Energy-absorbing folding support device for aircraft

Abstract

The present invention provides an energy-absorbing folding support device for an aircraft, which relates to the technical field of aircraft. The device comprises four load-bearing supports, which are divided into two groups, a left group and a right group, and each group comprises two front and rear load-bearing supports respectively. When the load-bearing supports are rotated to an expanded state, the four load-bearing supports are spread out in an eight-shaped shape to support the fuselage to touch the ground. The four load-bearing supports are pipes with a relatively long length. The longer length can provide a better protection effect for the parachute recovery of the aircraft compared with the traditional design. When folding and recovering, the front load-bearing support rotates backward to be folded together, and the rear load-bearing support rotates forward to be folded together. The two load-bearing supports in the same group overlap each other on the side of the fuselage, do not occupy too much space, and do not affect the normal flight state of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and further to an energy-absorbing folding support device for an aircraft. Background Art

[0002] Compared with large aircraft, small and medium-sized aircraft are generally smaller in size, and therefore have many shortcomings in speed, ceiling, range, and flight time. However, they also have advantages that are different from large aircraft, such as being able to get closer to the target, perform more detailed regional operations, and have low costs for networking multiple aircraft in the region. Therefore, combined operations of large aircraft mounting and airdropping small and medium-sized aircraft have emerged.

[0003] Currently, there are several methods for landing and recovering aircraft, including wheeled landing, parachute recovery, net recovery, and rope recovery. Each method targets different applications and has different technical advantages. Parachute recovery is the most effective way to recover aircraft, but parachuting is only one part of the recovery process. When an aircraft descends at a speed of approximately 10 m / s, it cannot guarantee a lossless landing at the moment of touchdown.

[0004] In order to achieve the protection of the aircraft body during parachute recovery, parachute recovery aircraft are usually designed with a landing support device, such as a fixed skid or landing gear, or an inflatable airbag. However, the fixed skid or landing gear has a large wind resistance area and can only be used in conjunction with ground takeoff; the inflatable airbag is generally installed in the fuselage (the wing airfoil is thin and not easy to install). All multi-mission aircraft have a lot of onboard equipment, so the gas cylinders and airbags they carry are also limited, and the airbag protection over a large area cannot be achieved, and the protection effect of the ground balance is limited.

[0005] For those skilled in the art, how to provide better protection for the parachute recovery of aircraft is a technical problem that needs to be solved at present. Summary of the Invention

[0006] The present invention provides an energy-absorbing folding support device for an aircraft, which can provide better protection for the parachute recovery of the aircraft when unfolded, and does not affect the normal flight of the aircraft when folded. The specific scheme is as follows:

[0007] An energy-absorbing folding support device for an aircraft comprises four load-bearing supports, wherein the four load-bearing supports are divided into two groups, left and right, and each group comprises two front and rear load-bearing supports;

[0008] Each of the load-bearing brackets is rotatably mounted on a support provided on the fuselage, and the load-bearing bracket rotates relative to the support to achieve folding or unfolding;

[0009] Among them, in the unfolded state, the four load-bearing supports are spread out in an eight-shape to support the fuselage to touch the ground; the front load-bearing support can be rotated backward to be folded, and the rear load-bearing support can be rotated forward to be folded, and the two load-bearing supports in the same group overlap up and down on the side of the fuselage.

[0010] Optionally, each of the left and right groups of the load-bearing supports is provided with a folding stop pin, the folding stop pin comprising a telescopic mechanism and a latch, the telescopic mechanism being capable of driving the latch to move, the latch being capable of being inserted into the ground contacting end of the load-bearing support in the subsequent folding order to keep the load-bearing support in the folded state;

[0011] A clamping ring is provided between the two load-bearing brackets in the same group, and the load-bearing bracket in the later folding order keeps the load-bearing bracket in the earlier folding order in the folded state through the clamping ring.

[0012] Optionally, an expansion torsion spring is provided between the load-bearing bracket and the support, and the expansion torsion spring applies a torque to the load-bearing bracket to rotate it toward the expanded state.

