CN114111462A - High light landing buffer gear of used repeatedly carrier rocket - Google Patents
High light landing buffer gear of used repeatedly carrier rocket Download PDFInfo
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- CN114111462A CN114111462A CN202111272022.XA CN202111272022A CN114111462A CN 114111462 A CN114111462 A CN 114111462A CN 202111272022 A CN202111272022 A CN 202111272022A CN 114111462 A CN114111462 A CN 114111462A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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Abstract
The invention relates to a high-light landing buffer mechanism for a reusable carrier rocket, belonging to the field of landing buffer mechanism design; comprises a main leg, a supporting pneumatic cover and a rubber disc; wherein, the main leg is in a rod-shaped structure; the supporting pneumatic cover is of a trapezoidal structure; the upper ends of the main legs and the supporting pneumatic cover are rotationally connected with the rocket body of the external carrier rocket; the lower ends of the main legs and the supporting pneumatic cover are rotatably connected with the rubber disc through a rotating shaft; the main leg is of a multi-sub-leg nested structure, and the landing buffer mechanism is unfolded and folded through the extension and contraction of the sub-legs of the main leg; the invention greatly reduces the whole weight and the working load of the landing buffer mechanism, and is beneficial to improving the whole launching efficiency of the carrier rocket and improving the environment of returning to the landing load.
Description
Technical Field
The invention belongs to the field of design of landing buffer mechanisms, and relates to a high-light landing buffer mechanism for a reusable carrier rocket.
Background
The carrier rocket is a main tool for spaceflight and carrying into space. The high launching cost corresponding to the prior disposable carrier rocket limits the progress and the degree of space development and utilization of human beings. The reuse of the carrier rocket is an important technical approach for reducing the cost of entering space transportation, and a landing buffer mechanism design technology for reusing the carrier rocket becomes a key technology for returning the carrier rocket to the earth to realize reuse. The prior art adopts the traditional composite material to develop the integral design of the landing mechanism with respect to the design of the metal material landing mechanism. The mechanism design scheme can not meet the multiple functions of folding, unfolding, locking, buffering and the like.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the high-light landing buffer mechanism of the reusable carrier rocket is provided, the whole weight and the working load of the landing buffer mechanism are greatly reduced, and the improvement on the whole launching efficiency of the carrier rocket and the improvement on the environment of returning to the landing load are facilitated.
The technical scheme of the invention is as follows:
a high light landing buffer mechanism of a reusable carrier rocket comprises a main leg, a supporting pneumatic cover and a rubber disc; wherein, the main leg is in a rod-shaped structure; the supporting pneumatic cover is of a trapezoidal structure; the upper ends of the main legs and the supporting pneumatic cover are rotationally connected with the rocket body of the external carrier rocket; the lower ends of the main legs and the supporting pneumatic cover are rotatably connected with the rubber disc through a rotating shaft; the main leg is of a multi-sub-leg nested structure, and the landing buffer mechanism is unfolded and folded through the stretching of the sub-legs of the main leg.
In the above reusable launch vehicle high-light landing buffer mechanism, the main leg comprises an upper joint, a first sub-leg, a second sub-leg, a third sub-leg, a fourth sub-leg, a buffer sub-leg and a lower joint; wherein the upper joint, the first sub-leg, the second sub-leg, the third sub-leg, the fourth sub-leg, the buffer sub-leg and the lower joint are sequentially butted from top to bottom along the axial direction;
the lower joint is used for connecting the main leg with the rubber disc, and the upper joint is used for connecting the outer carrier rocket body; joint bearings are arranged at the upper joint and the lower joint; the buffer sub-leg is made of an integral metal pipe and internally provided with a buffer aluminum honeycomb; the first sub-leg, the second sub-leg, the third sub-leg and the fourth sub-leg are all in a carbon fiber composite material structure form; the leg tube wall thickness of the first sub-leg, the second sub-leg, the third sub-leg and the fourth sub-leg is 5-6mm, and the unidirectional weftless fabric is adopted for laying; the inner pipe wall adopts a forming rigid mould boundary to realize dimensional precision control, the outer pipe wall adopts prepressing flexible boundary control and reserves a machine allowance to realize that the whole dimension meets the design requirement; besides the size design, the overall structure strength and rigidity are directly influenced by the sub-leg structure laying layer design, the interlayer butt joint design and the metal piece connection design.
