CN112027119B - Reusable rocket landing leg collapse energy-absorbing bidirectional buffer - Google Patents
Reusable rocket landing leg collapse energy-absorbing bidirectional buffer Download PDFInfo
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- CN112027119B CN112027119B CN202010797646.2A CN202010797646A CN112027119B CN 112027119 B CN112027119 B CN 112027119B CN 202010797646 A CN202010797646 A CN 202010797646A CN 112027119 B CN112027119 B CN 112027119B
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
Abstract
The invention relates to a collapse energy-absorbing bidirectional buffer for a repeatedly used rocket landing leg, belonging to the field of rocket landing leg design; the device comprises an outer barrel component, an inner barrel component, a drop buffering honeycomb component and an expansion buffering honeycomb component; the open end of the outer cylinder component is vertically placed downwards; the closed end at the top end of the outer cylinder component is coaxially butted with an external rocket landing leg; the falling shock buffering honeycomb component is arranged in the inner cavity of the outer cylinder component; the opening end of the inner cylinder component is vertically placed downwards; the closed end of the top end of the inner cylinder component extends into the outer cylinder component from the open end of the outer cylinder component, and the falling shock buffering honeycomb component is arranged between the outer wall of the top end of the inner cylinder component and the inner wall of the top end of the outer cylinder component; the unfolding buffer honeycomb component extends into the inner cylinder component from the opening end of the inner cylinder component; the invention realizes the buffering and energy absorption of impact in the processes of landing leg expansion and falling shock, reduces the impact on the rocket body structure and protects the safety of the rocket.
Description
Technical Field
The invention belongs to the field of rocket landing leg design, and relates to a collapse energy-absorbing bidirectional buffer for a reusable rocket landing leg.
Background
When the vertical take-off and landing repeatedly uses the rocket for landing, the landing legs are unfolded and locked, and then the impact of the rocket for landing is buffered. The tip of the landing leg needs to be provided with a buffer with bidirectional buffering capacity, so that impact in the two processes of unfolding and falling shock of the landing leg is buffered and energy-absorbed, the safety of the rocket structure is protected, and the landing stability is improved.
The reusable rocket landing leg buffer can meet the requirement of expanding/landing bidirectional buffering energy absorption, and has strong buffering capacity and high compression ratio. The existing landing buffer can realize buffering mainly by a multi-cell material deformation method, a thin-wall metal pipe deformation method, a hydraulic damping method, a special material stretching method and the like. The aluminum honeycomb buffering energy absorption is mainly used for landing buffering and generally only has unidirectional buffering capacity; the deformation method of the thin-wall metal pipe absorbs energy by means of plastic expanding deformation and friction heating of the thin-wall metal pipe, can be used for buffering the seat of an astronaut, and has large influence on performance consistency due to lubrication. The hydraulic damper has the advantages of strong load adaptability, complex structure, heavy weight, high sealing requirement and large influence of parameters such as density, pressure, viscosity coefficient, temperature and the like of liquid and gas on performance. The special material stretching method buffers energy through plastic stretching deformation of the pull rod, can be used for a bidirectional buffer needing stretching buffering, but needs to adopt a superplastic material, has high requirements on material performance and has limited buffering capacity.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the collapse energy-absorbing bidirectional buffer for the landing leg of the rocket is repeatedly used, the impact of the expansion and falling shock process of the landing leg is buffered and absorbed, the impact on the rocket body structure is reduced, and the safety of the rocket is protected.
The technical scheme of the invention is as follows:
a reusable rocket landing leg collapse energy-absorbing bidirectional buffer comprises an outer cylinder component, an inner cylinder component, a drop buffering honeycomb component and an unfolding buffering honeycomb component; wherein, the outer cylinder component is a hollow cylindrical structure with one open end; the open end of the outer cylinder component is vertically placed downwards; the closed end at the top end of the outer cylinder component is coaxially butted with an external rocket landing leg; the falling shock buffering honeycomb component is arranged in the inner cavity of the outer cylinder component; the inner cylinder component is a hollow cylindrical structure with one open end; the opening end of the inner cylinder component is vertically placed downwards; the closed end of the top end of the inner cylinder component extends into the outer cylinder component from the open end of the outer cylinder component, and the falling shock buffering honeycomb component is arranged between the outer wall of the top end of the inner cylinder component and the inner wall of the top end of the outer cylinder component; the unfolding buffer honeycomb component extends into the inner cylinder component from the opening end of the inner cylinder component; the bottom end of the deployed buffer honeycomb assembly is connected with an external landing foot.
In the above-mentioned reusable rocket landing leg collapse energy-absorbing bidirectional buffer, the outer cylinder component comprises an outer cylinder, a locking device and a limiting block; the outer cylinder is a hollow cylindrical structure with one open end; the locking device is fixedly arranged on the outer side wall of the top end of the outer cylinder; the top of the outer cylinder is butted with an external rocket landing leg through a locking device; the limiting block is arranged on the inner wall of the lower end opening end of the outer cylinder; when the inner cylinder component moves in the outer cylinder along the axial direction, the limiting block prevents the inner cylinder component from being separated from the outer cylinder.