[0013] Optionally, a positioning pin and an ejection spring are provided on the support, and a limiting hole is provided on the load-bearing bracket;

[0014] When the limiting hole is rotated to a position facing the positioning pin, the ejection spring pushes the positioning pin to be inserted into the limiting hole, so as to limit the relative angle between the support and the load-bearing bracket.

[0015] Optionally, the number of the positioning pins is set to be more than two, and the limiting holes are set on circles of different radii and at unequal distances from the center of the circle; each positioning pin is correspondingly provided with one limiting hole;

[0016] Among them, at the same time, only one positioning pin is inserted into its corresponding limiting hole. When the positioning pin is broken by impact to absorb energy and buffer, the load-bearing bracket is further rotated relative to the support to allow the next positioning pin to be inserted into its corresponding limiting hole, thereby achieving step-by-step buffering.

[0017] Optionally, the radii between the positioning pins and the axis are not equal, and the central angle of two adjacent positioning pins is not equal to the central angle of two corresponding adjacent limiting holes.

[0018] Optionally, the stiffness of the last positioning pin for bearing shear force is greater than the shear force generated during impact.

[0019] Optionally, each of the load-bearing supports comprises at least two segments;

[0020] Among them, in the unfolded state, the strength of each segment gradually weakens from top to bottom, so as to achieve step-by-step self-destruction and energy absorption of each segment.

[0021] Optionally, two adjacent segments are plugged into each other and fitted together, and a shock-absorbing spring is provided between the two plugged-in segments, so that the impact energy is compressed and absorbed by the shock-absorbing spring.

[0022] Optionally, the support is mounted on the front frame beam or the rear frame beam of the fuselage, and the load-bearing bracket is located above or below the wing when folded.

[0023] The present invention provides an energy-absorbing folding support device for an aircraft, comprising four load-bearing supports, which are divided into two groups, a left group and a right group, each group comprising two front and rear load-bearing supports respectively; when the load-bearing supports are rotated to an expanded state, the four load-bearing supports are spread out in an eight-shaped shape to support the fuselage to touch the ground; the four load-bearing supports are pipes with a relatively long length, and the longer length can provide a better protection effect for the parachute recovery of the aircraft compared with the traditional design; during folding and recovery, the front load-bearing support is rotated backward to be folded together, and the rear load-bearing support is rotated forward to be folded together, and the two load-bearing supports in the same group are overlapped on the side of the fuselage up and down, do not occupy too much space, and do not affect the normal flight state of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without paying any creative work.

[0025] Figure 1 A partial schematic diagram of the aircraft energy-absorbing folding support device provided by the present invention in the state where the load-bearing bracket is deployed;

[0026] Figure 2 A partial schematic diagram of the aircraft energy-absorbing folding support device provided by the present invention in a folded state of the load-bearing bracket;

[0027] Figure 3 Schematic diagram of the coordination between the load-bearing bracket and the folding stop pin;

[0028] Figure 4 Schematic diagram of the coordination between the support and the load-bearing bracket;

[0029] Figure 5 It is a partial structural diagram of the rotating end of the load-bearing bracket;

[0030] Figure 6 is a schematic cross-sectional view of the fuselage;

[0031] Figure 7 This is the front view of the fuselage and the load-bearing bracket;

[0032] Figure 8 It is a top view of the fuselage and the load-bearing bracket;

[0033] Figure 9 Schematic diagram of the folding and unfolding states of the aircraft energy-absorbing folding support device of the present invention.

[0034] The diagram includes:

[0035] Fuselage 1, load-bearing bracket 2, unfolding torsion spring 21, limiting hole 22, shock-absorbing spring 23, snap ring 24, folding stop pin 3, telescopic mechanism 31, latch 32, wing 4, support 5, positioning pin 51, ejection spring 52. DETAILED DESCRIPTION

[0036] The core of this invention is to provide an energy-absorbing, foldable aircraft support device that provides enhanced protection during parachute recovery and does not affect the aircraft's normal flight. To help those skilled in the art better understand the technical solution of this invention, the following detailed description of this energy-absorbing, foldable aircraft support device is provided with reference to the accompanying drawings and specific embodiments.