In the reusable high-light landing buffer mechanism for the carrier rocket, the pipe walls of the first sub-leg, the second sub-leg, the third sub-leg, the fourth sub-leg and the buffer sub-leg adopt a design form of combining fibers in the direction of 0 degree, fibers in the direction of 90 degrees and fibers in the direction of +/-45 degrees; wherein the fiber accounts for 50-60% in the 0 degree direction, 20-30% in the 90 degree direction and 20-30% in the +/-45 degree direction.
In the reusable high-light landing buffer mechanism for the carrier rocket, the upper joint and the sub-leg are in a connection design form between a metal piece and a composite material piece; the upper joint consists of a connecting piece and a ring connecting piece; the upper joint is used for connecting the main leg with the carrier rocket, and the connecting piece adopts a double-region step-variable topological structure design form to realize the effect that the upper concentrated force is effectively diffused to be uniformly transmitted with a sub-leg through the self structure; the annular connecting piece is radially connected with the sub-leg and axially connected with the connecting piece, so that axial load transmission between the annular connecting piece and the connecting piece is realized, axial distribution of load on the sub-leg is further realized, and the condition of bearing concentrated force at the boundary of the sub-leg is further improved.
In the above reusable high-light landing buffer mechanism for a carrier rocket, the two sub-legs comprise two sub-leg composite pipe parts, an annular air bag and a locking limiting part; the three-leg composite material pipe part and the annular limiting elastic sheet are arranged on the three-leg composite material pipe part; the two-sub-leg composite material pipe part and the three-sub-leg composite material pipe part are consistent with the layer design scheme of the one-sub-leg composite material pipe part; the annular air bag consists of an air bag and an air inlet nozzle; the air bag is made of aramid plain fabric through curing; the annular air bag has the advantages of high integral structure strength, high elongation, good air tightness, strong environmental adaptability, long service life and excellent wear resistance; the locking limiting part is formed by adding a high-strength steel integrally, is fixed to the inner wall of the two-sub-leg composite pipe part as an insert and is wound with the end part of the relevant carbon fiber in the pipe part, so that the strength connection between the locking limiting part and the two-sub-leg composite pipe part is realized, and the relevant load is effectively transmitted to the carbon fiber; the annular limiting elastic sheet is formed by adding a high-strength steel whole machine, is embedded in the outer wall of the pipe part of the composite material with three sub-legs and is wound with relevant carbon fibers inside the pipe part, so that the strength connection between the annular limiting elastic sheet and the pipe part of the composite material with three sub-legs is realized, and relevant loads are effectively transmitted to the carbon fibers.
In the reusable high-light landing buffer mechanism for the carrier rocket, a combined design scheme of spring pieces and air bags is adopted among the sub-legs in the main leg; after the three-subsidiary leg is unfolded in place in the two-subsidiary leg in a sliding manner, the lower end of an annular limiting elastic sheet which is externally embedded and outside the composite pipe part of the three-subsidiary leg is limited by a locking limiting piece, and the three-subsidiary leg is unfolded in place; meanwhile, the elastic sheet at the upper end of the annular limiting elastic sheet slides through the upper end of the locking limiting piece and enters the lower part of the upper end of the locking limiting piece to realize locking; after the locking in place, two-way constraint is axially formed between the three sub-legs and the two sub-legs, and the effective transmission of axial load between the sub-legs is realized; meanwhile, the bending moment load transmission between the sub-legs is realized through the design of the axial repeated lap joint part between the three sub-legs and the two sub-legs.
In the reusable high-light landing buffer mechanism of the carrier rocket, in order to realize the reusability of the landing buffer mechanism, the main leg has an unlocking function; the air bag is placed in front of the annular limiting elastic sheet and the locking limiting piece, and high-pressure air does not exist in the air bag during locking, so that the air bag does not participate in interaction among the sub-legs in the unfolding process of the main leg; during unlocking, high-pressure gas is filled into the air bag, the unlocking effect on the annular limiting elastic sheet is realized under the action of the high-pressure gas, and the elastic sheet is radially pressed in to realize unlocking; after the three-sub-leg is pushed into the two-sub-leg for a distance after unlocking, the annular limiting elastic sheet is separated from the locking area, and the air bag is exhausted, so that the three-sub-leg can be further retracted into the two-sub-leg.
