxiliary support leg structure of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0071] Figure 32c This is a schematic diagram showing the connection between the second sleeve of the auxiliary leg and the second telescopic shaft of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0072] Figure 32d This is a schematic diagram of the structure of the second sleeve and the second telescopic shaft of the auxiliary leg of the wheeled landing gear helicopter crash protection device in Embodiment 2 of the present invention.

[0073] Figure 33a This is a schematic diagram of the auxiliary outrigger locking mechanism of the wheeled landing gear helicopter crashworthiness device in Embodiment 2 of the present invention. Figure 1 .

[0074] Figure 33b This is a schematic diagram of the auxiliary outrigger locking mechanism of the wheeled landing gear helicopter crashworthiness device in Embodiment 2 of the present invention. Figure 2 .

[0075] In the picture: the fuselage of a 100-ton helicopter; 200 Installation platform, 201 Platform branch chain, 202 Platform working cylinder, 203 Branch chain locking mechanism, 204 Platform main board, 205 Support rod, 206 Platform top plate, 2011 Platform branch chain upper rod, 2012 Platform branch chain lower rod, 2013 Upper rod connecting ring, 2014 Lower rod connecting ring, 2031 Branch chain locking spring, 2032 Branch chain locking pin, 2033 Branch chain locking pin groove, 2034 Branch line locking pin hole, 207 U-shaped rod, 208 Working cylinder connecting rod; 300-leg main shaft; 400 Auxiliary outrigger, 401 First cylinder, 402 First telescopic shaft, 403 First energy-absorbing block, 404 Circular cutter head platform, 405 Square connecting block, 406 Connecting block explosion bolt, 407 Fixing rod, 408 Second cylinder, 409 Second telescopic shaft, 410 Second energy-absorbing block, 411 Conical protrusion, 412 Helical internal thread, 413 Auxiliary yoke block, 414 Second fixing rod, 415 Yoke block explosion bolt; 500 Energy Absorption Module, 501 Connecting Lower Rod, 510 Energy Absorption Unit, 511 Upper Plate, 512 Lower Plate, 513 Branch Chain, 514 Airbag, 515 Airbag Protective Layer, 516 Inflation Module, 517 Branch Chain Upper Rod, 518 Branch Chain Lower Rod, 520 Cable Tie, 530 Pyrotechnic Cutter. 600 foot pads; 700 fire-operated cylinder; 800 Rotary hinge drive mechanism, 801 yoke block, 802 rotary hinge block, 803 base, 804 rotary hinge spring, 805 rack, 806 gear, 807 pin, 8031 ​​spring groove, 8032 slider, 8033 slide groove; 900 swivel opening and locking mechanism, 901 locking spring, 902 locking pin, 903 limit block, 904 locking pin groove, 905 locking pin hole; 1000 Outer shell, 1010 First fixed outer shell, 1020 First movable outer shell, 1030 First outer shell locking mechanism, 1031 First outer shell locking explosion bolt, 1032 First outer shell drive spring, 1033 Connecting upper block, 1034 Connecting lower block, 1040 Second fixed outer shell, 1050 Second movable outer shell, 1060 Second outer shell locking mechanism, 1061 Second outer shell locking explosion bolt, 1062 Second outer shell drive spring, 1063 Outer shell locking explosion nut, 1064 Spring sleeve. Detailed Implementation

[0076] The present invention will be further described below: Please see Figures 1-3 3.

[0077] Example 1 like Figure 1 The diagram shown is a structural schematic of a skid-type landing gear helicopter crash protection device in the retracted state, including: Helicopter fuselage 100; The mounting platform 200 is fixed to the belly of the helicopter fuselage 100; The main support rod 300 has one end hinged to the mounting platform 200 and the other end hinged to the inner end of the energy absorption module 500. An auxiliary support leg 400, one end of which is hinged to the mounting platform 200 and the other end of which is hinged to the support leg main rod 300; An energy-absorbing module 500, the outer end of which is connected to the inner end of the foot pad 600 via a ball joint; The fire-operating cylinder 700 has one end connected to the helicopter fuselage 100 via a ball joint, and the other end connected to the outer end of the energy-absorbing module 500 via a ball joint, for driving the energy-absorbing module 500 to move and unfold. The mounting platform 200, the outrigger main rod 300, the auxiliary outrigger 400 and the energy-absorbing module 500 are disposed inside the outer shell 1000.

[0078] The image shows the device in its retracted state. The main outrigger 300, auxiliary outrigger 400, energy-absorbing module 500, and foot pad 600 together form a buffer outrigger. There are four buffer outriggers in total, installed on the fuselage underside, inside the landing gear. Two outer shells 1000 are mounted on the mounting platform 200, enclosing the buffer outriggers. When the helicopter is operating normally, the device is in its retracted state, occupying minimal space and not affecting helicopter operation.

[0079] like Figure 2The diagram shows the structure of the skid-mounted helicopter crash protection device in the deployed state. The energy-absorbing module 500 is deployed at a downward angle, forming a 45° angle with the vertical direction. At this time, the mounting platform 200 is fully deployed and locked, and the platform mainboard 204 is basically flush with the bottom of the landing gear, ensuring that the energy-absorbing module 500 is not interfered with by the landing gear during operation. The foot pad 600 is located at the end of the energy-absorbing module 500, ensuring sufficient ground contact area in the event of a crash. The energy-absorbing module 500 and the outrigger main rod 300 are connected by a hinge. The centerline of the energy-absorbing module 500 is defined as M1 in the retracted state and N1 when deployed and locked. The hinge axis L1 is perpendicular to the plane formed by M1 and N1. For ease of display, the outer shell 1000 is hidden.

[0080] like Figure 3 The diagram shows the buffering state of the skid-mounted landing gear helicopter crash protection device. The foot pad 600 has already touched the ground, buffering a certain distance. At this point, some of the airbags in the energy-absorbing unit 510 of the energy-absorbing module 500 have deflated and retracted, shortening the energy-absorbing module 500. Under the combined action of the outrigger main rod 300, ground friction, and the auxiliary outrigger 400, the foot pad 600 maintains its ground contact position. As the helicopter moves downwards, the auxiliary outrigger 400 extends, increasing the angle between the energy-absorbing module 500 and the helicopter. This process continues until the energy-absorbing module 500 deflates and retracts to its limit or the helicopter's descent velocity reaches zero, ending the buffering process.

[0081] like Figure 4 , 5 The diagram shows the connection of the outer shell of a skid-mounted landing gear helicopter crash protection device. The outer shell 1000 includes a first fixed outer shell 1010, a first movable outer shell 1020, and a first outer shell locking mechanism 1030. The first fixed outer shell 1010 has a square structure and is fixed to the belly of the helicopter fuselage 100. The platform top plate 206 is fixed to the upper part of the first fixed outer shell 1010 and connected to the belly of the helicopter fuselage 100. The first movable outer shell 1020 has a hollow square structure with an open top. The ejection process is as follows: Figure 4 As shown, after removing the first movable outer casing 1020, the device is as follows: Figure 5 As shown, it consists of a mounting platform 200, outrigger main rods 300, auxiliary outriggers 400, energy-absorbing modules 500, foot pads 600, various drive mechanisms, and locking mechanisms. When the helicopter is operating normally, it is in a retracted and locked state, reducing its space occupation. For clarity, Figure 5 The first fixed outer shell 1010 is hidden in the middle.

