A sub-stage recovery and landing mechanism for a launch vehicle

Abstract

The present invention discloses a sub-stage recovery and landing mechanism of a carrier rocket, comprising: a conformal support structure, which is provided with a plurality of structures around the circumference of the rocket body, one end of which is rotatably connected to the rocket body, and has a folded state when locked by an initial locking structure and folded to the outer surface of the rocket body, and a landing support state when the initial locking structure is unlocked and extended outward; a telescopic rod structure, one end of which is hinged to the rocket body and the other end is hinged to the conformal support structure, and comprises at least two hollow support rods that are movably sleeved in sequence; an inter-stage locking component, which is used to lock two adjacent hollow support rods after being extended to the extreme position, so that the telescopic rod structure, the conformal support structure in the landing support state and the rocket body form a triangular structure. In this recovery and landing mechanism, the telescopic rod structure can provide strong and reliable support for the conformal support structure, so that the sub-stage of the carrier rocket can land smoothly, and provide guarantee for the recovery and reuse of the rocket sub-stage and the reduction of the launch cost.

Description

Technical Field

[0001] The invention relates to the technical field of carrier rocket recovery, and in particular to a sub-stage recovery and landing mechanism of a carrier rocket. Background Art

[0002] Satellites, spacecrafts, planetary probes and other spacecraft mainly rely on rockets to enter space. As the launch technology of spacecraft becomes more and more mature, the demand for high-reliability and low-cost launch vehicles is becoming stronger. As we all know, the launch vehicles currently used are almost all disposable vehicles, and it costs about 10,000 to 20,000 US dollars to transport 1 kg of objects into space, which makes the cost of space launch high.

[0003] The reason why the cost of a single flight in the aviation field can be greatly reduced is precisely because of its reusability. The recovery and reuse of launch vehicles is also an effective way to reduce launch costs. The landing process of the rocket sub-stage is a crucial step in achieving rocket recovery.

[0004] The existing recovery and landing mechanism has large air resistance when the rocket is launched. During the vertical landing of the rocket, due to the large peak impact force and the influence of first-order vibration, the rocket body may become unstable, resulting in failure of the recovery work. Summary of the invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problem in the prior art that rocket sub-stages are prone to instability due to excessive impact force during vertical landing and recovery, thereby providing a sub-stage recovery and landing mechanism for a carrier rocket.

[0006] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0007] A sub-stage recovery and landing mechanism of a launch vehicle, comprising:

[0008] Arrow body;

[0009] A plurality of shape-preserving support structures are provided around the circumference of the arrow body, one end of which is rotatably connected to the arrow body around a first axis; the shape-preserving support structure has a retracted state in which it is retracted to the outer surface of the arrow body when locked by an initial locking structure, and a landing support state in which it is extended outward after the initial locking structure is unlocked;

[0010] A telescopic rod structure, one end of which is hinged to the arrow body and the other end of which is hinged to the shape-preserving support structure, comprising at least two hollow support rods that are movably sleeved in sequence;

[0011] The inter-stage locking component is arranged at the connection node of two adjacent hollow support rods, and is used to lock the two adjacent hollow support rods after being extended to the extreme position, so that the telescopic rod structure, the conformal support structure in the landing support state and the rocket body form a triangular structure.

[0012] Furthermore, the inter-stage locking component comprises:

[0013] A locking groove is provided on the outer wall of the hollow support rod with a smaller diameter;

[0014] The locking block structure is connected to the hollow support rod with a larger diameter. When two adjacent hollow support rods are extended to the limit position, the locking block structure extends into the locking groove to lock the two adjacent hollow support rods.

[0015] Furthermore, the end of the hollow support rod with a larger diameter is connected to a first connecting ring, and the inner wall surface of the first connecting ring is provided with a mounting groove with an opening radially inward; the locking block structure comprises:

[0016] A locking block is slidably connected to the installation slot along the radial direction of the telescopic rod structure, and has an extended state in which at least part of the locking block is extended out of the installation slot to cooperate with the locking slot to lock two adjacent hollow support rods, and a retracted state in which the locking block is retracted into the installation slot;

[0017] An elastic member is elastically connected between the bottom of the installation slot and the locking block, and its elastic force drives the locking block to extend out of the opening of the installation slot.

[0018] Furthermore, there are a plurality of the installation grooves, which are evenly spaced along the circumferential direction of the first connecting ring; and a locking block is correspondingly arranged in each of the installation grooves.

[0019] Furthermore, the connection surface between the first connecting ring and the hollow support rod with a larger diameter is a wedge surface.