In the above reusable high-light landing buffer mechanism for a launch vehicle, the supporting pneumatic cover comprises an upper joint, a lower joint, a skin, a supporting tube, a reinforcing beam and a cover; the upper joint and the lower joint are integrally formed by high-strength steel, key bearings are placed in the upper joint and the lower joint, and the upper joint and the lower joint are respectively connected with the rocket body of the carrier rocket and the rubber disc through connecting pins; the skin, the supporting tube, the reinforcing beam and the cover are all made of carbon fiber composite structural materials; the supporting pneumatic cover adopts a secondary curing technology to integrally form the skin, the supporting tube and the reinforcing beam.
In the reusable high-light landing buffer mechanism for the carrier rocket, the skin is laid at an angle of +/-45 degrees by adopting the inner carbon fiber and the outer carbon fiber, and the aluminum honeycomb is embedded in the skin, so that the integral specific stiffness of the skin is greatly improved.
In the reusable high-light landing buffer mechanism for the carrier rocket, the overall structural design form of the supporting tube is consistent with that of the composite material sub-leg in the main leg, and the supporting tube is connected with the upper joint and the lower joint in a radial and axial two-way manner; the supporting tube effectively transmits the loads at the upper joint and the lower joint on one hand, and effectively expands the related loads into the supporting pneumatic cover on the other hand, so that the overall bearing efficiency of the supporting pneumatic cover is improved; a plurality of stiffening beams are placed inside the support pneumatic cover and used for enhancing the whole bearing efficiency of the support pneumatic cover, the bearing environment of the support pipe is optimized, and the damage of the large bending moment environment to the carbon fiber inside the support pipe is avoided.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the landing buffer mechanism, a large amount of carbon fiber composite materials are adopted as the integral main structural materials, and meanwhile, a large amount of corresponding structural and mechanism designs are adopted for the characteristics of the carbon fiber composite materials, so that the mass of the integral structure is reduced by more than 60% compared with that of the traditional metal materials;
(2) the landing mechanism of the invention adopts a design form of carbon fiber composite material and metal inner and outer inserts in large quantity, thus effectively improving the bearing efficiency and the mechanism functional reliability of the whole mechanism;
(3) the landing buffer mechanism has the functions of folding, stable unfolding, strong buffering and light bearing;
(4) the integral high-light design scheme of the landing buffer mechanism not only reduces the self weight, but also greatly improves the self landing load environment of the landing mechanism, and reduces the load environment of each working condition of unfolding locking and landing buffering caused by the self weight.
Drawings
FIG. 1 is a schematic view of a high light weight landing gear in an extended state;
FIG. 2 is a schematic view of a high light landing buffer mechanism in a folded state;
FIG. 3 is a schematic view of a main leg component;
FIG. 4 is a schematic view of the connection area of the upper joint of the main leg with a sub-leg;
FIG. 5 is a schematic view of the connection locking region of the second sub-leg and the third sub-leg of the main leg;
FIG. 6 is a partially enlarged view of the connection locking region between the second sub-leg and the third sub-leg of the main leg;
FIG. 7 is a schematic view of the components of the support pneumatic housing.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a high-light-weight composite landing buffer mechanism for a reusable carrier rocket, which is mainly used for vertical return landing buffer of the carrier rocket. The mechanism can not only provide large-range landing support area required by the landing stability of the carrier rocket, but also greatly improve the overall stability of the rocket body returning to the landing; the folding deformation function is also provided to provide a good aerodynamic shape for vertical launching of the carrier rocket; the overall structure adopts a great deal of composite materials and a mechanism design form facing the composite materials, so that the overall weight and the working load of the landing buffer mechanism are greatly reduced, and the carrier rocket overall launching efficiency is improved and the environment of returning to the landing load is improved.