In the above collapse energy-absorbing bidirectional buffer for landing legs of a reusable rocket, the inner cylinder component comprises an inner cylinder, an anti-friction ring, an inner cylinder plug cover, a rubber pad, a support frame and a retaining nail; wherein, the inner cylinder is a hollow cylindrical structure with one open end; the anti-friction ring is sleeved on the outer wall of the top end of the inner cylinder; when the inner cylinder moves in the outer cylinder, friction is reduced; the inner cylinder plug cover is arranged at the top end of the inner cylinder to realize the sealing of the top of the inner cylinder; the supporting frame is fixedly arranged at the top of the inner cylinder plug cover; the rubber pad is fixedly arranged at the top of the support frame; the stopping nails are uniformly arranged at the top end of the inner cylinder plug cover in a surrounding way.
In the above-mentioned reusable rocket landing leg collapse energy-absorbing bidirectional buffer, the drop buffering honeycomb component comprises 3 drop buffering honeycombs, 3 retainers, honeycomb end covers, blanking caps and 3 antifriction sleeves; wherein, the drop buffering honeycomb is a columnar structure; 3 drop shock buffering honeycombs are coaxially arranged along the vertical direction; the section of the retainer is of a T-shaped annular structure; wherein, 1 retainer is sleeved on the outer wall of the bottom end of the bottommost drop shock buffering honeycomb; the other 2 retainers are respectively sleeved at the joints of the adjacent 2 falling shock buffering honeycombs; the honeycomb end cover is fixedly arranged at the top end of the topmost drop buffering honeycomb; the plugging cover is arranged at the top of the honeycomb end cover; the outer wall of each retainer is correspondingly sleeved with 1 antifriction sleeve.
In the above-mentioned reusable rocket landing leg collapse energy-absorbing bidirectional buffer, when the inner cylinder component moves in the inner cavity of the outer cylinder component along the axial direction, the rubber pad pushes the bottommost drop-absorbing buffer honeycomb, so that the 3 drop-absorbing buffer honeycombs are kept coaxial.
In the above-mentioned reusable rocket landing leg collapse energy-absorbing bidirectional buffer, the top end of the backstop nail is provided with a barb; the backstop nail stretches into the interior of the bottommost drop shock buffering honeycomb, and the inner barrel is prevented from being separated from the bottommost drop shock buffering honeycomb through the barb.
In the above-mentioned reusable rocket landing leg collapse energy-absorbing bidirectional buffer, the honeycomb end cover is a disc-shaped structure; the surface of honeycomb end cover is provided with the type through-hole that diverges of snowflake form, when the inner tube subassembly was at outer section of thick bamboo subassembly inner chamber along axial displacement, realizes discharging the gas of honeycomb end cover below through the type through-hole that diverges, reduces the resistance.
In the above-mentioned reusable rocket landing leg collapse energy-absorbing bidirectional buffer, the expansion buffering honeycomb component comprises a buffer ejector rod, a joint bearing, a lower end cover, a joint, a screwing nut, an expansion buffering honeycomb, a honeycomb pressing plate, a spring retainer and a spring; wherein, the buffer ejector rod is a rod-shaped structure extending into the inner cylinder; the joint bearing is arranged at the axial bottom end of the buffer ejector rod; the landing leg is connected with an external landing leg through a joint bearing; the honeycomb pressing plate is fixedly sleeved on the outer wall of the axial ejector rod of the buffer ejector rod; the joint is sleeved on the outer wall of the middle part of the buffer ejector rod; the lower end cover is sleeved on the outer wall of the joint; the lower end cover is fixedly connected with the inner wall of the opening end of the inner cylinder, and the joint is fixedly connected with the lower end cover; the tightening nut is sleeved on the outer wall of the buffer ejector rod and is positioned below the joint in the axial direction; the unfolded buffering honeycomb is sleeved on the outer wall of the buffer ejector rod and is in contact with the lower surface of the honeycomb pressing plate; the spring retainer is arranged between the expansion buffer honeycomb and the lower end cover; the spring is arranged in the spring retainer.
When the landing leg of the external rocket is extended to prepare for landing, the buffer ejector rod drives the honeycomb pressing plate to vertically move downwards under the action of gravity; under the limiting action of the lower end cover, the honeycomb pressing plate compresses and expands the buffering honeycomb and the spring downwards to buffer gravity; after the stabilization, the expansion buffering honeycomb recovers under the action of the spring resetting force.
When an external landing foot connected with a joint bearing contacts with the ground, a buffer ejector rod vertically moves upwards under the action of a reaction force, and a tightening nut pushes a joint, a lower end cover and an inner cylinder to integrally and vertically move upwards along the axial direction; and the falling shock buffering honeycomb assembly is compressed to realize buffering.