[0082] Figure 8 shows a schematic diagram of the first outer shell locking mechanism 1030 of the skid landing gear helicopter crash protection device. The first outer shell locking mechanism 1030 includes a first outer shell locking explosive bolt 1031, a first outer shell drive spring 1032, a connecting upper block 1033, and a connecting lower block 1034. The connecting lower block 1034 is fixed to the upper inner wall of the first movable outer shell 1020. One side of the top of the connecting lower block 1034 is provided with a threaded hole that matches the external thread of the first outer shell locking explosive bolt 1031, and the other side of the top of the connecting lower block 1034 is provided with a hole for placing the first outer shell drive spring 1032. The outer shell has a locking spring groove. The first fixed outer shell 1010 has a connecting lower block hole for the connecting lower block 1034 to pass through. The connecting upper block 1033 is fixed to the top of the connecting lower block hole. The connecting upper block 1033 has a bolt hole for the first outer shell locking explosion bolt 1031 to pass through. The screw of the first outer shell locking explosion bolt 1031 passes through the bolt hole and is threadedly connected to the threaded hole. During operation, the first outer shell locking explosion bolt 1031 is ignited and disconnected. The first movable outer shell 1020 is thrown away from the machine body under the action of the first outer shell drive spring 1032, providing space for the energy absorption module 500 to unfold and move. like Figure 6 , 7The diagram shows the retracted and extended states of the mounting platform 200 for the skid-mounted landing gear helicopter crash protection device. The mounting platform 200 includes a platform support chain 201, a platform fire-operated cylinder 202, a support chain locking mechanism 203, a platform main board 204, support rods 205, and a platform top plate 206. The platform top plate 206 is connected to the belly of the helicopter fuselage 100. The four bottom corners of the platform top plate 206 are fixedly connected to the top ends of the support rods 205. The bottom end of the support rods 205 is hinged to the top end of the platform support chain 201. The bottom end of the platform support chain 201 is hinged to the four top corners of the platform main board 204. The platform fire-operated cylinder 202 is connected between the middle of the upper surface of the platform main board 204 and the middle of the lower surface of the platform top plate 206. The platform support chain 201 includes an upper platform support chain rod 2011 and a lower platform support chain rod 202. The platform support chain includes a rod 2012, an upper rod connecting ring 2013, and a lower rod connecting ring 2014. The top end of the upper rod 2011 is hinged to the bottom end of the support rod 205. The bottom end of the upper rod 2011 is provided with the upper rod connecting ring 2013. The bottom end of the lower rod 2012 is hinged to the top four corners of the main platform 204. The top ends of the lower rod 2012 are provided with the lower rod connecting rings 2014 on both sides. A gap is provided between the two lower rod connecting rings 2014 for the insertion of the upper rod connecting ring 2013. The axial connection of the upper rod connecting ring 2013 and the lower rod connecting ring 2014 is hinged through a connecting ring shaft. The mounting platform 200 is connected to the helicopter belly structure and is located inside the landing gear. The platform fire working cylinder 202 has ball joints at both ends and is connected to the platform top plate 206 and the platform main platform 204 through ball joints, respectively. In storage, the installation platform 200 is retracted and locked. Upon receiving the unfolding signal, the platform fire actuator 202 operates, pushing the platform mainboard 204 downward to unfold the installation platform 200. After unfolding, the position of the bottom platform mainboard 204 of the installation platform 200 is basically flush with the bottom of the landing gear, ensuring that the energy absorption module 500 is not disturbed during buffering.

[0083] Figure 9 shows a schematic diagram of the chain locking mechanism 203 of the skid-type landing gear helicopter crash protection device. The chain locking mechanism 203 is provided between the upper rod connecting ring 2013 and the lower rod connecting ring 2014. The chain locking mechanism 203 includes a chain locking spring 2031, a chain locking pin 2032, a chain locking pin groove 2033, and a chain locking pin hole 2034. Figure 9a The diagram shows the components and the platform branch 201 in its retracted / deployed state. Figure 9bThis is a schematic diagram of the component assembly method. A branch chain locking pin groove 2033 is machined directly above the inner front wall of the upper rod connecting ring 2013. The inner wall of the branch chain locking pin groove 2033 is connected to the inner wall of the branch chain locking pin 2032 by the branch chain locking spring 2031. A branch chain locking pin hole 2034 is also machined at the corresponding position directly above the inner ring of the lower rod connecting ring 2014. When the upper rod 2011 and the lower rod 2012 of the platform branch chain move to a straight line, the branch chain locking pin groove 2033 and the branch chain locking pin hole 2034 are aligned. Under the pushing force of the branch chain locking spring 2031, the branch chain locking pin 2032 is inserted into the branch chain locking pin hole 2034, thereby locking the platform branch chain 201. Figure 9a The diagram shows the positional relationship between the chain locking groove 2033 and the chain locking hole 2034 of the platform chain 201 in both the retracted and extended states. After the platform chain 201 is locked, the upper rod 2011 and the lower rod 2012 of the platform chain are aligned in a straight line, making the mounting platform 200 a stable structure that can withstand the force during buffering.

[0084] like Figure 10 The diagram shows the connection between the skid-mounted helicopter crash protection device mounting platform 200, the main outrigger 300, and the auxiliary outrigger 400. The main outrigger 300 and the auxiliary outrigger 400 are connected to the platform main board 204 in the mounting platform 200 via hinges. The other end of the auxiliary outrigger 400 is connected to the main outrigger 300 via a hinge. The auxiliary outrigger 400 contains a sliding joint. The main outrigger 300, the auxiliary outrigger 400, and the platform main board 204 constitute a planar four-bar linkage with three revolute joints and one sliding joint, which has only one degree of freedom. When the energy-absorbing module 500 is deployed and locked in place, it is aligned with the main outrigger 300. The main outrigger 300 is connected to the energy-absorbing module 500 via a pivot hinge. The centerline of the energy-absorbing module 500 in the retracted state is M1, and in the deployed state, the centerline is N1. The pivot hinge axis L1 is perpendicular to the plane formed by M1 and N1.

[0085] like Figure 11 The diagram shows the connection between the ignition cylinder 700 and the energy-absorbing module 500 of the skid-mounted helicopter crashworthiness protection system. The ignition cylinder 700 serves as the drive and locking mechanism for the energy-absorbing module 500, with its outer end connected to the outer end. The ignition cylinder 700 has ball joints at both ends; one end is connected to the fuselage via a ball joint, and the other end is connected to the energy-absorbing module 500 via a ball joint. During storage, the ignition cylinder 700 locks the energy-absorbing module 500. During operation, the ignition cylinder 700 ignites, driving the energy-absorbing module 500 to move. The ignition cylinder 700 is detachable; when the energy-absorbing module 500 reaches the predetermined position, the cylinder body and piston shaft of the ignition cylinder 700 separate. The centerline P1 of the ignition cylinder 700 is perpendicular to L1 and parallel to the plane formed by M1 and N1.