As shown in fig. 1 and 2, the landing buffer mechanism main body structure includes: the main leg 1, the support pneumatic cover 2 and the rubber disc 3. The working principle of the landing buffer mechanism is as follows: the mechanism consists of three components, namely a main leg 1, a supporting pneumatic cover 2 and a rubber disc 3. The main leg 1 and the upper joint of the supporting pneumatic cover 2 are connected with the carrier rocket body, and the lower joints are connected with the rubber disc through connecting rotating shafts. Joint bearings are embedded in all joints, and through the rotation function of the joint bearings and the rotation function of the bearings and the connecting rotating shaft, the connecting parts form an equivalent spherical hinge mode, so that the load environments of the main leg 1 and the supporting pneumatic cover 2 are effectively improved in the landing and unfolding processes. Fig. 1 shows the landing mechanism carrier rocket in the unfolded landing state in the descending stage, and fig. 2 shows the landing mechanism carrier rocket in the folded flying state in the ascending stage. The unfolding and folding state change of the landing mechanism is realized by the telescopic function of the multiple sub-legs of the main leg 1.
When the landing buffer mechanism is actually assembled and used, the supporting pneumatic cover 2 is firstly connected with the corresponding connecting part of the rocket body of the carrier rocket. And determining the relative position between the rubber disc 3 and the supporting pneumatic cover 2 according to the design position. Assembling the main leg 1 according to an unfolding and locking state, wherein the upper joint and the lower joint of the main leg 1 are respectively connected with the rocket body of the carrier rocket and the rubber disc. After the main leg 1, the supporting pneumatic cover 2 and the rubber disc 3 are connected, the main leg 1 is unlocked, and the folding and folding functions of the landing buffer mechanism are realized.
As shown in FIG. 3, the main leg 1 is composed of an upper joint 1-1, a first sub-leg 1-2, a second sub-leg 1-3, a third sub-leg 1-4, a fourth sub-leg 1-5, a buffer sub-leg 1-6 and a lower joint 1-7. The lower joint 1-7 is used for connecting the main leg 1 with the rubber disc 3, and the upper joint 1-1 is used for connecting with a rocket body of a carrier rocket. Joint bearings are arranged at the upper joint and the lower joint. Except that the buffering sub-legs are made of integral metal pipes and internally provided with buffering aluminum honeycombs, the other sub-legs are made of carbon fiber composite materials. The thickness of the composite material sub-leg pipe wall is 5-6mm, and the composite material sub-leg pipe wall is laid by adopting unidirectional non-woven cloth. The inner pipe wall adopts the boundary of a forming rigid mould to realize dimensional precision control, the outer pipe wall adopts prepressing flexible boundary control and reserves a machine allowance to realize that the whole dimension meets the design requirement. Besides the size design, the overall structure strength and rigidity are directly influenced by the sub-leg structure laying layer design, the interlayer butt joint design and the metal piece connection design. The pipe wall of the thigh adopts a design form of combining axial fibers with a direction of 0 degree, circumferential fibers with a direction of 90 degrees and oblique fibers with a degree of +/-45 degrees. Wherein the axial fiber accounts for about 50-60%, the circumferential fiber accounts for 20-30%, and the oblique fiber accounts for 20-30%. The pipe supporting part mainly adopts axial fibers and circumferential fibers, the inner wall and the outer wall of the pipe are paved in a staggered mode at the angle of +/-45 degrees of oblique fibers, the curing of the inner surface and the outer surface of the sub-leg is achieved in a skin-like mode, and the paving of an internal fiber layer can be effectively protected.
As shown in fig. 4, the upper joint 1-1 and the sub-leg 1-2 are designed to be connected by a metal piece and a composite material piece. The upper joint 1-1 consists of a connecting piece 1-1-1 and a ring connecting piece 1-1-2. The upper joint 1-1 is used for connecting the main leg with the carrier rocket, and the connecting piece 1-1-1 adopts a double-region step-variable topological structure design form, so that the effect that the upper concentrated force is effectively diffused to be uniformly transmitted with a sub-leg through the structure of the connecting piece. The annular connecting piece 1-1-2 adopts a design form of being radially connected with one sub-leg and axially connected with the connecting piece 1-1-1, so that not only is the axial load transmission between the annular connecting piece and the connecting piece 1-1-1 realized, but also the axial distribution of the load in one sub-leg 1-2 is further realized, and the condition of bearing the concentrated force at the boundary of one sub-leg 1-2 is further improved.