[0020] Furthermore, a first protrusion structure is provided on the outer wall of the hollow support rod with a smaller diameter and located on the outer side of the locking groove. The first protrusion structure is used to cooperate with the outer side of the locking block structure to prevent the hollow support rod with a smaller diameter from shrinking inwardly.

[0021] Furthermore, the inter-stage locking component further comprises:

[0022] The sealing structure is sleeved on the end of the hollow support rod with a larger diameter and abuts against the hollow support rod with a smaller diameter, so as to close the gap between two adjacent hollow support rods.

[0023] Furthermore, the sealing structure comprises:

[0024] The kit comprises a first sleeve ring sleeved on the end of a hollow support rod with a larger diameter and a second sleeve ring connected to the first sleeve ring, wherein the inner wall of the second sleeve ring is provided with an annular groove opening radially inward;

[0025] The sealing member is embedded in the annular embedding groove, and one end of the sealing member extending out of the annular embedding groove is tightly fitted with the outer wall of the hollow support rod with a smaller diameter.

[0026] Furthermore, the hollow support rod with a smaller diameter includes a rod body and a second connecting ring connected to the rod body, and the locking groove and the first protruding structure are both formed on the outer wall of the second connecting ring.

[0027] Furthermore, the connection surface between the second connection ring and the rod body is a wedge surface, and the inner wall of the second connection ring and the inner wall of the rod body together constitute the inner wall of the hollow support rod.

[0028] Furthermore, a second protrusion structure is provided on the outer wall of the hollow support rod with a smaller diameter located inside the hollow support rod with a larger diameter.

[0029] Furthermore, a thrust piece is connected to the arrow body; the telescopic end of the thrust piece is connected to the conformal support structure, and the thrust piece is used to drive the conformal support structure to rotate from the folded state to the landing support state; the telescopic rod structure realizes relative sliding of each section of the hollow support rod during the rotation of the conformal support structure.

[0030] Furthermore, a groove is provided on an inward side of the shape-keeping support structure; when the shape-keeping support structure is in the retracted state, the telescopic rod structure is embedded in the groove.

[0031] Furthermore, the initial locking structure is also embedded in the groove, and the connection between the initial locking structure and the shape-preserving support structure is a detachable connection.

[0032] Furthermore, the shape of the outward side of the shape-preserving support structure is streamlined.

[0033] Furthermore, in the circumferential direction of the arrow body, the conformal support structure is an aerodynamic shape with low ends and a high middle; in the axial flight direction of the arrow body, the conformal support structure is an aerodynamic shape with a pointed front and a wide rear.

[0034] Furthermore, in the telescopic rod structure, the first section of the support rod is connected to the arrow body, and the last section of the support rod is connected to the shape-preserving support structure; an oil-gas buffer is connected between the end of the last section of the support rod and the shape-preserving support structure.

[0035] Furthermore, the shape-preserving support structure and the telescopic rod structure are both made of carbon fiber material.

[0036] The technical solution of the present invention has the following advantages:

[0037] 1. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a plurality of conformal support structures in a folded state when the sub-stage of the launch vehicle is in the pre-landing stage of the ascending stage and the descending stage, and is attached to the outer surface of the rocket body, so as to rectify and protect the internal mechanism of the rocket body from being disturbed by the heat flow; when the sub-stage of the launch vehicle moves to the landing stage, the initial locking structure releases the lock on the conformal support structure, and the conformal support structure is unfolded outward around the first axis, and moves from the folded state to the landing support state, so that the rocket body can land smoothly; at the same time, the telescopic rod structure is rotated along with the rotation of the conformal support structure. During the process, on the one hand, it rotates around the upper rotating shaft on the rocket body, and on the other hand, the relative sliding of the hollow support rods at each level is realized, which matches the deployment process of the conformal support structure; when the telescopic rod structure moves to the extreme position, the inter-stage locking component locks the two adjacent hollow support rods, so that the telescopic rod structure becomes a rigid rod, and a stable triangular structure is formed between the rocket body, the conformal support structure and the telescopic rod structure. The telescopic rod structure can provide strong and reliable support for the conformal support structure, further improve the stability of the conformal support structure during landing, and then improve the stability of the rocket body during vertical landing and recovery.

[0038] 2. In the sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention, when two adjacent hollow struts are extended to the extreme position, the elastic member of the locking block structure on the hollow strut with a larger diameter drives the locking block to extend into the locking groove on the outer wall of the hollow strut with a smaller diameter, thereby realizing the inter-stage locking of the two adjacent hollow struts; this inter-stage locking component has a simple structure and high reliability, and can automatically realize the inter-stage locking of the telescopic rod structure.