[0086] like Figure 12 As shown in Figure 13, this is a structural schematic diagram of the hinge drive mechanism 800 of the skid-type landing gear helicopter crashworthiness protection device. The outrigger main rod 300 and the energy absorption module 500 are hinged together by the hinge drive mechanism 800. The hinge drive mechanism 800 includes a yoke block 801, a hinge block 802, a base 803, a hinge spring 804, a rack 805, a gear 806, and a pin 807. The yoke block 801 has a U-shaped structure, and the inner wall of the yoke block 801 is flush with the outrigger main rod 300. One end of the yoke block 801 is connected to the pin 807. The two ends of the yoke block 801 have pin holes for the pin 807 to pass through. A gap is provided between the two ends of the yoke block 801 for the insertion of the hinge block 802. The side wall of the hinge block 802 has a connecting hole for connection with the pin 807. The base 803, in a square structure, is fixed to the outer end of one side wall of the yoke block 801. The base 803 has a spring groove 8031 ​​inside for placing two hinge springs 804. A slider 8032, capable of sliding along the spring groove 8031, is connected between the two hinge springs 804. The outer wall of the base 803 has a groove 8033 for communicating with the spring groove 8031. The outer end of the slider 8032 passes through the groove 8033 and connects to the inner wall of the rack 805. The gear 806 meshes with the rack 805, and the gear 806 is circumferentially fixedly connected to the outer end of the pin 807. The length of the rack 805... The length of the slider 8032 is less than the length of the groove 8033, which is greater than the length of the slide 8033. In the retracted state, the axis of the pin 807 is perpendicular to the plane formed by the center lines of the energy-absorbing module 500 in both the retracted and extended states. When the energy-absorbing module 500 is extended, the hinge spring 804 pushes the rack 805 to move linearly, which in turn drives the gear 806 to rotate. The gear 806 and the pin 807 are fixedly connected, thereby realizing the rotation of the energy-absorbing module 500. When the energy-absorbing module 500 is extended, it is driven by the fire-working cylinder 700 and the hinge drive mechanism 800 together.

[0087] Figure 14 shows a schematic diagram of the hinge deployment locking mechanism 900 of the skid-type landing gear helicopter crashworthiness protection device. The hinge deployment locking mechanism 900 is located between the yoke block 801 and the hinge block 802. The hinge deployment locking mechanism 900 includes a locking spring 901, a locking pin 902, and a limiting block 903. A locking pin groove 904, arranged horizontally, is provided on the outer side of the connecting hole of the hinge block 802. The cross-sectional shape of the locking pin groove 904 matches the cross-sectional shape of the locking pin 902. The locking spring 901 connects the inner wall of the locking pin groove 904 to the inner wall of the locking pin 902. The depth of the locking pin groove 904 is greater than that of the locking pin 902. The length of 02; the pin hole side of the yoke block 801 is provided with a locking pin hole 905 for the insertion of the locking pin 902, and the angle between the locking pin hole 905 and the horizontal direction is determined by the extended state of the support leg; the top of the yoke block 801 is provided with a limiting block 903, and the outer end of the limiting block 903 forms a limiting inclined surface. When the energy absorption module 500 is extended into place, the top of the hinge block 802 contacts the limiting inclined surface, at which time the locking pin 902 can be inserted into the locking pin hole 905; when the energy absorption module 500 is extended into place, the locking pin 902 pops out under the pushing force of the locking spring 901 and inserts into the corresponding locking pin hole 905, thereby locking the energy absorption module 500. Figure 14c and d show the positional relationship between the locking pin groove 904 and the locking pin hole 905 in the hinge extension locking mechanism 900 when the energy absorption module 500 is in the retracted state and the extended state. A limiting block 903 is designed on the top of the yoke block 801. After the energy absorption module 500 rotates to the position of the limiting block 903, it is restricted by the limiting block 903. At this time, the hinge unfolding locking mechanism 900 works to lock the energy absorption module 500.

[0088] Figure 15 shows a schematic diagram of the connection relationship between the main outrigger 300, platform main board 204, auxiliary outrigger 400, and energy absorption module 500 of the skid landing gear helicopter crash protection device. The main outrigger 300 and energy absorption module 500 are connected by a hinge; when deployed, the energy absorption module 500 rotates around the hinge axis. The main outrigger 300, platform main board 204, and auxiliary outrigger 400 constitute a planar four-bar linkage with three revolute joints and one prismatic joint. The hinge axis connecting the main outrigger 300 and energy absorption module 500 is located at L1 in the retracted state, and the centerline of the energy absorption module 500 is located at M1 in the retracted state. (This is in conjunction with the previous...) Figure 2 The center line of the energy absorption module 500 is located at N1 in the unfolded state, and L1 is perpendicular to the plane formed by M1 and N1.

[0089] Figures 16 and 17 show a schematic diagram of the auxiliary outrigger 400 of the skid-type landing gear helicopter crashworthiness protection device. The auxiliary outrigger 400 includes a first cylinder 401, a first telescopic shaft 402, a first energy-absorbing block 403, and a circular cutter platform 404. The closed end of the first cylinder 401 and the outer end of the first telescopic shaft 402 are provided with square connecting blocks 405. The outer end of the square connecting blocks 405 is provided with ear plates. The inner end of the first telescopic shaft 402 can slide with the inner wall of the first cylinder 401. The inner end of the first telescopic shaft 402 is provided with the circular cutter platform 404. The inner end of the circular cutter platform 404 is provided with the first energy-absorbing block 403. The inner end of the first telescopic shaft 402 is inside the first cylinder 401. The material of the first energy-absorbing block 403 can be aluminum honeycomb or aluminum foam. The other end of the circular cutter platform 404 is a smooth cylindrical surface. When the auxiliary outrigger 400 is unlocked, during the crash cushioning process, the angle between the energy-absorbing module 500 and the vertical direction increases. At this time, the auxiliary outrigger 400 extends, and the cutter head on the circular cutter head platform 404 cuts the inside of the first cylinder 401, achieving the cushioning function. Conversely, when the ground is uneven, the angle between the energy-absorbing module 500 and the vertical direction may decrease. In this case, the auxiliary outrigger 400 retracts, and the circular cutter head platform 404 compresses the first energy-absorbing block 403, achieving the cushioning function. The cushioning function of the auxiliary outrigger 400 can counteract the sliding friction between the outrigger foot pad 600 and the ground during a crash, ensuring that the foot pad 600 does not move after landing, thus guaranteeing the cushioning function. A first fixing rod 407 is connected between one side wall of the two square connecting blocks 405. The first fixing rod 407 is connected to the square connecting blocks 405 by a connecting block explosion bolt 406. When the energy absorption module 500 is deployed and locked, the connecting block explosion bolt 406 detonates, releasing the lock and allowing the auxiliary outrigger 400 to move freely. During the crash cushioning process, the energy absorption module 500 is guaranteed to function normally.

[0090] like Figure 18 As shown in Figure 19, this is a schematic diagram of the energy-absorbing module of the skid-type landing gear helicopter crash protection device. The energy-absorbing module 500 is composed of multiple energy-absorbing units 510 stacked together. When the energy-absorbing units 510 are stacked, the overlapping plates fuse together, and the stacked energy-absorbing units 510 form a cuboid energy-absorbing module 500. To prevent the energy-absorbing units 510 from moving freely in the folded state, the energy-absorbing module 500 is locked in the folded state using cable ties 520. Two cable ties lock the energy-absorbing module 500 in the folded state. An unlocking mechanism is designed at the end of the energy-absorbing module 500. The unlocking mechanism uses a pyrotechnic cutter 530. When a deployment signal is received, the pyrotechnic cutter 530 cuts the cable ties 520, releasing the lock. The energy-absorbing module 500 has a hinge block 802 and a connecting rod 501 at both ends. The hinge block 802 is connected to the outrigger main rod 300 through a hinge, and the connecting rod 501 is connected to the foot pad 600 through a ball joint.

[0091] like Figure 20 , 21 The diagram shows the structure of the energy-absorbing unit of the skid-mounted landing gear helicopter crash protection device. The energy-absorbing unit 510 includes an upper plate 511, a lower plate 512, branches 513, an airbag 514, an airbag protective layer 515, and an inflation module 516. The bottom corners of the upper plate 511 and the top corners of the lower plate 512 are connected by several branches 513. The airbag 514 is fixed in the middle of the top of the lower plate 512. The bottom of the airbag 514 has air holes. The interior of the lower plate 512 is equipped with... The airbag 514 is equipped with an inflation module 516, which is connected to the air vent of the airbag 514 to inflate the airbag 514. The lower plate 512, which is connected to the airbag 514, is also designed with a one-way exhaust valve and an air passage to release air and buffer when the airbag 514 is compressed. The airbag protective layer 515 is a ring structure made of flexible material, and its top and bottom ends are connected to the bottom of the upper plate 511 and the top of the lower plate 512, respectively. The airbag 514 is located inside the airbag protective layer 515.