As shown in fig. 5 and 6, the structure of the connection and locking between the sub-legs of the composite material is schematically shown. In order to ensure the scalability of the main leg of the landing buffer mechanism and realize the overall expansion and folding functions of the landing buffer mechanism, the overall scalability degree of the main leg is about high, and the overall folding and unfolding performance of the landing buffer mechanism is correspondingly improved. Taking the connection locking mechanism between the two-sub-legs 1-3 and the three-sub-legs 1-4 as an example, the corresponding connection locking part mainly comprises five parts, namely a two-sub-leg composite pipe part 1-3-1, an annular air bag 1-3-2, a locking limiting part 1-3-3, a three-sub-leg composite pipe part 1-4-1 and an annular limiting elastic sheet 1-4-2. The two-sub-leg composite material pipe part 1-3-1 and the three-sub-leg composite material pipe part 1-4-1 are consistent with the design scheme of the layer of the one-sub-leg composite material pipe part. The annular air bag 1-3-2 consists of an air bag and an air inlet nozzle. The air bag is made of aramid plain woven fabric through curing. The annular air bag 1-3-2 has the advantages of high integral structure strength, high elongation, good air tightness, strong environmental adaptability, long service life, excellent wear resistance and the like. The locking limiting part 1-3-3 is formed by adding a high-strength steel whole machine, is used as an insert and fixed on the inner wall of the two-sub-leg composite pipe part 1-3-1 and is wound with the end part of the relevant carbon fiber inside the pipe part, so that the strength connection between the locking limiting part 1-3-3 and the two-sub-leg composite pipe part 1-3-1 is realized, and the relevant load is effectively transferred to the carbon fiber. The annular limiting elastic sheet 1-4-2 is formed by adding a high-strength steel integral machine, is externally embedded on the outer wall of the three-leg composite pipe part 1-4-1 and is wound with relevant carbon fibers inside the pipe part, so that the strength connection between the annular limiting elastic sheet 1-4-2 and the three-leg composite pipe part 1-4-1 is realized, and relevant loads are effectively transferred to the carbon fibers.
As shown in fig. 6, a combined design scheme of a spring piece and an air bag is adopted between the sub-legs in the main leg 1. After the three-legged section 1-4 slides and unfolds in place in the two-legged section 1-3, the lower end of an annular limiting elastic sheet 1-4-2 embedded outside the three-legged composite pipe section 1-4-1 is limited by a locking limiting piece 1-3-3, and the three-legged section unfolds in place. Meanwhile, the elastic sheet at the upper end of the annular limiting elastic sheet 1-4-2 slides over the upper end of the locking limiting piece 1-3-3 and enters the lower part of the upper end of the locking limiting piece 1-3-3 to realize locking. After the locking in place, two-way constraint is formed between the three sub-legs 1-4 and the two sub-legs 1-3 in the axial direction, and the effective transmission of axial loads between the sub-legs is realized. Meanwhile, the bending moment load transmission between the sub-legs is also realized through the design of the axial repeated lap joint part between the three sub-legs 1-4 and the two sub-legs 1-3. In order to realize the repeated use of the landing buffer mechanism, the main leg 1 needs to have an unlocking function. The air bag 1-3-2 is placed in front of the annular limiting elastic sheet 1-4-2 and the locking limiting piece 1-3-3, and high-pressure gas does not exist in the air bag 1-3-2 during locking and does not participate in interaction between the sub-legs in the unfolding process of the main leg 1. During unlocking, high-pressure gas is filled into the air bag 1-3-2, the annular limiting elastic sheet 1-4-2 is unlocked under the action of the high-pressure gas, and the elastic sheet is radially pressed in to realize unlocking. After the unlocking, the three-sub-legs 1-4 are pushed into the two-sub-legs 1-3 for a distance, namely the annular limiting elastic sheet 1-4-2 is separated from the locking area, and the air bag 1-3-2 is exhausted, so that the three-sub-legs 1-4 can be further retracted into the two-sub-legs 1-3.