[0039] 3. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a structure in which a locking block structure is installed on a first connecting ring, and then the first connecting ring is connected to the end of a hollow support rod with a larger diameter. Compared with the method of directly machining a mounting groove on the inner wall of the hollow support rod and installing the locking block structure, on the one hand, the machining and manufacturing is more convenient; on the other hand, since the part of the hollow support rod where the locking block structure is installed needs to withstand greater pressure than other parts, the requirements for the structural strength and thickness of this part are higher. The method of separately manufacturing the first connecting ring and the hollow support rod can reduce the weight of the telescopic rod structure as much as possible while meeting the requirements for the structural strength of each part of the telescopic rod structure.

[0040] 4. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a plurality of installation grooves evenly spaced along the circumferential direction of the connecting ring, and a locking block structure is correspondingly arranged in each installation groove, which can not only make the locking between two adjacent hollow support rods more secure, but also make the gap between the two adjacent hollow support rods more consistent, thereby ensuring the sealing of the telescopic rod structure after the inter-stage locking.

[0041] 5. In the sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention, the connecting surface between the first connecting ring and the hollow support rod is in the form of a wedge surface, which can increase the connection area between the two, thereby improving the connection reliability of the first connecting ring.

[0042] 6. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a structure in which the first protrusion structure on the outer wall of a hollow support rod with a smaller diameter cooperates with the locking block structure, which can prevent the hollow support rod with a smaller diameter from shrinking inward, thereby improving the locking effect of the inter-stage locking component.

[0043] 7. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention needs to have a gas generator installed in the telescopic rod structure, and the gas generated by the gas generator pushes the telescopic rod structure to extend to maintain the rigid state of the telescopic rod structure. The setting of the sealing structure between two adjacent hollow support rods can ensure the air tightness of the telescopic rod structure during the extension process, thereby ensuring that the telescopic rod structure can maintain a stable rigid state, providing stable and reliable support for the landing of the rocket body.

[0044] 8. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a seal embedded in the annular groove of the kit and tightly fits with a hollow support rod with a smaller diameter. The installation structure of the seal has high stability and can ensure the airtightness of the telescopic rod structure during the telescopic process.

[0045] 9. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a higher requirement on the structural strength and thickness of the portion where the locking groove and the first protruding structure of the hollow support rod are provided, because the portion needs to withstand greater pressure than other portions. The second connecting ring and the hollow support rod are manufactured separately, so that the weight of the telescopic rod structure itself can be reduced as much as possible while meeting the structural strength requirements of each portion of the telescopic rod structure.

[0046] 10. In the sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention, the connecting surface between the second connecting ring and the hollow support rod is in the form of a wedge surface, which can increase the connection area between the two, thereby improving the connection reliability of the second connecting ring; the inner wall of the second connecting ring and the inner wall of the rod body together constitute the structure of the inner wall of the hollow support rod, which can reduce the overall thickness of the hollow support rod as much as possible while ensuring the structural strength of each part of the hollow support rod, thereby reducing the dead weight of the telescopic rod structure.

[0047] 11. In the sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention, the second protrusion structure on the outer wall of the hollow support rod guides the telescopic movement of the hollow support rod, thereby ensuring that the hollow support rod performs telescopic movement along its axial direction, thereby reducing the influence of the movement deviation of the hollow support rod on the sealing of the telescopic rod structure.

[0048] 12. In the sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention, the conformal support structure is expanded outward around the first axis under the action of the thrust piece, and moves from a retracted state to a landing support state, so that the rocket body can land smoothly; at the same time, the telescopic rod structure rotates around the upper rotating shaft on the rocket body during the rotation of the conformal support structure, and on the other hand, relative sliding of the hollow support rods at various levels is achieved, which matches the expansion process of the conformal support structure, thereby achieving an orderly expansion process of the conformal support structure.

[0049] 13. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a groove on the inner side of the conformal support structure for burying structures such as the telescopic rod structure and the initial locking structure, which can reduce the space occupied by the landing and recovery mechanism.

[0050] 14. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has an initial locking structure that is detachably connected to the conformal support structure, which makes disassembly and replacement more convenient and also facilitates testing the performance of the initial locking structure alone.

[0051] 15. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has a conformal support structure that is an aerodynamic shape with low ends and high in the middle in the circumferential direction of the rocket body; and has an aerodynamic shape that is pointed at the front and wide at the rear in the axial flight direction of the rocket body. This conformal support structure with an aerodynamic shape can reduce the resistance of the recovery and landing mechanism during the ascent process, and can also reduce the resistance of the descending rocket body during the recovery process.