Compared with the prior art, the invention has the beneficial effects that:
(1) on the basis of meeting the requirements of geometric overall dimension and interface for repeatedly using rocket landing leg tip installation, the invention designs energy absorption materials, bidirectional buffer implementation forms, reset function implementation modes and the like, and realizes preset functions through the combination of a plurality of parts;
(2) the invention can be used for buffering the impact of the falling shock during the landing of the rocket and the impact caused by the inertia force when the landing leg is unfolded in place, thereby forming the bidirectional buffering capacity. The purpose of adjusting the product performance of the mechanism is achieved through replacement and quantity change of key parts, so that the requirements of different use environments are met.
Drawings
FIG. 1 is a schematic overall view and a schematic sectional view of a bi-directional buffer according to the present invention;
FIG. 2 is a schematic view of the outer barrel assembly of the present invention;
FIG. 3 is a schematic view of the inner barrel assembly of the present invention;
FIG. 4 is a schematic view of a drop cushioning honeycomb assembly of the present invention;
FIG. 5 is a schematic view of a honeycomb end cap of the present invention;
FIG. 6 is a schematic view of an unfolded cushioning honeycomb assembly of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
In the technology of reusing the rocket recovery mechanism in vertical take-off and landing, when a first-stage rocket is about to land, the expansion and locking of the landing legs are required to be completed to help the rocket realize vertical landing.
The landing legs arranged on the tail section/rear transition section of the rocket are tightly attached to the surface of the rocket body in a folded state in the ascending section of the main task of the rocket so as to reduce the resistance. The landing legs are unfolded before landing to complete the landing of the rocket and provide support for the rocket. The invention provides a collapse energy-absorbing bidirectional buffer for landing legs of a reusable rocket, wherein the tip of each landing leg is provided with a buffer, so that impact in the processes of unfolding and falling shock of the landing leg is buffered and absorbed, the impact on a rocket body structure is reduced, and the safety of the rocket is protected.
The landing leg is unfolded by means of self gravity or active pushing impact force and the like, and self locking is completed when the landing leg is unfolded in place, so that the landing leg becomes a stable supporting structure. The landing legs are unfolded in place at a certain angular speed, and when the landing legs are locked, the buffer is required to absorb impact energy caused by self inertia force, so that the impact of the landing legs on the rocket body structure when the landing legs are unfolded in place is reduced, and the safety and the stability of the rocket body are ensured. The rocket still has a certain descending speed when landing, and the self weight of the rocket is larger, so that larger landing impact force and energy can be formed, the impact force is reduced by a buffer and the impact energy is absorbed, and the safety and the landing stability of the rocket body are ensured.
The buffer is required to be capable of being arranged at the tip of the landing leg to reliably complete the preset actions such as unfolding locking and the like, can meet the requirements of bidirectional buffering and energy absorption for unfolding/landing, and can stably work under the severe thermal environment.
A rocket landing leg collapse energy-absorbing bidirectional buffer which is reused and mainly comprises an outer cylinder component 1, an inner cylinder component 2, a drop buffering honeycomb component 3 and an unfolding buffering honeycomb component 4 as shown in figure 1; wherein, the outer cylinder component 1 is a hollow cylindrical structure with one open end; the open end of the outer cylinder component 1 is vertically placed downwards; the closed end of the top end of the outer cylinder component 1 is coaxially butted with an external rocket landing leg; the falling shock buffering honeycomb component 3 is arranged in the inner cavity of the outer cylinder component 1; the inner cylinder component 2 is a hollow cylindrical structure with one open end; the opening end of the inner cylinder component 2 is vertically placed downwards; the closed end of the top end of the inner cylinder component 2 extends into the component of the outer cylinder component 1 from the open end of the outer cylinder component 1, and the falling shock buffering honeycomb component 3 is arranged between the outer wall of the top end of the inner cylinder component 2 and the inner wall of the top end of the outer cylinder component 1; the unfolding buffer honeycomb component 4 extends into the inner cylinder component 2 from the opening end of the inner cylinder component 2; the bottom end of the deployed buffer honeycomb assembly 4 is connected to an external landing foot. As shown in fig. 1. The inner cylinder component 2 is coaxial with the outer cylinder component 1, the inner cylinder component 2 can move towards the inside of the outer cylinder component 1 along the axial direction, so that the falling shock buffering honeycomb component 3 arranged inside the outer cylinder component 1 is compressed, and the impact energy of landing legs during rocket landing is absorbed through the collapse energy absorption effect of the honeycomb material. The deployment buffer honeycomb assembly 4 is installed inside the inner cylinder assembly 2.
The specific structure of the outer cylinder component 1 is shown in figure 2, and comprises an outer cylinder 1-1, a locking device 1-2 and a limiting block 1-3; the outer cylinder 1-1 is a thin-wall cylindrical part, the upper end of the outer cylinder is provided with a locking device 1-2 used for being connected with the landing leg main body part, the inner cylinder 2-1 is sleeved inside the outer cylinder 1-1, and the bottom of the outer cylinder is connected with a limiting block 1-3 used for limiting the outward axial displacement of the inner cylinder 2-1 relative to the outer cylinder. The outer cylinder 1-1 is a hollow cylindrical structure with one open end; the locking device 1-2 is fixedly arranged on the outer side wall of the top end of the outer cylinder 1-1; the top of the outer cylinder 1-1 is butted with an external rocket landing leg through a locking device 1-2; the limiting block 1-3 is arranged on the inner wall of the lower end opening end of the outer cylinder 1-1; when the inner cylinder component 2 moves in the outer cylinder 1-1 along the axial direction, the limiting blocks 1-3 prevent the inner cylinder component 2 from being separated from the outer cylinder 1-1.