[0037] Combine Figures 1 to 9 The present invention provides an energy-absorbing folding support device for an aircraft, comprising four load-bearing supports 2. The load-bearing supports 2 are tubular structures of a certain length, which contact the ground to provide support when unfolded and can provide cushioning when the aircraft is parachuted. The load-bearing supports 2 are rotatably mounted on the supports 5. Each load-bearing support 2 corresponds to a support 5, and the supports 5 can be fixed to the outer surface of the fuselage by screws. The four load-bearing supports 2 are divided into two groups, left and right, and each group includes two front and rear load-bearing supports 2 respectively; according to the flight direction of the aircraft, two of the load-bearing supports 2 are located on the left side of the fuselage 1, and the other two load-bearing supports 2 are located on the right side of the fuselage 1. The fuselage 1 and the wings 4 are the main structures of the aircraft.

[0038] Each load-bearing bracket 2 is rotatably installed on a support 5 provided on the fuselage 1. The load-bearing bracket 2 rotates relative to the support 5 to achieve folding or unfolding. The folded state is a non-use state, at which time the load-bearing bracket 2 is close to the fuselage 1; the unfolded state is a use state, at which time the load-bearing bracket 2 is away from the fuselage 1 and faces downward.

[0039] In the deployed state, the four load-bearing supports 2 are spread out in an "eight" shape to support the fuselage 1 touching the ground. Each load-bearing support 2 is tilted downward in the deployed state, increasing the area enclosed by the contact point between the bottom end of the load-bearing support 2 and the ground, providing more stable support. The front load-bearing support 2 can be rotated backward to be folded, and the rear load-bearing support 2 can be rotated forward to be folded. In the folded state, the two load-bearing supports 2 of the same group overlap on the side of the fuselage 1; the two groups of load-bearing supports 2 can be folded and located on the outside of the aircraft. Since the windward surface after folding is only the cross-sectional area of ​​the two groups of tubular load-bearing supports 2, the two groups of load-bearing supports 2 can be either externally mounted (simple structure, wider application range) or built into the inside of the fuselage skin. External placement of the support is more convenient for aircraft application. It can be modified on existing aircraft or applied to newly developed aircraft. It does not hinder its use in current traditional aircraft, so it has good adaptability.

[0040] Compared to the prior art, the aircraft energy-absorbing folding support device of the present invention provides ground support during parachuting through a tubular load-bearing bracket 2. The length design of the load-bearing bracket 2 is more flexible, and the longer load-bearing bracket 2 can provide better protection for the parachute recovery of the aircraft compared to the traditional design. Each of the four load-bearing brackets 2 is designed with an energy-absorbing device, which can better prevent damage to the aircraft caused by the instantaneous impact of parachute landing. The unfolded figure-eight bracket has a significant advantage in stability in supporting the landing of the aircraft compared to existing traditional structures such as fixed skids or landing gear, inflatable airbags, etc.

[0041] On the basis of the above scheme, the left and right groups of load-bearing supports 2 of the present invention are respectively provided with a folding stop pin 3, and the folding stop pin 3 includes a telescopic mechanism 31 and a latch 32. The telescopic mechanism 31 has a telescopic moving block and can be electrically driven. The telescopic mechanism 31 can drive the latch 32 to move, and the latch 32 can be inserted into the end of the load-bearing support 2 that touches the ground to limit its position, so that the load-bearing support 2 remains in a folded state.

[0042] It should be noted that, in the present invention, a group of two load-bearing supports 2 only needs to be provided with one folding stop pin 3. There is a sequence in the folding of the two load-bearing supports 2 in the same group. The load-bearing support 2 that completes folding first does not need to be provided with a folding stop pin 3. Only the load-bearing support 2 that completes folding later is provided with a folding stop pin 3. The latch 32 can be inserted into the end of the ground-touching end of the load-bearing support 2 with the later folding sequence to keep the load-bearing support 2 in a folded state; a snap ring 24 is provided between the two load-bearing supports 2 in the same group, and the snap ring 24 is provided on the load-bearing support 2 with the later folding sequence. The load-bearing support 2 with the later folding sequence keeps the load-bearing support 2 with the earlier folding sequence in a folded state through the snap ring 24. The load-bearing support 2 that folds later is limited by the folding stop pin 3, and the load-bearing support 2 that folds earlier is limited by the snap ring 24. When the lock of one folding stop pin 3 is released, the two load-bearing supports 2 in the same group are unfolded at the same time.