[0092] At least three branches 513 are provided between the upper plate 511 and the lower plate 512. Each branch 513 includes an upper branch 517 and a lower branch 518. The top end of the upper branch 517 and the bottom end of the lower branch 518 are respectively hinged to the bottom corner of the upper plate 511 and the top corner of the lower plate 512 via revolute joints. The upper branch 517 and the lower branch 518 are hinged together via an intermediate revolute joint. The axes of the revolute joints at the top and bottom ends of adjacent branches 513 are perpendicular. The intermediate revolute joint is a single-degree-of-freedom revolute joint, and its direction of motion is away from the branch 513. 3. The direction of the connection angle with the upper plate 511 and the lower plate 512. After folding, the upper branch 517 and the lower branch 518 are located between the upper plate 511 and the lower plate 512. The upper branch 517 and the lower branch 518 have equal lengths. The upper plate 511 and the lower plate 512 are square structures with equal widths. The length of the upper branch 517 is less than the width of the upper plate 511. The upper plate 511, the lower plate 512, and the branch 513 form a single-degree-of-freedom one-dimensional unfolding mechanism, the Sarrus mechanism. The movement of this mechanism is the relative parallel movement of the upper plate 511 and the lower plate 512. The two ends of the upper branch 517 and the lower branch 518 are parallel revolute joints. The branch 513, which is composed of connecting rods, contains three parallel revolute joints. In the embodiment, the Sarrus mechanism contains n (n≥3) branches, and at least two branches have non-parallel revolute joint axes. The figure provided in this invention shows four branches, and the revolute joints between adjacent branches are perpendicular to each other. The airbag 514 is located inside the Sarrus mechanism and is made of a flexible material with good airtightness and strength. According to design requirements, the airbag 514 is connected to the lower plate 512, with an opening at the connection point. The opening of the airbag 514 connects to an air passage on the plate, which in turn connects to the inflation module 516. The airbag protective layer 515 is made of a high-strength flexible material to protect the airbag 514 during a collision, preventing it from being damaged by flames, sharp objects, etc. The inflation module 516 is installed inside the lower plate 512 connected to the airbag 514 and contains sodium trinitride and an ignition reaction device. Upon receiving an inflation signal, the sodium trinitride reacts to generate a large amount of gas, which inflates the airbag 514 through the air passage. The lower plate 512, connected to the airbag 514, is also designed with a one-way exhaust valve and an air passage. During the buffering process of the energy absorption unit 510, the gas is discharged through the one-way exhaust valve via the air passage, providing a buffering function. Both airbag 514 and the Sarrus mechanism have deployment and retraction functions. In the storage state, both are retracted. Upon impact, airbag 514 inflates, causing the Sarrus mechanism to deploy. When the device touches ground, under the impact, the Sarrus mechanism compresses airbag 514, causing airbag 514 to deflate and contract, buffering the impact force. Simultaneously, the Sarrus mechanism retracts. The movements of the Sarrus mechanism and airbag 514 are synchronized.

[0093] Working principle and process of skid landing gear helicopter crash protection device: Figure 1This refers to the device's state during normal helicopter operation, specifically its retracted and stored state. Figure 2 This is the state of the device after it was deployed when the helicopter crashed. Figure 3 This refers to the device's state during the buffer phase after the helicopter crashes and touches down. The device's operation process is from... Figure 1 Transition to Figure 2 ,go through Figure 3 The process ultimately achieves cushioning in the event of a helicopter crash. In its stored state, the first fixed outer shell 1010 and the first movable outer shell 1020 are connected together, the mounting platform 200 is retracted, the auxiliary outriggers 400 are locked, the straps of the energy-absorbing module 500 are locked, the energy-absorbing unit 510 is retracted, and the airbag 514 is retracted. Upon receiving the deployment signal during a crash, the device operates as follows: 1. In Figure 8, the first outer shell locking explosion bolt 1031 ignites and explodes, releasing the locking state of the first fixed outer shell 1010 and the first movable outer shell 1020. The first outer shell drive spring 1032 pushes the first movable outer shell 1020 to be ejected from the fuselage. After ejection, as... Figure 4 As shown; 2. Figure 11 The intermediate-fire working cylinder 700 is ignited, releasing the lock of the energy-absorbing module 500 and pushing it to rotate and unfold. Figure 12 The hinge drive mechanism 800 of the energy-absorbing module operates, in which the hinge spring 804 pushes the rack 805 to move, the rack 805 drives the gear 806 to rotate, the gear 806 drives the pin 807 to rotate, and the pin 807 drives the energy-absorbing module 500 to rotate. This process continues until the energy-absorbing module 500 is fully deployed. Figure 12 When the hinge unfolding locking mechanism 900 of the energy absorption module 500 is triggered, the locking spring 901 pushes the locking pin 902 to extend and lock in the locking pin hole 905 of the yoke block 801, thereby locking the energy absorption module 500. 3. Figure 7 The platform ignition cylinder 202 in the installation platform 200 is ignited, pushing the installation platform 200 downwards. Figure 6 The movement of the contraction state in the middle to Figure 7 In the unfolded state, the branch locking spring 2031 in the branch locking mechanism 203 in Figure 9 pushes the branch locking pin 2032 to extend and lock in place. Figure 7 The platform 200 is locked in place by means of the support chain locking pin hole 2034 on the lower rod connecting ring 2014 of the lower rod 2012 of the platform support chain; 4. Figure 17 When the explosive bolt 406 of the connecting block of the auxiliary outrigger 400 is ignited and detonated, the first fixing rod 407 loses its fixing point and loses its locking function on the auxiliary outrigger 400. 5.Figure 18 The cable tie 520 of the energy absorption module 500 is unlocked, that is, the pyrotechnic cutter 530 is ignited, and the cutter of the pyrotechnic cutter 530 cuts the cable tie 520. 6. Figure 18 The energy-absorbing unit 510 in the device inflates and deploys. Specifically, the inflation module 516 is ignited to generate a large amount of gas, which enters the airbag 514 through the air passage. The airbag 514 inflates and expands, thereby driving the one-dimensional deployment mechanism, the Sarrus mechanism, to deploy. The device's control system sends signals to control the movement of each component, realizing each action during the device's deployment process.

[0094] After the helicopter crashes and touches down, the buffering process of the device is as follows: 1. The foot pad 600 touches down, transmitting the impact to the energy-absorbing unit 510; 2. Under the pressure of the foot pad 600 and the helicopter, the airbag 514 of the energy-absorbing unit 510 is squeezed by the upper and lower plates in the Sarrus mechanism, causing the internal pressure to rise, which in turn opens the one-way exhaust valve. The gas is discharged from the one-way exhaust valve through the air passage, and the collision kinetic energy is consumed in the compression exhaust process; 3. As the energy-absorbing unit 510 retracts and the helicopter descends, the angle between the energy-absorbing module 500 and the vertical direction increases, causing the auxiliary support leg 400 to straighten and lengthen. In Figure 16, the first telescopic shaft 402 of the auxiliary support leg 400 moves, and the cutter head of its circular cutter platform 404 cuts the inside of the first cylinder 401. The cutting force is balanced with the friction of the foot pad 600, so that the foot pad 600 remains stationary in the landing position, maintaining the stability of the anti-crash device; 4. The buffering process continues until the helicopter's crash speed decreases to 0, or the energy absorption module 500 exhaust retracts to its limit position, at which point the buffering function fails.