As shown in FIG. 7, the supporting pneumatic cover 2 is composed of an upper joint 2-1, a lower joint 2-2, a skin 2-3, a supporting pipe 2-4, a reinforcing beam 2-5, a flap 2-6 and the like. The upper joint 2-1 and the lower joint 2-2 are integrally formed by high-strength steel, key bearings are placed in the upper joint and are respectively connected with the rocket body of the carrier rocket and the rubber disc 3 through connecting pins. The skin 2-3, the supporting tube 2-4, the reinforcing beam 2-5 and the cover 2-6 are all made of carbon fiber composite structural materials. The supporting pneumatic cover 2 integrally forms the skins 2-3, the supporting tubes 2-4 and the reinforcing beams 2-5 by adopting a secondary curing technology. The skin 2-3 adopts a structural design form that internal and external carbon fibers are paved at +/-45 degrees and an aluminum honeycomb is embedded, so that the integral specific stiffness of the skin is greatly improved. The integral structural design form of the support tubes 2-4 is consistent with that of the composite material sub-legs in the main leg 1, and the support tubes are connected with the upper joint and the lower joint in a radial and axial two-way mode. The supporting pipes 2-4 can effectively transmit the loads at the upper joint and the lower joint on one hand, and can also effectively expand the related loads into the supporting pneumatic cover 2 on the other hand, so that the overall bearing efficiency of the supporting pneumatic cover 2 is improved. A plurality of stiffening beams 2-5 are arranged inside the supporting pneumatic cover 2 and used for enhancing the overall bearing efficiency of the supporting pneumatic cover 2, and meanwhile, the bearing environment of the supporting tubes 2-4 is optimized, so that the damage of the large bending moment environment to the carbon fibers inside the supporting tubes is avoided.
The key point of the invention is a multifunctional integrated high-light landing buffer mechanism with functions of folding, unfolding, locking and landing buffering. The main leg and the main leg support the pneumatic cover are made of carbon fiber composite material, and the internal layer of the composite material structure, the connection form of the metal piece for stress diffusion and the composite material and the scheme of a repeatable limiting locking mechanism facing the composite material telescopic pipe mechanism are designed. The main leg adopts the form of inner and outer embedded metal pieces to realize locking connection and load transfer, and the upper end and the lower end of the main leg are provided with corresponding metal joints to realize connection with the rocket body of the carrier rocket and the rubber disc. The air bags are placed in the sub-legs of the main leg to unlock the locking and limiting mechanism, so that the whole mechanism can be repeatedly used. And buffer materials such as aluminum honeycombs and the like in the buffer leg parts realize buffer energy absorption. The supporting pneumatic cover adopts a design scheme of secondary forming of a carbon fiber composite material structure, and the integral rigidity of the landing mechanism is synchronously improved while the load transfer, the diffusion and the buffering energy absorption of the integral mechanism are realized. Therefore, the main leg extension, locking limit, air pressure unlocking, stress diffusion, integrated forming design of the supporting pneumatic cover and optimized layout design of the internal structure are basic units of the landing buffer mechanism.
The landing buffer mechanism of the invention adopts a great deal of carbon fiber composite materials as the main structural materials, and adopts a great deal of corresponding structure and mechanism design aiming at the characteristics of the carbon fiber composite materials, and the mass of the whole structure is reduced by more than 60% compared with the mass of the traditional metal material; the landing mechanism adopts a design form of carbon fiber composite material and metal internal and external inserts in a large quantity, so that the bearing efficiency and the mechanism functional reliability of the whole mechanism are effectively improved; the landing buffer mechanism has multiple functions of folding, stable unfolding, strong buffering and light bearing; the integral high-light design scheme of the landing buffer mechanism not only reduces the self weight, but also greatly improves the self landing load environment of the landing mechanism, and reduces the load environment of each working condition of unfolding locking and landing buffering caused by the self weight.
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 (10)
1. The utility model provides a high light landing buffer gear of used carrier rocket which characterized in that: comprises a main leg (1), a supporting pneumatic cover (2) and a rubber disc (3); wherein, the main leg (1) is of a rod-shaped structure; the supporting pneumatic cover (2) is of a trapezoidal structure; the upper ends of the main legs (1) and the supporting pneumatic cover (2) are rotationally connected with an external carrier rocket body; the lower ends of the main legs (1) and the supporting pneumatic cover (2) are rotatably connected with the rubber disc (3) through a rotating shaft; the main leg (1) is of a multi-sub-leg nested structure, and the landing buffer mechanism is unfolded and folded through the stretching of the sub-legs of the main leg (1).