[0043] The folding stop pins 3 limit the ground contact end of the load-bearing bracket 2, thereby preventing the load-bearing bracket 2 from shaking during flight. In addition to the above-described form, each load-bearing bracket 2 can also be provided with a corresponding folding stop pin 3. The folding stop pins 3 can be driven electrically or pneumatically. When the lock needs to be released, the extension rods of each folding stop pin 3 retract simultaneously, thereby releasing the lock on the load-bearing bracket 2.

[0044] Combine Figure 4 An expansion torsion spring 21 is provided between the support bracket 2 and the support 5. The expansion torsion spring 21 is provided at the position of the rotating shaft connecting the support bracket 2 and the support 5. The expansion torsion spring 21 applies a torque to the support bracket 2 to rotate it toward the expanded state. When the support bracket 2 is unlocked, the support bracket 2 automatically expands under the action of the torque of the expansion torsion spring 21. A limit structure is provided between the support bracket 2 and the support 5. When the support bracket 2 is expanded to a specific angle, the position of the support bracket 2 is blocked and limited.

[0045] Based on any of the above technical solutions and their combination, Figure 4 、 Figure 5 A positioning pin 51 and an ejection spring 52 are provided on the support 5, and a limiting hole 22 is provided on the load-bearing bracket 2; wherein, when the limiting hole 22 rotates to a position facing the positioning pin 51, the ejection spring 52 pushes the positioning pin 51 to insert into the limiting hole 22, so as to limit the relative angle between the support 5 and the load-bearing bracket 2. The positioning pin 51 can be broken by impact to achieve buffering. When the load-bearing bracket 2 is unlocked, the load-bearing bracket 2 rotates relative to the support 5. When the positioning pin 51 is inserted into the limiting hole 22, the angle between the load-bearing bracket 2 and the support 5 is limited, which plays a role in limiting the angle of the load-bearing bracket 2. The positioning pin 51 bears the shear force generated by the relative rotation between the support 5 and the load-bearing bracket 2. When the shear force on the positioning pin 51 reaches the maximum, the positioning pin 51 breaks, absorbing the impact force on the load-bearing bracket 2 when the aircraft lands.

[0046] It should be noted that the limiting hole 22 is a blind hole set on the load-bearing bracket 2. In order to release the lock of the positioning pin 51, a through hole with a smaller diameter can be opened on the load-bearing bracket 2 at a position opposite the center of the limiting hole 22. The withdrawal pin can be extended from this channel to push the positioning pin 51 out of the limiting hole 22.

[0047] Combine Figure 5The number of positioning pins 51 is set to be more than two, and each positioning pin 51 corresponds to a limiting hole 22. The radius between each positioning pin 51 and the axis is not equal, and the limiting holes 22 are set on circles with different radii. The central angle of two adjacent positioning pins 51 is not equal to the central angle of two corresponding adjacent limiting holes 22; it should be noted that the multiple positioning pins 51 in the present invention do not extend into the limiting holes 22 at the same time to limit and withstand shear force. At the same time, only one positioning pin 51 is inserted into its corresponding limiting hole 22. When the positioning pin 51 is broken by impact and absorbs energy, the load-bearing bracket 2 and the support 5 can continue to rotate under the elastic force and inertia of the unfolded torsion spring 21. The load-bearing bracket 2 further rotates relative to the support 5 to allow the next positioning pin 51 to be inserted into its corresponding limiting hole 22, thereby achieving step-by-step buffering. After the first positioning pin 51 is shear-damaged, the limit between the support 5 and the load-bearing bracket 2 is released. At this time, the load-bearing bracket 2 continues to rotate relative to the support 5. After rotating to a certain angle, the other positioning pin 51 comes into play, limiting the load-bearing bracket 2 and the support 5, and the load-bearing bracket 2 cannot continue to rotate. Then, the positioning pin 51 continues to bear the shear force. When the positioning pin 51 reaches the maximum shear force, the positioning pin 51 breaks to absorb the impact and form a buffer. By providing more than two positioning pins 51, each positioning pin 51 plays a buffering role in turn, and can gradually withstand the impact to achieve a better buffering effect.