[0095] Example 2 The similarities between this embodiment and Embodiment 1 will not be repeated. The difference lies in the retracted state of the wheeled landing gear helicopter crash protection device, as shown in Figure 22. The energy-absorbing modules 500 are retracted within the outer casing 1000. There are four energy-absorbing modules 500, installed on the side of the fuselage, flush with the fuselage. Four outer casings 1000 are installed on the mounting platform 200, enclosing the energy-absorbing modules 500. When the helicopter is operating normally, the device is in the retracted state, occupying little space and not affecting the helicopter's operation. Figures a and b show two perspectives of the device in the retracted state.

[0096] like Figure 23The diagram shows the deployed state of the crash protection device for a wheeled landing gear helicopter. When deployed, the energy-absorbing module 500 forms a 45° angle with the vertical direction, pointing downwards, ensuring that the energy-absorbing module 500 is not interfered with by the landing gear during operation. Foot pads 600 are located at the end of the energy-absorbing module 500, ensuring sufficient ground contact area in the event of a crash. The energy-absorbing module 500 and the outrigger main rod 300 are also connected by hinges. The centerline of the energy-absorbing module 500 is defined as M2 in the retracted state and N2 after being fully deployed and locked. In the retracted state, the hinge axis L2 is perpendicular to the plane formed by M2 and N2. For ease of display, the second fixed outer shell 1040 is hidden.

[0097] like Figure 24 The diagram shows the buffering state of the crash protection device for a wheeled landing gear helicopter. The energy-absorbing module 500 has already touched down, buffering a certain distance. At this point, some of the airbags in the energy-absorbing units 510 within the energy-absorbing module 500 have deflated and retracted, causing the energy-absorbing module 500 to shorten. The foot pads 600 maintain their contact position under the combined action of the energy-absorbing module 500, ground friction, and the auxiliary outriggers 400. As the helicopter descends, the angle between the energy-absorbing module 500 and the vertical direction increases, and the auxiliary outriggers 400 straighten and lengthen. This process continues until the energy-absorbing module 500 deflates and retracts to its limit, ending the buffering process, or until the helicopter's descent speed decreases to zero.

[0098] like Figure 25 The diagram shows the energy-absorbing module of the wheeled landing gear helicopter crash protection device installed inside the housing. In the storage state, the energy-absorbing module is enclosed inside the housing 1000, as shown in this figure. For ease of display, the housing 1000 is shown in perspective in the figure.

[0099] like Figure 26 As shown in Figure 27, this is a schematic diagram of the outer shell and impact-absorbing outriggers in the crash protection device for a wheeled landing gear helicopter. The outer shell 1000 includes a second fixed outer shell 1040, a second movable outer shell 1050, and a second outer shell locking mechanism 1060. The second fixed outer shell 1040 and the second movable outer shell 1050 are hollow structures with equilateral right-angled triangles and inclined openings. The open ends of the second fixed outer shell 1040 and the second movable outer shell 1050 are combined to form a hollow square structure. The outer ends of the U-shaped rod 207 and the moving cylinder connecting rod 208 are connected to both sides of the outer wall of the second fixed outer shell 1040. The inner ends of the main outrigger rod 300 and the auxiliary outrigger 400 pass through the outer wall of the second fixed outer shell 1040 and are hinged to the outer end of the U-shaped rod 207. The inner end of the fire-working moving cylinder 700 passes through the outer wall of the second fixed outer shell 1040 and is hinged to the outer end of the moving cylinder connecting rod 208. The ejection process is as follows: Figure 26As shown in Figure 27, after removing the second movable outer shell 1050, the device consists of a mounting platform 200, outrigger main rods 300, auxiliary outriggers 400, energy-absorbing modules 500, foot pads 600, various drive mechanisms, and locking mechanisms. It is in a retracted and locked state during normal helicopter operation, reducing space occupation. Figures 27a and b show two perspectives of the buffer outriggers. The outrigger main rods 300 are connected to the energy-absorbing modules 500 via hinges. The centerline of the energy-absorbing modules 500 is M2 in the retracted state and N2 in the deployed state. In the retracted state, the hinge axis L2 is perpendicular to the plane formed by M2 and N2.

[0100] Figure 28 shows a schematic diagram of the second outer shell locking mechanism 1060 in the crash protection device for wheeled landing gear helicopters. The second outer shell locking mechanism 1060 includes a second outer shell locking explosive bolt 1061, a second outer shell driving spring 1062, an outer shell locking explosive nut 1063, and a spring sleeve 1064. The screw of the second outer shell locking explosive bolt 1061 passes through the connection between the second fixed outer shell 1040 and the second movable outer shell 1050 and is connected to the outer shell locking explosive nut 1063. The spring sleeve 1064 has a hollow cylindrical structure with an open outer end. Its closed end is fixed to the top front end of the inner wall of the second fixed outer shell 1040. The front end of the spring sleeve 1064 can make close contact with the upper part of the inner wall of the second movable outer shell 1050. The second outer shell driving spring 1062 is fitted inside the spring sleeve 1064. Figure 28a This is a schematic diagram showing the installation location of the mechanism. Figure 28b A schematic diagram illustrating the installation method of the second outer casing locking explosion bolt 1061. Figure 28c This is a schematic diagram of the installation method of the second outer shell drive spring 1062. For ease of display, the outer shells are shown in perspective in Figure 28. In the figure, the second outer shell locking explosion bolt 1061 and the second outer shell drive spring 1062 are installed separately. The second outer shell drive spring 1062 is fitted inside the spring sleeve 1064. When the second outer shell locking explosion bolt 1061, in conjunction with the outer shell locking explosion nut 1063, locks and fixes the second fixed outer shell 1040 and the second movable outer shell 1050, the inner wall of the second movable outer shell 1050 closes the open end of the spring sleeve 1064. During operation, the second outer shell locking explosion bolt 1061 is ignited and disconnected. The second movable outer shell 1050 is thrown away from the machine body under the action of the second outer shell drive spring 1062, providing space for the energy absorption module to unfold and move.

[0101] like Figure 29 , 30As shown in Figure 31, the installation platform 200 of the wheeled landing gear helicopter crash protection device is connected to the energy absorption module 500. The installation platform 200 includes a U-shaped rod 207 and a moving cylinder connecting rod 208. The two inner ends of the U-shaped rod 207 and the inner end of the moving cylinder connecting rod 208 are connected to the front and rear sides of the lower side walls of the helicopter fuselage 100. The upper and lower parts of the outer end of the U-shaped rod 207 are hinged to the inner ends of the main outrigger rod 300 and the auxiliary outrigger 400, respectively. The outer end of the main outrigger rod 300 is connected to the hinge drive mechanism 80. The inner end of the energy-absorbing module 500 is hinged to the pivot drive mechanism 800, which is equipped with the pivot unfolding and locking mechanism 900. The inner end of the fire-operating cylinder 700 is connected to the outer end of the cylinder connecting rod 208 via a ball joint, and the outer end of the fire-operating cylinder 700 is connected to the top of the outer end of the energy-absorbing module 500 via a ball joint. The driving and locking mechanism of the energy-absorbing module 500 is the fire-operating cylinder 700. The energy-absorbing module 500 is connected to the mounting platform 200 via the fire-operating cylinder 700, and the mounting platform 200 is connected to the machine body. During storage, the fire-operating cylinder 700 locks the energy-absorbing module 500. During operation, the fire-operating cylinder 700 is ignited, driving the energy-absorbing module 500 to move. The fire-operating cylinder is detachable. When the energy-absorbing module 500 reaches the predetermined position, the cylinder body of the fire-operating cylinder 700 and the piston shaft separate. The centerline P2 of the fire-operating cylinder 700 is perpendicular to L2 and parallel to the plane formed by M2 and N2.