The inner cylinder component 2 is shown in figure 3 and comprises an inner cylinder 2-1, an anti-friction ring 2-2, an inner cylinder plug cover 2-3, a rubber pad 2-4, a support frame 2-5 and a backstop nail 2-6; wherein, the inner cylinder 2-1 is a hollow cylindrical structure with one open end; the antifriction ring 2-2 is sleeved on the outer wall of the top end of the inner cylinder 2-1; the friction is reduced when the inner cylinder 2-1 moves in the outer cylinder 1-1; the inner cylinder plug 2-3 is arranged at the top end of the inner cylinder 2-1 to realize the sealing of the top of the inner cylinder 2-1; the support frame 2-5 is fixedly arranged at the top of the inner cylinder plug cover 2-3; the rubber pad 2-4 is fixedly arranged at the top of the support frame 2-5; the retaining nails 2-6 are uniformly arranged at the top end of the inner cylinder block cover 2-3 in a surrounding way.
The falling shock buffering honeycomb component 3 is a cylindrical component and is arranged inside the outer barrel 1-1, the inner barrel component 2 is pressed to move axially along the buffer when the rocket lands so as to compress the honeycomb, and the impact is reduced through the collapse energy absorption performance of the honeycomb material. The falling shock buffering honeycomb component 3 is formed by connecting a plurality of falling shock buffering honeycombs 3-1, a retainer 3-2 and an antifriction sleeve 3-5 in series, and the buffering and energy absorbing capacity of the buffer can be changed by adjusting the height of a single falling shock buffering honeycomb 3-1 and the performance of the honeycomb. The plug cover 3-4 is used for being connected with the outer barrel and has an axial limiting function on the honeycomb, the honeycomb end cover 3-3 is provided with air holes in the middle of the figure 5, and the air holes are formed in the air holes, so that when the falling shock buffering honeycomb 3-1 is pressed, the air in the outer barrel 1-1 can be reserved from the air holes and the air holes, and the phenomenon that the air in the closed cavity is pressed to generate extra buffering force except for honeycomb buffering, the actual buffering force is greater than a pre-calculated value, and the force value is too large to damage the structure is avoided. As shown in fig. 4, the drop shock buffering honeycomb assembly 3 comprises 3 drop shock buffering honeycombs 3-1, 3 retainers 3-2, a honeycomb end cover 3-3, a plugging cover 3-4 and 3 antifriction sleeves 3-5; wherein, the drop shock buffering honeycomb 3-1 is a columnar structure; 3 drop shock buffering honeycombs 3-1 are coaxially arranged along the vertical direction; the section of the retainer 3-2 is of a T-shaped annular structure; wherein 1 retainer 3-2 is sleeved on the outer wall of the bottom end of the bottommost dropping buffer honeycomb 3-1; the other 2 retainers 3-2 are respectively sleeved at the joints of the adjacent 2 falling shock buffering honeycombs 3-1; the honeycomb end cover 3-3 is fixedly arranged at the top end of the topmost drop buffering honeycomb 3-1; the plugging cover 3-4 is arranged at the top of the honeycomb end cover 3-3; the outer wall of each retainer 3-2 is correspondingly sleeved with 1 antifriction sleeve 3-5.
When the inner cylinder component 2 moves in the inner cavity of the outer cylinder component 1 along the axial direction, the rubber pad 2-4 pushes the bottommost drop shock buffering honeycomb 3-1, and 3 drop shock buffering honeycombs 3-1 are kept coaxial. The inner cylinder component 2 plays a role in compressing the falling shock buffering honeycomb 3-1, the rubber pad 2-4 and the supporting frame 2-5 are installed at the top end of the inner cylinder 2-1, and the rubber pad 2-4 is in a pressed state after installation is completed, so that assembly dimension errors caused by tolerance accumulation can be eliminated, and shaking of the inner cylinder 2-1 in rocket flight is avoided.
The top end of the inner cylinder 2-1 is provided with a retaining nail 2-6 which has the function of being inserted into the collapsed honeycomb when the inner cylinder compresses the honeycomb and is connected with the honeycomb into a whole, so that the inner cylinder 2-1 is prevented from being relatively far away from the honeycomb when the rocket lands and bounces. The top ends of the backstop nails 2-6 are provided with barbs; the backstop nail 2-6 extends into the bottom-most falling shock buffering honeycomb 3-1, and the inner barrel 2-1 is prevented from being separated from the bottom-most falling shock buffering honeycomb 3-1 through the barb.
As shown in fig. 5, the honeycomb end cap 3-3 has a disk-like structure; the surface of the honeycomb end cover 3-3 is provided with snowflake-shaped divergent through holes, and when the inner cylinder assembly 2 moves in the inner cavity of the outer cylinder assembly 1 along the axial direction, gas below the honeycomb end cover 3-3 is discharged through the divergent through holes, so that resistance is reduced.