[0048] The locating pins 51 do not simultaneously bear shear forces. A single locating pin 51 ensures that when the maximum bearing capacity is exceeded, it will break, absorbing energy and buffering the force. This prevents the aircraft from rebounding when the load-bearing bracket 2 contacts the ground. The positioning of the locating pins 51 allows for adjustment of the height at which the aircraft supports the ground, as well as the degree to which the bracket supports the ground.

[0049] The stiffness of the last positioning pin 51 for bearing shear force is greater than the shear force generated during impact. When multiple positioning pins 51 are broken in sequence and the shear force is borne by the last positioning pin 51, the shear force borne by the last positioning pin 51 is less than the stiffness of the positioning pin 51. The last positioning pin 51 will not be broken and will stop at the final position after rotating to the last positioning pin 51, thereby preventing the fuselage 1 from contacting the ground.

[0050] Specifically, combined Figure 4 The locating pin 51 is installed on the support 5 through the ejection spring 52. The load-bearing bracket 2 is provided with a limiting hole 22 for inserting the locating pin 51, and each locating pin 51 corresponds to a limiting hole 22; when the locating pin 51 rotates with the load-bearing bracket 2 to a position facing the limiting hole 22, the ejection spring 52 ejects the locating pin 51 and inserts it into the limiting hole 22. At this time, the locating pin 51 plays a limiting role and withstands shear force.

[0051] Combine Figure 5The radii between two adjacent limiting holes 22 and the rotation center of the load-bearing bracket 2 are not equal and are located in different radial directions. Figure 5 The upper right limiting hole 22 first cooperates with the positioning pin 51, and the lower left limiting hole 22 cooperates with the positioning pin 51 later. Ensure that the positioning pin 51 and the limiting hole 22 are matched and work in sequence. The impact energy of the aircraft landing can be absorbed by cutting off the positioning pin 51 to form a buffer. Each time a positioning pin 51 is cut off, the aircraft body will drop a certain height. Based on the same design principle, each additional pair of positioning pins 51 and limiting holes 22 can increase the energy absorption level. Therefore, the support height of the load-bearing bracket 2 is important to allow the design of a multi-stage energy absorption device.

[0052] By designing the relative displacement distance between the positioning pin 51 and the limiting hole 22, the Figure 7 、 Figure 8 The openings W1 and W2 and height H1 of the middle load-bearing support 2 have better adaptability to different types of landing sites for the aircraft. Among them, low height H1, corresponding to large openings W1 and W2, is suitable for landing on flat terrain; large height H1, corresponding to low openings W1 and W2, is suitable for landing on terrain with obstacles such as stones on the ground.

[0053] Furthermore, the load-bearing support 2 of the present invention comprises at least two segments. When deployed, the strength of each segment gradually decreases from top to bottom, enabling each segment to self-destruct and absorb energy. The strength of each segment decreases gradually from top to bottom, and can vary depending on the material, or the thickness of the same material. The upper support rod is stronger, while the lower support rod is weaker, allowing the lower support rod to self-destruct and absorb energy during the impact of the aircraft parachute landing.

[0054] Further, combined Figure 4 Adjacent segments are interlocked and nested, and can move longitudinally. A shock-absorbing spring 23 is provided between the interlocking segments to absorb impact energy through compression. When the load-bearing bracket 2 contacts the ground during landing, the bottom end generates an impact, which is transmitted to the shock-absorbing spring 23, causing the adjacent segments to retract toward each other, thereby achieving the energy absorption effect.