[0102] Figures 32 and 33 show schematic diagrams of the auxiliary outrigger 400 and its locking mechanism in the crash protection device for wheeled landing gear helicopters. The auxiliary outrigger 400 includes a second cylinder 408, a second telescopic shaft 409, a second energy-absorbing block 410, a conical protrusion 411, and a helical internal tooth 412. The closed end of the second cylinder 408 and the outer end of the second telescopic shaft 409 are connected to an auxiliary yoke block 413 in the shape of a concave "U". The inner end of the second telescopic shaft 409 can slide with the inner wall of the second cylinder 408. The outer end of the inner wall of the second cylinder 408 is provided with a helical internal tooth 412. The inner end of the second telescopic shaft 409 is provided with a conical protrusion 411 that is threadedly connected to the helical internal tooth 412. The inner end of the conical protrusion 411 is provided with a second energy-absorbing block 410 with the same inner diameter as the second cylinder 408. The material of the second energy-absorbing block 410 can be aluminum honeycomb or aluminum foam. When the auxiliary outrigger 400 is unlocked, during the crash cushioning process, the angle between the energy-absorbing module 500 and the vertical direction increases. At this time, the auxiliary outrigger 400 extends, and the conical protrusion 411 disrupts the spiral internal tooth structure, achieving the cushioning function. Conversely, when the ground is uneven, the angle between the energy-absorbing module 500 and the vertical direction may decrease. In this case, the auxiliary outrigger 400 retracts, and the conical protrusion 411 compresses the second energy-absorbing block 410, achieving the cushioning function. The cushioning function of the auxiliary outrigger 400 can counteract the sliding friction between the footpad 600 and the ground during a crash, ensuring that the footpad 600 does not move after the energy-absorbing module 500 lands, thus ensuring the cushioning function of the energy-absorbing module 500. The auxiliary outrigger 400 also has a locking mechanism that locks the moving parts of the auxiliary outrigger 400. This mechanism includes a second fixing rod 414 and a yoke block explosive bolt 415. The second fixing rod 414 is connected between one side wall of the two auxiliary yoke blocks 413. The second fixing rod 414 is connected to the auxiliary yoke blocks 413 through the yoke block explosive bolt 415. When the energy-absorbing module 500 is deployed and locked in place, the yoke block explosive bolt 415 detonates, releasing the lock and allowing the auxiliary outrigger 400 to move freely. During the crash cushioning process, this ensures the normal functioning of the energy-absorbing module. In this invention, the connecting block explosive bolt 406, the yoke block explosive bolt 415, the first outer shell locking explosive bolt 1031, and the second outer shell locking explosive bolt 1061 are all existing explosive bolt technologies, and their working principles will not be described in detail. In this invention, the platform fire-operated cylinder 202 and the fire-operated cylinder 700 are both existing technologies, and their working principles will not be described in detail.

[0103] Working principle and process of wheeled landing gear helicopter crash protection device: Figure 22 shows the device in its normal helicopter operation state, i.e., the device's storage state. Figure 23 This is the state of the device after it was deployed when the helicopter crashed. Figure 24 This describes the device's state during the initial impact and buffering phase after the helicopter crashes and touches down. The device's operation involves transitioning from Figure 22 to...Figure 23 ,go through Figure 24 The process ultimately achieves cushioning in the event of a helicopter crash. In its stored state, the second fixed outer shell 1040 and the second movable outer shell 1050 are connected together, the auxiliary outriggers 400 are locked, the energy-absorbing module 500 locking drive mechanism is locked, the energy-absorbing unit 510 is retracted, and the airbag 514 is retracted. Upon receiving the deployment signal during a crash, the device operates as follows: 1. In Figure 28, the second outer shell locking explosion bolt 1061 ignites and explodes, releasing the locking state of the second fixed outer shell 1040 and the second movable outer shell 1050. The second outer shell drive spring 1062 pushes the second movable outer shell 1050 to be ejected from the fuselage. After ejection, as... Figure 26 As shown; 2. Figure 29 The intermediate-fire working cylinder 700 is ignited, releasing the lock of the energy-absorbing module 500 and pushing it to rotate and unfold. Figure 30 The hinge drive mechanism 800 of the energy-absorbing module operates, in which the hinge spring 804 pushes the rack 805 to move, the rack 805 drives the gear 806 to rotate, the gear 806 drives the pin 807 to rotate, and the pin 807 drives the energy-absorbing module 500 to rotate. This process continues until the energy-absorbing module 500 is fully deployed. Figure 30 When the deployment and locking mechanism 900 of the energy absorption module is triggered, the locking spring 901 pushes the locking pin 902 to extend and lock in the locking pin hole 905 of the yoke block 801, thereby locking the energy absorption module 500. 3. When the locking mechanism of the auxiliary outrigger 400 in Figure 33 is unlocked, that is, the yoke block explosive bolt 415 is ignited and detonated, the second fixing rod 414 loses its fixing point and loses its locking function on the auxiliary outrigger 400; 4. Figure 18 The cable tie 520 of the energy absorption module 500 is unlocked, that is, the pyrotechnic cutter 530 is ignited, and the cutter of the pyrotechnic cutter 530 cuts the cable tie 520. 5. Figure 20 The energy-absorbing unit 510 in the device inflates and deploys. Specifically, the inflation module 516 is ignited to generate a large amount of gas, which enters the airbag 514 through the air passage. The airbag 514 inflates and expands, thereby driving the one-dimensional deployment mechanism, the Sarrus mechanism, to deploy. The device's control system sends signals to control the movement of each component, realizing each action during the device's deployment process.

[0104] After the helicopter crashes and touches down, the buffering process of the device is as follows: 1. The foot pad 600 touches down, transmitting the impact to the energy-absorbing unit 510; 2. Under the pressure of the foot pad 600 and the helicopter, the airbag 514 of the energy-absorbing unit 510 is squeezed by the upper and lower plates in the Sarrus mechanism, causing the internal pressure to rise, which in turn opens the one-way exhaust valve. The gas is discharged from the one-way exhaust valve through the air passage, and the collision kinetic energy is consumed in the compression exhaust process; 3. As the energy-absorbing unit 510 retracts and the helicopter descends, the angle between the energy-absorbing module 500 and the vertical direction increases, causing the auxiliary outrigger 400 to straighten and lengthen. In Figure 32, the second telescopic shaft 409 of the auxiliary outrigger 400 moves, and its conical protrusion 411 crushes and destroys the spiral internal teeth 412 of the second cylinder 408. The resistance during the crushing process is balanced with the friction of the foot pad 600, so that the foot pad 600 remains stationary in the landing position, maintaining the stability of the anti-crash device; 4. The buffering process continues until the helicopter's crash speed decreases to 0, or the energy absorption module 500 exhaust retracts to its limit position, at which point the buffering function fails.