[0052] 16. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention has an oil-gas buffer on the last support rod of the telescopic rod structure. The oil-gas buffer is pushed according to the pneumatic principle, which can effectively reduce the dead weight of the telescopic rod structure, thereby reducing the overall weight of the rocket recovery and landing device.

[0053] 17. The sub-stage recovery and landing mechanism of the launch vehicle provided by the present invention adopts a conformal support structure made of carbon fiber material and various levels of support rods of a telescopic rod structure, which has the advantages of high strength, good heat and impact resistance, and light weight. It can effectively reduce the overall weight of the rocket recovery and landing device and enhance the carrying capacity of the rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0055] Figure 1 This is a schematic diagram of a carrier rocket sub-stage before recovery and landing in an embodiment of the present invention;

[0056] Figure 2 It is a schematic diagram of the recovery and landing of the carrier rocket sub-stage in an embodiment of the present invention;

[0057] Figure 3 It is a structural schematic diagram of a shape-preserving support structure in an embodiment of the present invention;

[0058] Figure 4 It is a structural schematic diagram of the telescopic rod structure in an embodiment of the present invention;

[0059] Figure 5 A longitudinal sectional structural diagram of the telescopic rod structure in an embodiment of the present invention;

[0060] Figure 6 for Figure 5 The enlarged view of point A in the middle;

[0061] Figure 7 for Figure 5 A schematic cross-sectional structure diagram of the telescopic rod structure after the longitudinal section to show the internal structure of the inter-stage locking component;

[0062] Figure 8 for Figure 7 Enlarged view of point B in the middle.

[0063] Explanation of the reference numerals in the accompanying drawings: 1. arrow body; 2. conformal support structure; 21. groove; 3. telescopic rod structure; 31. hollow support rod; 5. interstage locking component; 6. thrust piece; 7. oil-gas buffer; 8. upper rotating shaft; 9. lower rotating shaft; 51. first connecting ring; 511. mounting groove; 52. second connecting ring; 521. locking groove; 522. first protruding structure; 53. locking block; 54. elastic member; 55. kit; 551. first ring; 552. second ring; 553. annular groove; 56. sealing member; 57. second protruding structure. DETAILED DESCRIPTION

[0064] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0065] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0066] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0067] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0068] like Figure 1 and Figure 2 The sub-stage recovery and landing mechanism of a carrier rocket shown in the figure comprises a conformal support structure 2, an initial locking structure, a telescopic rod structure 3 and an inter-stage locking component 5. Among them, four conformal support structures 2 are evenly spaced around the circumference of the rocket body 1, and one end of the conformal support structure 2 is rotatably connected to the rocket body 1 around the lower rotating shaft 9; the conformal support structure 2 has a folded state when locked by the initial locking structure and folded to the outer surface of the rocket body 1, and a landing support state when the initial locking structure is unlocked and extended outward. One end of the telescopic rod structure 3 is rotatably connected to the rocket body 1 around the upper rotating shaft 8, and the other end is hinged to the end of the conformal support structure 2 away from the lower rotating shaft 9. The telescopic rod structure 3 comprises at least two hollow support rods 31 that are movably sleeved in sequence, and the inter-stage locking component 5 is arranged at the connection node of two adjacent hollow support rods 31. The inter-stage locking component 5 is used to lock the two adjacent hollow support rods 31 after being extended to the extreme position, so that the telescopic rod structure 3, the conformal support structure 2 in the landing support state and the rocket body 1 form a triangular structure.

[0069] In this recovery and landing mechanism, when the sub-stage of the carrier rocket is in the ascending stage and the pre-landing stage of the descent stage, the four conformal support structures 2 are in a folded state and attached to the outer surface of the rocket body 1, which are used to rectify and protect the internal structure of the rocket body 1 from heat flow interference; when the sub-stage of the carrier rocket moves to the landing stage, the initial locking structure releases the lock on the conformal support structure 2, and the conformal support structure 2 is unfolded around the lower rotating shaft 9, and moves from the folded state to the landing support state, so that the rocket body 1 can land smoothly; at the same time, the telescopic rod structure 3 rotates with the conformal support structure 2, on the one hand, around the upper surface of the rocket body 1 On the one hand, the upper rotating shaft 8 rotates, and on the other hand, the relative sliding of the hollow support rods 31 at each level is realized, which matches the expansion process of the shape-conserving support structure 2; when the telescopic rod structure 3 moves to the extreme position, the inter-stage locking component 5 locks the two adjacent hollow support rods 31, so that the telescopic rod structure 3 becomes a rigid rod, and a stable triangular structure is formed among the rocket body 1, the shape-conserving support structure 2 and the telescopic rod structure 3. The telescopic rod structure 3 can provide strong and reliable support for the shape-conserving support structure 2, further improve the stability of the shape-conserving support structure 2 during landing, and thereby improve the reliability of the vertical landing recovery process of the rocket body 1.