The specific structure of the expanded buffer honeycomb component 4 is shown in FIG. 6, and comprises a buffer ejector rod 4-1, a knuckle bearing 4-2, a lower end cover 4-3, a joint 4-4, a tightening nut 4-5, an expanded buffer honeycomb 4-6, a honeycomb pressing plate 4-7, a spring retainer 4-8 and a spring 4-9; wherein, the buffer mandril 4-1 is a rod-shaped structure extending into the inner cylinder 2-1; the knuckle bearing 4-2 is arranged at the axial bottom end of the buffer ejector rod 4-1; the connection with an external landing foot is realized through a joint bearing 4-2; the honeycomb pressing plate 4-7 is fixedly sleeved on the outer wall of the buffer ejector rod 4-1 axial ejector rod; the joint 4-4 is sleeved on the outer wall of the middle part of the buffer ejector rod 4-1; the lower end cover 4-3 is sleeved on the outer wall of the joint 4-4; the lower end cover 4-3 is fixedly connected with the inner wall of the opening end of the inner cylinder 2-1, and the joint 4-4 is fixedly connected with the lower end cover 4-3; the tightening nut 4-5 is sleeved on the outer wall of the buffer ejector rod 4-1 and is positioned below the joint 4-4 in the axial direction; the expansion buffering honeycomb 4-6 is sleeved on the outer wall of the buffer ejector rod 4-1 and is in contact with the lower surface of the honeycomb pressing plate 4-7; the spring retainer 4-8 is arranged between the expansion buffer honeycomb 4-6 and the lower end cover 4-3; the spring 4-9 is arranged in the spring holder 4-8.
When the landing leg of the external rocket is extended to prepare for landing, the buffer ejector rod 4-1 drives the honeycomb pressing plate 4-7 to vertically move downwards under the action of gravity; under the limiting action of the lower end cover 4-3, the honeycomb pressing plate 4-7 compresses and expands the buffer honeycomb 4-6 and the spring 4-9 downwards to realize the buffering of gravity; after the stabilization, the unfolding buffer honeycombs 4-6 are recovered under the action of the restoring force of the springs 4-9. When an external landing foot connected with the joint bearing 4-2 contacts the ground, under the action of a reaction force, the buffer ejector rod 4-1 vertically moves upwards, and the joint 4-4, the lower end cover 4-3 and the inner cylinder 2-1 are pushed to integrally move upwards vertically along the axial direction by screwing the nut 4-5; and the falling shock buffering honeycomb component 3 is compressed to realize buffering.
When the rocket landing leg is unfolded in place, the unfolding speed and the self mass of the rocket landing leg can form a large inertia force load. One end of the unfolding buffer cellular component is connected with the inner buffer cylinder, and the other end of the unfolding buffer cellular component is connected with a tip structure of the landing leg, and the main purpose of the unfolding buffer cellular component is to reduce the impact when the landing leg is unfolded in place.
The lower end cover 4-3 and the joint 4-4 are connected with the inner barrel of the buffer, and the buffer ejector rod 4-1 penetrates through the round holes at the centers of the lower end cover 4-3 and the joint 4-4 and can slide relative to the round holes along the axial direction. The bottom end of the buffer ejector rod 4-1 is embedded with a joint bearing 4-2 which is used for being connected with a landing leg, and the buffer ejector rod 4-1 can be pulled outwards when the landing leg is unfolded in place. A boss with threads is arranged in the middle of the buffer ejector rod 4-1, double nuts are used for limiting the axial displacement of the buffer ejector rod 4-1 towards the inner cylinder 2-1, namely, the falling shock impact is transmitted to the inner cylinder 2-1 from the tip of a landing leg through the buffer ejector rod 4-1 when the rocket lands, and then the falling shock buffering honeycomb component 3 is compressed to realize buffering.
A cylindrical expansion buffer honeycomb 4-6 is arranged in the inner cylinder 2-1, a through hole is formed in the center of the honeycomb and can be sleeved outside the buffer ejector rod 4-1, and a honeycomb pressing plate 4-7 is connected to the top end of the buffer ejector rod 4-1. When the landing legs are unfolded in place, the landing legs can drive the buffer ejector rods 4-1 to move outwards along the axial direction, and further pull the honeycomb pressing plates 4-7 to transfer loads to the unfolded buffer honeycombs 4-6, so that the honeycombs are crushed to absorb energy, and the impact force is reduced.
A spring retainer 4-8 and a spring 4-9 are arranged between the expansion buffer honeycomb 4-7 and the lower end cover 4-3, and the purpose is to contract and reset the buffer after the expansion buffer process is finished. In the initial state of the buffer installation, the springs 4-9 are in a compressed state, and the force of the springs 4-9 is smaller than the crushing critical value of the unfolded buffer honeycomb 4-7, so that the initial state of the springs does not influence the performance of the honeycomb or crush the honeycomb in advance. When the unfolding buffering process is finished, the unfolding buffering honeycombs 4-7 are completely or partially crushed, and the height is reduced. The spring 4-9 loses the compression limit along the axial direction and extends to push the expansion buffering honeycomb to expand the buffering honeycomb 4-6, the honeycomb pressing plate 4-7 and the buffer ejector rod 4-1, so that the buffer is reset from the elongated state and is ready for landing and falling shock buffering.