[0105] In summary, this invention uses airbags as the cushioning material and employs a one-dimensional deployment mechanism to enhance the rigidity of the airbags, preventing instability during cushioning and constructing high-rigidity energy-absorbing units. These units are then stacked and combined to create energy-absorbing modules with long cushioning distances, overcoming the short cushioning distance limitation of traditional airbags. Combining the energy-absorbing modules and mechanisms creates a cushioning outrigger with a large folding ratio, adaptable to the needs of helicopter crash cushioning. Depending on the helicopter configuration, the cushioning outrigger is installed at the bottom or side of the fuselage. During normal helicopter operation, the outrigger is in a retracted state; upon crash, it deploys to provide cushioning. Traditional helicopter cushioning devices include three types: cushioning landing gear, energy-absorbing fuselage, and crash-resistant seats. This invention proposes a new cushioning device, expanding the types of helicopter cushioning devices and improving the helicopter's crashworthiness. The cushioning outrigger proposed in this invention uses pyrotechnic locking during the retraction phase and pyrotechnic actuation during deployment, offering advantages such as high locking rigidity and fast deployment speed. This invention retracts when the helicopter is in normal operation, taking up little space and not affecting the normal operation of the helicopter. It unfolds in the event of a helicopter crash to provide a cushioning function, making full use of the helicopter's fuselage space and improving the helicopter's safety.

[0106] The above description is merely an embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent modifications made based on the content of the present invention specification and drawings, or direct or indirect applications in related technical fields, are similarly included within the patent protection scope of the present invention.

Claims

1. A helicopter crash cushioning device, characterized in that: include: Helicopter fuselage (100); The mounting platform (200) is fixed to the belly or side of the helicopter fuselage (100); The main support rod (300) is hinged at one end to the mounting platform (200) and at the other end to the inner end of the energy absorption module (500). An auxiliary support leg (400) is provided, one end of which is hinged to the mounting platform (200) and the other end of which is hinged to the main support leg (300). An energy-absorbing module (500) is provided, the outer end of which is connected to the inner end of a footpad (600) via a ball joint. The fire-working cylinder (700) has one end connected to the helicopter fuselage (100) via a ball joint, and the other end connected to the outer end of the energy-absorbing module (500) via a ball joint, for driving the energy-absorbing module (500) to move and unfold.

2. The helicopter crash cushioning device according to claim 1, characterized in that: The energy-absorbing module (500) is composed of multiple energy-absorbing units (510). Each energy-absorbing unit (510) includes an upper plate (511), a lower plate (512), a branch chain (513), an airbag (514), an airbag protective layer (515), and an inflation module (516). The bottom corner of the upper plate (511) and the top corner of the lower plate (512) are connected by several branches (513). The airbag (514) is fixed in the middle of the top of the lower plate (512). The bottom of the airbag (514) is provided with air holes. The interior is provided with an inflation module (516), which is connected to the air hole of the airbag (514) to inflate the airbag (514). The lower plate (512) connected to the airbag (514) is also provided with a one-way exhaust valve and an air passage to release air and buffer when the airbag (514) is compressed. The airbag protective layer (515) is a ring structure made of flexible material, and its top and bottom ends are connected to the bottom of the upper plate (511) and the top of the lower plate (512) respectively. The airbag (514) is located inside the airbag protective layer (515).

3. A helicopter crash cushioning device according to claim 2, characterized in that: At least three branches (513) are provided between the upper plate (511) and the lower plate (512). Each branch (513) includes an upper branch (517) and a lower branch (518). The top end of the upper branch (517) and the bottom end of the lower branch (518) are respectively hinged to the bottom corner of the upper plate (511) and the top corner of the lower plate (512) through a revolute joint. The upper branch (517) and the lower branch (518) are hinged together through an intermediate revolute joint. The revolute joint shafts at the top and bottom ends of adjacent branches (513) are... The line is perpendicular, and the direction of movement of the intermediate rotating joint is away from the connection angle between the branch (513) and the upper plate (511) and the lower plate (512). After the branch upper rod (517) and branch lower rod (518) are folded, they are located between the upper plate (511) and the lower plate (512). The lengths of the branch upper rod (517) and branch lower rod (518) are equal. The upper plate (511) and the lower plate (512) are positive direction structures with equal widths. The length of the branch upper rod (517) is less than the width of the upper plate (511).

4. A helicopter crash cushioning device according to claim 3, characterized in that: The main support rod (300) and the energy absorption module (500) are hinged together by a hinge drive mechanism (800). The hinge drive mechanism (800) includes a yoke block (801), a hinge block (802), a base (803), a hinge spring (804), a rack (805), a gear (806), and a pin (807). The yoke block (801) has a U-shaped structure, and its inner wall is connected to the main support rod (300). One end of the yoke block (801) is connected to the pin shaft (807). The two ends of the yoke block (801) have pin holes in the middle for the pin shaft (807) to pass through. A gap is provided between the two ends of the yoke block (801) for the insertion of the hinge block (802). The side wall of the hinge block (802) has a connecting hole in the middle for connection with the pin shaft (807). The base (803) is square in structure and fixed to the outer end of one side wall of the yoke block (801). The base (803) has an internal structure... There is a spring groove (8031) for placing two of the hinge springs (804), and a slider (8032) that can slide along the spring groove (8031) is connected between the two hinge springs (804). The outer wall of the base (803) is provided with a sliding groove (8033) for communicating with the spring groove (8031). The outer end of the slider (8032) passes through the sliding groove (8033) and is connected to the inner wall of the rack (805). The gear (806) meshes with the rack (805), and the gear (806) is circumferentially fixedly connected to the outer end of the pin (807); the length of the rack (805) is greater than the length of the slide groove (8033), and the length of the slider (8032) is less than the length of the slide groove (8033); in the retracted state, the axial direction of the pin (807) is perpendicular to the plane formed by the center line of the energy absorption module (500) in the retracted and unfolded states.

5. A helicopter crash cushioning device according to claim 4, characterized in that: A hinge deployment locking mechanism (900) is provided between the yoke block (801) and the hinge block (802). The hinge deployment locking mechanism (900) includes a locking spring (901), a locking pin (902), and a limiting block (903). A locking pin groove (904) is provided on the outer side of the connecting hole of the hinge block (802) along the horizontal direction. The cross-sectional shape of the locking pin groove (904) matches the cross-sectional shape of the locking pin (902). The inner wall of the locking pin groove (904) matches the inner wall of the locking pin (902). The locking spring (901) is connected between them, and the depth of the locking pin groove (904) is greater than the length of the locking pin (902). The pin hole side of the yoke block (801) is provided with a locking pin hole (905) for the insertion of the locking pin (902). The top of the yoke block (801) is provided with a limiting block (903), and the outer end of the limiting block (903) forms a limiting slope. When the top of the hinge block (802) contacts the limiting slope, the locking pin (902) can be inserted into the locking pin hole (905).

6. A helicopter crash cushioning device according to claim 5, characterized in that: The installation platform (200) includes a platform branch (201), a platform fire-operated cylinder (202), a branch locking mechanism (203), a platform main board (204), a support rod (205), and a platform top plate (206). The platform top plate (206) is connected to the belly of the helicopter fuselage (100). The four bottom corners of the platform top plate (206) are fixedly connected to the top of the support rod (205). The bottom end of the support rod (205) is hinged to the top of the platform branch (201). The bottom end of the platform branch (201) is hinged to the four top corners of the platform main board (204). The platform fire-operated cylinder (202) is connected between the middle of the upper surface of the platform main board (204) and the middle of the lower surface of the platform top plate (206). The platform branch (201) includes an upper platform branch rod (2011), a lower platform branch rod (2012), an upper rod connecting ring (2013), and a lower rod connecting ring (2014). The top end of the upper platform branch rod (2011) is hinged to the bottom end of the support rod (205). The bottom end of the upper platform branch rod (2011) is provided with the upper rod connecting ring (2013). The bottom end of the lower platform branch rod (2012) is hinged to the top four corners of the platform main board (204). The top two sides of the lower platform branch rod (2012) are provided with the lower rod connecting rings (2014). There is a gap between the two lower rod connecting rings (2014) for the insertion of the upper rod connecting ring (2013). The axial connection of the upper rod connecting ring (2013) and the lower rod connecting ring (2014) is hinged through the connecting ring shaft. The branch locking mechanism (203) is provided between the upper rod connecting ring (2013) and the lower rod connecting ring (2014). The branch locking mechanism (203) includes a branch locking spring (2031), a branch locking pin (2032), a branch locking pin groove (2033), and a branch locking pin hole (2034). The upper rod connecting ring (2013) has a branch locking spring (2031) with the same cross-sectional shape as the branch locking pin (2032) directly above the inner ring front wall. A branch locking pin groove (2033) is provided, and the inner wall of the branch locking pin groove (2033) is connected to the inner wall of the branch locking pin (2032) by the branch locking spring (2031). The depth of the branch locking pin groove (2033) is greater than the length of the branch locking pin (2032). The inner ring of the lower rod connecting ring (2014) is provided with a branch locking pin hole (2034) for the insertion of the branch locking pin (2032).