2. A reusable launch vehicle high light weight landing buffer mechanism according to claim 1, wherein: the main leg (1) comprises an upper joint (1-1), a first sub-leg (1-2), a second sub-leg (1-3), a third sub-leg (1-4), a fourth sub-leg (1-5), a buffer sub-leg (1-6) and a lower joint (1-7); wherein the upper joint (1-1), the first sub-leg (1-2), the second sub-leg (1-3), the third sub-leg (1-4), the fourth sub-leg (1-5), the buffer sub-leg (1-6) and the lower joint (1-7) are sequentially butted from top to bottom along the axial direction;
the lower joint (1-7) is used for connecting the main leg (1) with the rubber disc (3), and the upper joint (1-1) is used for connecting with an external carrier rocket body; joint bearings are arranged at the upper joint (1-1) and the lower joint (1-7); the buffer sub-legs (1-6) are made of integral metal pipes and internally provided with buffer aluminum honeycombs; the first sub-leg (1-2), the second sub-leg (1-3), the third sub-leg (1-4) and the fourth sub-leg (1-5) all adopt a carbon fiber composite material structure form; the tube wall thickness of the legs of the first sub-leg (1-2), the second sub-leg (1-3), the third sub-leg (1-4) and the fourth sub-leg (1-5) is 5-6mm, and the unidirectional weftless fabric is adopted for laying; the inner pipe wall adopts a forming rigid mould boundary to realize dimensional precision control, the outer pipe wall adopts prepressing flexible boundary control and reserves a machine allowance to realize that the whole dimension meets the design requirement; besides the size design, the overall structure strength and rigidity are directly influenced by the sub-leg structure laying layer design, the interlayer butt joint design and the metal piece connection design.
3. A reusable launch vehicle high light weight landing buffer mechanism according to claim 2, wherein: the tube walls of the first sub-leg (1-2), the second sub-leg (1-3), the third sub-leg (1-4), the fourth sub-leg (1-5) and the buffer sub-leg (1-6) adopt a combined design form of fibers in the 0-degree direction, fibers in the 90-degree direction and fibers in the +/-45-degree direction; wherein the fiber accounts for 50-60% in the 0 degree direction, 20-30% in the 90 degree direction and 20-30% in the +/-45 degree direction.
4. A reusable launch vehicle high light weight landing buffer mechanism according to claim 3, wherein: the upper joint (1-1) and the sub-leg (1-2) are connected by a metal piece and a composite material piece; the upper joint (1-1) consists of a connecting piece (1-1-1) and a ring connecting piece (1-1-2); the upper joint (1-1) is used for connecting the main leg with the carrier rocket, and the connecting piece (1-1-1) adopts a double-region step-variable topological structure design form, so that the effect that the upper concentrated force is effectively diffused to be uniformly transmitted with a sub-leg through the self structure is realized; the annular connecting piece (1-1-2) is radially connected with the sub-leg (1-2) and axially connected with the connecting piece (1-1-1), so that not only is axial load transmission between the annular connecting piece and the connecting piece (1-1-1) realized, but also the load is further distributed in the axial direction of the sub-leg (1-2), and the load bearing condition of the boundary concentrated force of the sub-leg (1-2) is further improved.
5. A reusable launch vehicle high light weight landing buffer mechanism according to claim 4, wherein: the two sub-legs (1-3) comprise two sub-leg composite material pipe parts (1-3-1), annular air bags (1-3-2) and locking limiting parts (1-3-3); the three-leg (1-4) comprises a three-leg composite pipe part (1-4-1) and an annular limiting elastic sheet (1-4-2); wherein, the two-sub-leg composite material pipe part (1-3-1) and the three-sub-leg composite material pipe part (1-4-1) are consistent with the layer design scheme of the one-sub-leg composite material pipe part; the annular air bag (1-3-2) consists of an air bag and an air inlet nozzle; the air bag is made of aramid plain fabric through curing; the annular air bag (1-3-2) has the advantages of high integral structure strength, high elongation, good air tightness, strong environmental adaptability, long service life and excellent wear resistance; the locking limiting part (1-3-3) is formed by adding a high-strength steel whole machine, is used as an insert and fixed on the inner wall of the two-sub-leg composite material pipe part (1-3-1) and is wound with the end part of the related carbon fiber in the pipe part, so that the strength connection between the locking limiting part (1-3-3) and the two-sub-leg composite material pipe part (1-3-1) is realized, and related loads are effectively transmitted to the carbon fiber; the annular limiting elastic sheet (1-4-2) is formed by adding a high-strength steel whole machine, is externally embedded on the outer wall of the three-leg composite pipe part (1-4-1), and is wound with relevant carbon fibers inside the pipe part, so that the strength connection between the annular limiting elastic sheet (1-4-2) and the three-leg composite pipe part (1-4-1) is realized, and relevant loads are effectively transferred to the carbon fibers.