The invention provides a design method of a collapse energy-absorbing bidirectional buffer for a reusable rocket landing leg, which is characterized in that on the basis of meeting the requirements of geometric overall dimension and interface of tip installation of the reusable rocket landing leg, an energy-absorbing material, a bidirectional buffer implementation form, a reset function implementation form and the like are designed, and a preset function is realized through combination of a plurality of parts; the purpose of product performance of the adjusting mechanism is achieved through replacement of key parts and quantity change, so that the requirements of different use environments are met.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (6)
1. The utility model provides a two-way buffer of energy-absorbing of landing leg collapse of used repeatedly rocket which characterized in that: comprises an outer cylinder component (1), an inner cylinder component (2), a drop buffering honeycomb component (3) and an expansion buffering honeycomb component (4); wherein, the outer cylinder component (1) is a hollow cylindrical structure with one open end; the open end of the outer cylinder component (1) is vertically placed downwards; the closed end of the top end of the outer cylinder component (1) is coaxially butted with an external rocket landing leg; the falling shock buffering honeycomb component (3) is arranged in the inner cavity of the outer cylinder component (1); the inner cylinder component (2) is a hollow cylindrical structure with one open end; the opening end of the inner cylinder component (2) is vertically placed downwards; the closed end of the top end of the inner barrel component (2) extends into the outer barrel component (1) from the open end of the outer barrel component (1), and the falling shock buffering honeycomb component (3) is arranged between the outer wall of the top end of the inner barrel component (2) and the inner wall of the top end of the outer barrel component (1); the unfolding buffer honeycomb component (4) extends into the inner cylinder component (2) from the opening end of the inner cylinder component (2); the bottom end of the unfolding buffer honeycomb component (4) is connected with an external landing foot;
The outer cylinder component (1) comprises an outer cylinder (1-1), a locking device (1-2) and a limiting block (1-3); the outer cylinder (1-1) is a hollow cylindrical structure with one open end; the locking device (1-2) is fixedly arranged on the outer side wall of the top end of the outer cylinder (1-1); the top of the outer cylinder (1-1) is butted with an external rocket landing leg through a locking device (1-2); the limiting block (1-3) is arranged on the inner wall of the opening end at the bottom end of the outer cylinder (1-1); when the inner cylinder component (2) moves in the outer cylinder (1-1) along the axial direction, the limiting block (1-3) prevents the inner cylinder component (2) from being separated from the outer cylinder (1-1);
the inner cylinder component (2) comprises an inner cylinder (2-1), an anti-friction ring (2-2), an inner cylinder plug cover (2-3), a rubber pad (2-4), a support frame (2-5) and a backstop nail (2-6); wherein, the inner cylinder (2-1) is a hollow cylindrical structure with one open end; the anti-friction ring (2-2) is sleeved on the outer wall of the top end of the inner cylinder (2-1); the friction is reduced when the inner cylinder (2-1) moves in the outer cylinder (1-1); the inner cylinder plug cover (2-3) is arranged at the top end of the inner cylinder (2-1) to realize the sealing of the top of the inner cylinder (2-1); the supporting frame (2-5) is fixedly arranged at the top of the inner cylinder plug cover (2-3); the rubber pad (2-4) is fixedly arranged at the top of the support frame (2-5); the retaining nails (2-6) are uniformly arranged at the top end of the inner cylinder plug cover (2-3) in a surrounding way;
The drop shock buffering honeycomb component (3) comprises 3 drop shock buffering honeycombs (3-1), 3 retainers (3-2), honeycomb end covers (3-3), plugging covers (3-4) and 3 antifriction sleeves (3-5); wherein the falling shock buffering honeycomb (3-1) is of a columnar structure; 3 drop shock buffering honeycombs (3-1) are coaxially arranged along the vertical direction; the section of the retainer (3-2) is of a T-shaped annular structure; wherein 1 retainer (3-2) is sleeved on the outer wall of the bottom end of the bottommost falling shock buffering honeycomb (3-1); the other 2 retainers (3-2) are respectively sleeved at the joints of the adjacent 2 falling shock buffering honeycombs (3-1); the honeycomb end cover (3-3) is fixedly arranged at the top end of the topmost drop shock buffering honeycomb (3-1); the plugging cover (3-4) is arranged at the top of the honeycomb end cover (3-3); the outer wall of each retainer (3-2) is correspondingly sleeved with 1 antifriction sleeve (3-5);
the unfolding buffer honeycomb component (4) comprises a buffer ejector rod (4-1), a joint bearing (4-2), a lower end cover (4-3), a connector (4-4), a screwing nut (4-5), an unfolding buffer honeycomb (4-6), a honeycomb pressing plate (4-7), a spring retainer (4-8) and a spring (4-9); wherein, the buffer ejector rod (4-1) is a rod-shaped structure extending into the inner cylinder (2-1); the joint bearing (4-2) is arranged at the axial bottom end of the buffer ejector rod (4-1); the connection with an external landing foot is realized through a joint bearing (4-2); the honeycomb pressing plate (4-7) is fixedly sleeved on the outer wall of the axial ejector rod of the buffer ejector rod (4-1); the joint (4-4) is sleeved on the outer wall of the middle part of the buffer ejector rod (4-1); the lower end cover (4-3) is sleeved on the outer wall of the joint (4-4); the lower end cover (4-3) is fixedly connected with the inner wall of the opening end of the inner cylinder (2-1), and the joint (4-4) is fixedly connected with the lower end cover (4-3); the tightening nut (4-5) is sleeved on the outer wall of the buffer ejector rod (4-1) and is positioned below the joint (4-4) in the axial direction; the unfolding buffer honeycomb (4-6) is sleeved on the outer wall of the buffer ejector rod (4-1) and is in contact with the lower surface of the honeycomb pressing plate (4-7); the spring retainer (4-8) is arranged between the expansion buffer honeycomb (4-6) and the lower end cover (4-3); the springs (4-9) are arranged in the spring holders (4-8).