7. A helicopter crash cushioning device according to claim 6, characterized in that: The upper sides of the front wall of the platform main board (204) are respectively hinged to the inner ends of a support leg main rod (300), and the outer ends of each support leg main rod (300) are hinged to an energy absorption module (500); the lower sides of the front wall of the platform main board (204) are respectively hinged to the inner ends of an auxiliary support leg (400), and the outer ends of the auxiliary support leg (400) are hinged to the inner walls of the outer ends of the support leg main rod (300). The auxiliary support leg (400) includes a first cylinder (401), a first telescopic shaft (402), a first energy absorption block (403), and a circular cutter head platform (404). The closed end of the first cylinder (401) and the first The outer end of the telescopic shaft (402) is provided with a square connecting block (405), and the outer end of the square connecting block (405) is provided with an ear plate. The inner end of the first telescopic shaft (402) can slide in cooperation with the inner wall of the first cylinder (401). The inner end of the first telescopic shaft (402) is provided with the circular cutter head platform (404), and the inner end of the circular cutter head platform (404) is provided with the first energy-absorbing block (403). A fixing rod (407) is connected between one side wall of the two square connecting blocks (405), and the fixing rod (407) is connected to the square connecting block (405) by a connecting block explosion bolt (406).

8. A helicopter crash cushioning device according to claim 7, characterized in that: The mounting platform (200), outrigger main rod (300), auxiliary outrigger (400), and energy absorption module (500) are disposed within the outer shell (1000). The outer shell (1000) includes a first fixed outer shell (1010), a first movable outer shell (1020), and a first outer shell locking mechanism (1030). The first fixed outer shell (1010) is square in shape and fixed to the belly of the helicopter fuselage (100). The platform top plate (206) is fixed to the upper part of the first fixed outer shell (1010), and the top of the platform top plate (206) is connected to the belly of the helicopter fuselage (100). The first movable outer shell (1020) is a hollow square structure with an open top. The first outer shell locking mechanism (1030) is provided between the upper inner wall of the first movable outer shell (1020) and the first fixed outer shell (1010). The first outer shell locking mechanism (1030) includes a first outer shell locking explosion bolt. 1031), a first housing drive spring (1032), an upper connecting block (1033), and a lower connecting block (1034). The lower connecting block (1034) is fixed above the inner wall of the first movable housing (1020). The top side of the lower connecting block (1034) is provided with a threaded hole that matches the external thread of the first housing locking explosion bolt (1031). The other side of the top of the lower connecting block (1034) is provided with a housing locking spring groove for placing the first housing drive spring (1032). The first fixed housing (1010) is provided with a lower connecting block hole through which the lower connecting block (1034) passes. The upper connecting block (1033) is fixed to the top of the lower connecting block hole. The upper connecting block (1033) is provided with a bolt hole through which the first housing locking explosion bolt (1031) passes. The screw of the first housing locking explosion bolt (1031) passes through the bolt hole and is threadedly connected to the threaded hole.

9. A helicopter crash cushioning device according to claim 5, characterized in that: The installation platform (200) includes a U-shaped rod (207) and a moving cylinder connecting rod (208). The two inner ends of the U-shaped rod (207) and the inner end of the moving cylinder connecting rod (208) are connected to the front and rear sides of the lower side walls of the helicopter fuselage (100). The upper and lower ends of the outer ends of the U-shaped rod (207) are respectively hinged to the inner ends of the main outrigger rod (300) and the auxiliary outrigger (400). The outer end of the main outrigger rod (300) is connected to the energy absorption module (5) through the hinge drive mechanism (800). The inner end of the rotating hinge drive mechanism (800) is hinged, and the rotating hinge unfolding and locking mechanism (900) is provided on the rotating hinge drive mechanism (800). The inner end of the fire working cylinder (700) is connected to the outer end of the moving cylinder connecting rod (208) by a ball joint, and the outer end of the fire working cylinder (700) is connected to the top of the outer end of the energy absorption module (500) by a ball joint. The outer end of the auxiliary leg (400) is hinged to the inner wall of the outer end of the main support rod (300). The auxiliary leg (400) includes a second The cylinder (408), the second telescopic shaft (409), the second energy-absorbing block (410), the conical protrusion (411), and the helical internal teeth (412) are connected to the closed end of the second cylinder (408) and the outer end of the second telescopic shaft (409). The auxiliary yoke block (413) in the shape of a "U" is connected to the closed end of the second cylinder (408) and the outer end of the inner wall of the second cylinder (408). The inner end of the second cylinder (408) is provided with helical internal teeth (412). The inner end of the second telescopic shaft (409) is provided with a conical protrusion (411) that is threaded to the helical internal thread (412). The inner end of the conical protrusion (411) is provided with a second energy-absorbing block (410) with the same inner diameter as the second cylinder (408). A second fixing rod (414) is connected between one side wall of the two auxiliary yoke blocks (413). The second fixing rod (414) and the auxiliary yoke blocks (413) are connected by yoke block explosion bolts (415).

10. A helicopter crash cushioning device according to claim 9, characterized in that: The installation platform (200), main support legs (300), auxiliary support legs (400), and energy absorption module (500) are housed within the outer casing (1000). The outer casing (1000) includes a second fixed outer casing (1040), a second movable outer casing (1050), and a second outer casing locking mechanism (1060). The second fixed outer casing (1040) and the second movable outer casing (1050) are hollow structures with an equilateral right-angled triangle opening on the inclined plane. The second fixed outer casing (1040) and the second movable outer casing (1050) are further... The open ends of 50) are combined to form a hollow square structure. The outer ends of the U-shaped rod (207) and the moving cylinder connecting rod (208) are connected to both sides of the outer wall of the second fixed housing (1040). The inner ends of the main support rod (300) and the auxiliary support leg (400) pass through the outer wall of the second fixed housing (1040) and are hinged to the outer end of the U-shaped rod (207). The inner end of the fire working moving cylinder (700) passes through the outer wall of the second fixed housing (1040) and is connected to the outer end of the moving cylinder connecting rod (208) by a ball joint. The second outer shell locking mechanism (1060) includes a second outer shell locking explosion bolt (1061), a second outer shell driving spring (1062), an outer shell locking explosion nut (1063), and a spring sleeve (1064). The screw of the second outer shell locking explosion bolt (1061) passes through the connection between the second fixed outer shell (1040) and the second movable outer shell (1050) and is connected to the outer shell locking explosion nut (1063). The spring sleeve (1064) has a hollow cylindrical structure with an open outer end. Its closed end is fixed to the top front end of the inner wall of the second fixed outer shell (1040). The front end of the spring sleeve (1064) can be in close contact with the upper part of the inner wall of the second movable outer shell (1050). The second outer shell driving spring (1062) is fitted inside the spring sleeve (1064).

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