[0055] The load-bearing bracket 2 is arranged on both sides of the fuselage 1, and the support 5 is installed on the front frame beam or the rear frame beam of the fuselage 1. The length of each load-bearing bracket 2 is only related to the distance between the front frame beam and the rear frame beam of the aircraft body. Therefore, the length design of the load-bearing bracket 2 is more flexible, and the longer bracket can provide better protection for the parachute recovery of the aircraft compared with the traditional design; when the load-bearing bracket 2 is folded, it is located above or below the wing 4. For a high-wing aircraft, the load-bearing bracket 2 can be set below the wing 4, and when unfolded, the load-bearing bracket 2 is directly rotated downward to open; for a low-wing aircraft, the load-bearing bracket 2 can be set above the wing 4. When unfolded, the load-bearing bracket 2 is first rotated upward and then rotated downward to open.

[0056] Here are some instructions for lower monoplane aircraft:

[0057] Combine Figure 2 In the folded state, when subjected to external force, the front support bracket 2 overcomes the elastic strain of the torsion spring 21 in its own rotating shaft and remains backward and downward. The rear support bracket 2 is treated in the same way, but forward and downward. The snap ring 24 of the front support bracket 2 is locked at the front end of the rear support bracket 2, achieving a combined state in which the front support bracket 2 is on top and the rear support bracket 2 is on the bottom, and the front support bracket 2 is folded outside the fuselage 1. Because the end face of the front support bracket 2 has an opening, after the latch 32 that moves with the folding stop pin 3 is inserted, the front support bracket 2 is locked in place, and the rear support bracket 2 is also restricted to the bottom of the front support bracket 2, forming the folded state of the aircraft energy-absorbing folding support device. Based on the reasonable trade-off between strength and weight, the diameter of the tubular support for a 200 kg aircraft is generally designed to be Φ4 cm. Therefore, the windward resistance area 22 of the support in the folded state, including the support rotating shaft, is only about 10 cm × 6 cm.

[0058] In the unfolded state, the folding stop pin 3 is actuated, driving the latch 32 to retreat and release the constraint on the front load-bearing bracket 2. The front load-bearing bracket 2 is rotated and extended upward (in conjunction with the lower single wing), outward, and forward under the elastic action of the unfolding torsion spring 21, and the rear load-bearing bracket 2 is rotated and extended upward (in conjunction with the lower single wing), outward, and backward under the elastic action of the torsion spring. When each bracket is rotated to the point where the locating pin 51 is inserted into the limiting hole 22 on the mating surface of the load-bearing bracket 2, the load-bearing bracket 2 stops. By designing the relative displacement spacing between the locating pin 51 and the limiting hole 22, the opening W1 and W2 and the height H1 of the load-bearing bracket 2 can be obtained, wherein the low height H1 corresponds to the large opening W1 and W2, which is suitable for landing on flat terrain; the large height H1 corresponds to the low opening W1 and W2, which is suitable for landing on terrain with obstacles such as stones on the ground.

[0059] Instructions for setting the rotation angle of the support 2, combined with Figure 9When the rotation axis A of the front load-bearing bracket 2 is set at a rearward acute angle (the sharp angle between the rotation axis and the axis of symmetry of the aircraft, such as 70°), the front load-bearing bracket 2 can rotate and extend upward (to match the lower monoplane wing), outward, and forward according to the trajectory of an obtuse cone (such as 140°); when the rotation axis B of the rear load-bearing bracket 2 is set at a forward acute angle (the sharp angle between the rotation axis and the axis of symmetry of the aircraft, such as 70°), the rear load-bearing bracket 2 can rotate and extend upward (to match the lower monoplane wing), outward, and backward according to the trajectory of an obtuse cone (such as 140°).

[0060] It should be noted that the design principle of the load-bearing bracket 2 used with the upper wing is the same, except that the upward rotation of the load-bearing bracket 2 is changed to a downward rotation.

[0061] The aforementioned arrangement of the load-bearing brackets 2 on both sides of the fuselage 1 involves arranging the load-bearing brackets 2 on the outside of the fuselage 1. To further reduce the windward aerodynamic drag of the folding device, the load-bearing brackets 2 can be designed as embedded structures within the fuselage skin. These specific implementations are all within the scope of protection of the present invention. The load-bearing brackets 2 in the folded state have a smaller windward cross-section and can be mounted externally or embedded within the fuselage skin. Because large aircraft have relatively high speeds and require a higher degree of aerodynamic drag reduction, they are particularly suitable for airdrop applications mounted on large aircraft.