2. A reusable rocket landing leg collapse energy absorbing bi-directional bumper as recited in claim 1, further comprising: when the inner cylinder assembly (2) moves in the inner cavity of the outer cylinder assembly (1) along the axial direction, the rubber pad (2-4) pushes the bottommost drop shock buffering honeycomb (3-1), and 3 drop shock buffering honeycombs (3-1) are kept coaxial.
3. A reusable rocket landing leg collapse energy absorbing bi-directional bumper as recited in claim 2, further comprising: the top ends of the retaining nails (2-6) are provided with barbs; the backstop nails (2-6) extend into the bottommost drop shock buffering honeycomb (3-1), and the inner barrel (2-1) is prevented from being separated from the bottommost drop shock buffering honeycomb (3-1) through the barbs.
4. A reusable rocket landing leg collapse energy absorbing bi-directional bumper as recited in claim 3, further comprising: the honeycomb end cover (3-3) is of a disc-shaped structure; the surface of the honeycomb end cover (3-3) is provided with snowflake-shaped divergent through holes, and when the inner cylinder assembly (2) moves in the inner cavity of the outer cylinder assembly (1) along the axial direction, gas below the honeycomb end cover (3-3) is discharged through the divergent through holes, so that the resistance is reduced.
5. A reusable rocket landing leg collapse energy absorbing bi-directional bumper as recited in claim 4, further comprising: when the landing leg of the external rocket is extended to prepare for landing, the buffer ejector rod (4-1) drives the honeycomb pressing plate (4-7) to vertically move downwards under the action of gravity; under the limiting action of the lower end cover (4-3), the honeycomb pressing plate (4-7) compresses and expands the buffering honeycomb (4-6) and the spring (4-9) downwards to buffer gravity; after the stabilization, the unfolding buffer honeycombs (4-6) are recovered under the action of the reset force of the springs (4-9).
6. A reusable rocket landing leg collapse energy absorbing bi-directional bumper as recited in claim 5, further comprising: when an external landing foot connected with the joint bearing (4-2) is in contact with the ground, under the action of a reaction force, the buffer ejector rod (4-1) moves vertically upwards, and the joint (4-4), the lower end cover (4-3) and the inner cylinder (2-1) are pushed to integrally move upwards vertically along the axial direction by tightening the nut (4-5); and compressing the falling shock buffering honeycomb assembly (3) to realize buffering.
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| CN202010797646.2A CN112027119B (en) | 2020-08-10 | 2020-08-10 | Reusable rocket landing leg collapse energy-absorbing bidirectional buffer |
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| CN202010797646.2A CN112027119B (en) | 2020-08-10 | 2020-08-10 | Reusable rocket landing leg collapse energy-absorbing bidirectional buffer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112722337B (en) * | 2021-01-23 | 2022-06-07 | 吉林大学 | Gradient energy-absorbing inner core planet detection buffering landing leg based on memory alloy |
| CN113844679B (en) * | 2021-08-31 | 2024-02-09 | 北京宇航系统工程研究所 | Wide-angle multi-buffer deformation assembly landing supporting mechanism |
| CN114111462B (en) * | 2021-10-29 | 2023-07-14 | 北京宇航系统工程研究所 | High-light landing buffer mechanism of reusable carrier rocket |
| CN114132532B (en) * | 2022-01-12 | 2023-09-29 | 北京中科宇航技术有限公司 | Landing leg mechanism for recovering rocket |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3525511A (en) * | 1967-02-10 | 1970-08-25 | Automotive Prod Co Ltd | Shock absorbers |
| JP2934494B2 (en) * | 1990-10-24 | 1999-08-16 | 宇宙開発事業団 | Collectible spacecraft |
| JP2004036871A (en) * | 2002-07-02 | 2004-02-05 | Reiko Koganei | Semiactive hydraulic shock absorber |