6. A reusable launch vehicle high light weight landing buffer mechanism according to claim 5, wherein: a combined design scheme of spring pieces and air bags is adopted among the sub-legs in the main leg (1); after the three-legged composite pipe part (1-4-1) slides and unfolds in place in the two-legged composite pipe part (1-3), the lower end of an annular limiting elastic sheet (1-4-2) externally embedded with the three-legged composite pipe part (1-4-1) is limited by a locking limiting piece (1-3-3) and unfolds in place; meanwhile, the elastic sheet at the upper end of the annular limiting elastic sheet (1-4-2) slides over the upper end of the locking limiting piece (1-3-3) and enters the lower part of the upper end of the locking limiting piece (1-3-3) to realize locking; after the locking in place, the three sub-legs (1-4) and the two sub-legs (1-3) axially form bidirectional constraint to realize the effective transmission of axial load between the sub-legs; meanwhile, the bending moment load transmission between the sub-legs is realized through the design of the axial repeated lap joint part between the three sub-legs (1-4) and the two sub-legs (1-3).
7. A reusable launch vehicle high light weight landing buffer mechanism according to claim 6, wherein: in order to realize the repeated use of the landing buffer mechanism, the main leg (1) has an unlocking function; the air bag (1-3-2) is placed in front of the annular limiting elastic sheet (1-4-2) and the locking limiting piece (1-3-3), high-pressure gas does not exist in the air bag (1-3-2) during locking, and the air bag does not participate in interaction between the sub-legs in the unfolding process of the main leg (1); during unlocking, high-pressure gas is filled into the air bag (1-3-2), the annular limiting elastic sheet (1-4-2) is unlocked under the action of the high-pressure gas, and the elastic sheet is radially pressed in to realize unlocking; after the unlocking, the three-sub-legs (1-4) are pushed into the two-sub-legs (1-3) for a certain distance, the annular limiting elastic sheet (1-4-2) is separated from the locking area, and the air bag (1-3-2) is exhausted, so that the three-sub-legs (1-4) can be further retracted into the two-sub-legs (1-3).
8. A reusable launch vehicle high light weight landing buffer mechanism according to claim 7, wherein: the supporting pneumatic cover (2) comprises an upper joint (2-1), a lower joint (2-2), a skin (2-3), a supporting pipe (2-4), a reinforcing beam (2-5) and a cover (2-6); the upper joint (2-1) and the lower joint (2-2) are integrally formed by high-strength steel, key bearings are placed in the upper joint and the lower joint, and the upper joint and the lower joint are respectively connected with a rocket body of the carrier rocket and a rubber disc (3) through connecting pins; the skin (2-3), the supporting tubes (2-4), the reinforcing beam (2-5) and the cover (2-6) are all made of carbon fiber composite structural materials; the supporting pneumatic cover (2) integrally forms the skin (2-3), the supporting tube (2-4) and the reinforcing beam (2-5) by adopting a secondary curing technology.
9. A reusable launch vehicle high light weight landing buffer mechanism according to claim 8, wherein: the skin (2-3) is laid at an angle of +/-45 degrees by adopting inner and outer carbon fibers, and is embedded with an aluminum honeycomb, so that the integral specific stiffness of the skin is greatly improved.
10. A reusable launch vehicle high light weight landing buffer mechanism according to claim 9, wherein: the overall structural design form of the supporting tubes (2-4) is consistent with that of the composite material sub-legs in the main leg (1), and the supporting tubes are connected with the upper joint and the lower joint in a radial and axial two-way mode; the supporting pipes (2-4) effectively transmit the loads at the upper joint and the lower joint on one hand, and effectively expand the related loads into the supporting pneumatic cover (2) on the other hand, so that the overall bearing efficiency of the supporting pneumatic cover (2) is improved; a plurality of stiffening beams (2-5) are arranged inside the supporting pneumatic cover (2) and used for enhancing the integral bearing efficiency of the supporting pneumatic cover (2), and meanwhile, the bearing environment of the supporting tubes (2-4) is optimized, so that the damage of the large bending moment environment to the carbon fiber inside the supporting tubes is avoided.
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