[0062] The energy-absorbing folding support device for aircraft provided by this invention can be applied to both unmanned aerial vehicles (UAVs) and manned aircraft, expanding the operational advantages of large aircraft and achieving a 1+1>2 effect. It is particularly useful in special operations such as emergency rescue and emergency communications. For other structural details of the aircraft, please refer to the prior art and will not be elaborated upon in this invention.

[0063] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An energy-absorbing folding support device for an aircraft, characterized in that: It comprises four load-bearing supports (2), wherein the four load-bearing supports (2) are divided into two groups, a left group and a right group, and each group comprises two front and rear load-bearing supports (2); Each of the load-bearing brackets (2) is rotatably mounted on a support (5) provided on the fuselage (1), and the load-bearing bracket (2) rotates relative to the support (5) to achieve folding or unfolding; Wherein, in the unfolded state, the four load-bearing supports (2) are spread out in an eight-shaped shape to support the fuselage (1) to touch the ground; the front load-bearing support (2) can be rotated backward to be folded, and the rear load-bearing support (2) can be rotated forward to be folded, and the two load-bearing supports (2) in the same group are overlapped on the side of the fuselage (1); The left and right groups of the load-bearing supports (2) are each provided with a folding stop pin (3), the folding stop pin (3) comprising a telescopic mechanism (31) and a latch (32), the telescopic mechanism (31) being capable of driving the latch (32) to move, and the latch (32) being capable of being inserted into the ground contacting end of the load-bearing support (2) that is later in the folding sequence to keep the load-bearing support (2) in a folded state; A snap ring (24) is provided between the two load-bearing supports (2) in the same group, and the load-bearing support (2) in the later folding order is kept in the folded state by the snap ring (24); A positioning pin (51) and an ejection spring (52) are provided on the support (5), and a limiting hole (22) is provided on the load-bearing bracket (2); When the limiting hole (22) is rotated to a position facing the positioning pin (51), the ejection spring (52) pushes the positioning pin (51) to be inserted into the limiting hole (22) to limit the relative angle between the support (5) and the load-bearing bracket (2); The number of the positioning pins (51) is set to be more than two, and the limiting holes (22) are set on circles of different radii and at unequal distances from the center of the circle; each positioning pin (51) is correspondingly provided with one limiting hole (22); Wherein, at the same time, only one positioning pin (51) is inserted into its corresponding limiting hole (22); after the positioning pin (51) is broken by impact to absorb energy and buffer, the load-bearing bracket (2) is further rotated relative to the support (5) to allow the next positioning pin (51) to be inserted into its corresponding limiting hole (22), thereby achieving step-by-step buffering.

2. The aircraft energy-absorbing folding support device according to claim 1, characterized in that: An expansion torsion spring (21) is provided between the load-bearing bracket (2) and the support (5), and the expansion torsion spring (21) applies a torque to the load-bearing bracket (2) to rotate it toward the expansion state.

3. The aircraft energy-absorbing folding support device according to claim 1, characterized in that: The radius between each positioning pin (51) and the axis is not equal, and the central angle of two adjacent positioning pins (51) is not equal to the central angle of two corresponding adjacent limiting holes (22).

4. The aircraft energy-absorbing folding support device according to claim 3, characterized in that: The rigidity of the last positioning pin (51) for bearing shear force is greater than the shear force generated during impact.

5. The aircraft energy-absorbing folding support device according to claim 4, characterized in that: Each of the load-bearing supports (2) comprises at least two segments; Among them, in the unfolded state, the strength of each segment gradually weakens from top to bottom, so as to achieve step-by-step self-destruction and energy absorption of each segment.

6. The aircraft energy-absorbing folding support device according to claim 5, characterized in that: Two adjacent segments are plugged into each other and fitted together. A shock-absorbing spring (23) is provided between the two plugged segments, and the shock-absorbing spring (23) compresses and absorbs impact energy.

7. The aircraft energy-absorbing folding support device according to claim 5, characterized in that: The support (5) is mounted on the front frame beam or the rear frame beam of the fuselage (1), and the load-bearing bracket (2) is located above or below the wing (4) when folded.

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