| CN105659777B (en) * | 2007-02-15 | 2012-02-22 | 北京空间飞行器总体设计部 | One landing seeker soft landing mechanism buffer |
| CN202451680U (en) * | 2011-12-23 | 2012-09-26 | 北京空间飞行器总体设计部 | Landing detector deformation buffer |
| KR20130139619A (en) * | 2012-06-13 | 2013-12-23 | 한국항공우주연구원 | Shock absorber for spacecraft lander |
| CN106704433A (en) * | 2017-01-12 | 2017-05-24 | 南京航空航天大学 | Bidirectional buffer with driving function |
| CN107972894A (en) * | 2017-11-01 | 2018-05-01 | 北京宇航系统工程研究所 | A kind of Control System for Reusable Launch Vehicle landing and buffering device |
| CN109178350A (en) * | 2018-09-28 | 2019-01-11 | 南京航空航天大学 | A kind of retractable driving device having tension compression bidirectional pooling feature |
| CN109307032A (en) * | 2018-11-15 | 2019-02-05 | 南京航空航天大学 | A kind of reusable passive energy-absorbing draws/press bidirectional buffer |
| CN109436380A (en) * | 2018-12-29 | 2019-03-08 | 哈尔滨工业大学 | A kind of length adjustable supporting leg buffer for rocket landing mechanism |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69508444D1 (en) * | 1995-09-14 | 1999-04-22 | Sikorsky Aircraft Corp | ENERGY ABSORBING CHASSIS / REAR POST WITH ARRANGEMENT FOR INDICATING THE FORCE OF AN IMMEDIATE LOAD |
| US6581919B2 (en) * | 2001-08-20 | 2003-06-24 | Eko Sport, Inc. | Shock absorbing seat post |
| US7332825B2 (en) * | 2006-01-06 | 2008-02-19 | Aerodyne Research, Inc. | System and method for controlling a power generating system |
| DE202008002704U1 (en) * | 2008-02-26 | 2008-05-15 | Skylotec Gmbh | absorber |
| CN101780841B (en) * | 2010-03-10 | 2013-07-03 | 南京航空航天大学 | Landing leg pressing, unfolding and locking device of lander |
| FR2992701B1 (en) * | 2012-07-02 | 2015-04-17 | Airbus Operations Sas | ROD INTEGRATING ENERGY ABSORBER |
| CN103661965B (en) * | 2013-11-22 | 2017-02-08 | 上海宇航系统工程研究所 | Built-in extension-type landing buffering mechanism |
| KR101807424B1 (en) * | 2016-09-08 | 2017-12-12 | 한국항공우주연구원 | Shock absorber having multiple extruding structure |
| CN111017269B (en) * | 2019-11-22 | 2021-07-13 | 北京宇航系统工程研究所 | Large-span foldable reusable rocket landing buffer structure |
-
2020
- 2020-08-10 CN CN202010797646.2A patent/CN112027119B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3525511A (en) * | 1967-02-10 | 1970-08-25 | Automotive Prod Co Ltd | Shock absorbers |
| JP2934494B2 (en) * | 1990-10-24 | 1999-08-16 | 宇宙開発事業団 | Collectible spacecraft |
| JP2004036871A (en) * | 2002-07-02 | 2004-02-05 | Reiko Koganei | Semiactive hydraulic shock absorber |
| CN105659777B (en) * | 2007-02-15 | 2012-02-22 | 北京空间飞行器总体设计部 | One landing seeker soft landing mechanism buffer |
| CN105659758B (en) * | 2009-09-08 | 2013-05-08 | 北京空间飞行器总体设计部 | One detector Landing Buffer mechanism |
| CN202451680U (en) * | 2011-12-23 | 2012-09-26 | 北京空间飞行器总体设计部 | Landing detector deformation buffer |
| KR20130139619A (en) * | 2012-06-13 | 2013-12-23 | 한국항공우주연구원 | Shock absorber for spacecraft lander |
| CN106704433A (en) * | 2017-01-12 | 2017-05-24 | 南京航空航天大学 | Bidirectional buffer with driving function |
| CN107972894A (en) * | 2017-11-01 | 2018-05-01 | 北京宇航系统工程研究所 | A kind of Control System for Reusable Launch Vehicle landing and buffering device |
| CN109178350A (en) * | 2018-09-28 | 2019-01-11 | 南京航空航天大学 | A kind of retractable driving device having tension compression bidirectional pooling feature |
| CN109307032A (en) * | 2018-11-15 | 2019-02-05 | 南京航空航天大学 | A kind of reusable passive energy-absorbing draws/press bidirectional buffer |
| CN109436380A (en) * | 2018-12-29 | 2019-03-08 | 哈尔滨工业大学 | A kind of length adjustable supporting leg buffer for rocket landing mechanism |
Non-Patent Citations (2)
| Title |
|---|
| 可重复使用运载火箭发展研究;王辰;王小军，张宏剑，张希，王江，季宝锋;《飞航导弹》;20180915(第9期);全文 * |
| 腿式着陆缓冲装置吸能特性及软着陆过程动力学仿真研究;李萌;《中国博士学位论文全文数据库工程科技II辑》;20140115(第1期);全文 * |
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