[0070] like Figure 2 As shown, in this embodiment, the arrow body 1 is also connected with a thrust piece 6, and one end of the thrust piece 6 connected to the arrow body 1 is the fixed end of the thrust piece 6, and the telescopic end of the thrust piece 6 is hinged with the shape-keeping support structure 2. The shape-keeping support structure 2 is unfolded outward around the lower rotating shaft 9 under the action of the thrust piece 6, and moves from the retracted state to the landing support state, so that the arrow body 1 can land smoothly; at the same time, the telescopic rod structure 3 rotates around the upper rotating shaft 8 connected to the arrow body 1 during the rotation of the shape-keeping support structure 2, and on the other hand, the relative sliding of the hollow support rods 31 at various levels can be achieved, which can match the unfolding process of the shape-keeping support structure 2, so as to achieve the orderly unfolding process of the shape-keeping support structure 2.

[0071] like Figure 2 and Figure 3 As shown, in this embodiment, a groove 21 is provided on the inner side of the conformal support structure 2; when the conformal support structure 2 is in a retracted state, the telescopic rod structure 3 and the initial locking structure are embedded in the groove 21. The embedded arrangement of the telescopic rod structure 3 and the initial locking structure can reduce the space occupied by the landing recovery mechanism. Preferably, the initial locking structure can realize the initial locking operation and the reset operation through the operating hole. The initial locking structure is an independent module and can be detachably connected to the conformal support structure 2, and can be independently tested and replaced. Specifically, the initial locking structure can be an explosive bolt.

[0072] Combination Figure 1 , Figure 2 and Figure 3As shown, in this embodiment, the outer side of the conformal support structure 2 is streamlined. In the circumferential direction of the rocket body 1, the conformal support structure 2 is an aerodynamic shape with low ends and high in the middle; in the axial flight direction of the rocket body 1, the conformal support structure 2 is an aerodynamic shape with a sharp front and a wide rear. This conformal support structure 2 with an aerodynamic shape can reduce the resistance of the recovery landing mechanism during the ascent process, and can also reduce the resistance of the descending rocket body 1 during the recovery process.

[0073] like Figure 4 As shown, in this embodiment, in the telescopic rod structure 3, the first section of the rod is connected to the rocket body 1, and the last section of the rod is connected to the shape-keeping support structure 2; an oil-pneumatic buffer 7 is connected between the end of the last section of the rod and the shape-keeping support structure 2. The oil-pneumatic buffer 7 is arranged on the last section of the rod of the telescopic rod structure 3, and is driven according to the pneumatic principle of the oil-pneumatic buffer 7, which can effectively reduce the dead weight of the telescopic rod structure 3, thereby reducing the overall weight of the rocket recovery landing device.

[0074] like Figure 5-8 As shown, in this embodiment, the inter-stage locking component 5 includes a locking groove 521 and a locking block structure. Among them, the locking block structure is arranged on the outer wall of the hollow support rod 31 with a smaller tube diameter among the two adjacent hollow support rods 31, and the locking block structure is connected to the hollow support rod 31 with a larger tube diameter. When the two adjacent hollow support rods 31 are extended to the limit position, the locking block structure on the hollow support rod 31 with a larger tube diameter extends into the locking groove 521 on the outer wall of the hollow support rod 31 with a smaller tube diameter, so as to realize the inter-stage locking of the two adjacent hollow support rods 31; this inter-stage locking component 5 has a simple structure and high reliability, and can automatically realize the inter-stage locking of the telescopic rod structure 3.

[0075] Combination Figure 6 and Figure 8As shown, in a specific implementation of the present embodiment, the end of a hollow support rod 31 with a larger diameter is connected to a first connecting ring 51, and the inner wall surface of the first connecting ring 51 is provided with a mounting groove 511 with an opening radially inward. The locking block structure includes a locking block 53 slidably connected to the mounting groove 511 along the radial direction of the telescopic rod structure 3, and an elastic member 54 elastically connected between the bottom of the mounting groove 511 and the locking block 53, and its elastic force drives the locking block 53 to extend out of the opening of the mounting groove 511. Under the elastic force of the elastic member 54, the locking block 53 has an extended state in which at least part of it extends out of the mounting groove 511 to cooperate with the locking groove 521 to lock two adjacent hollow support rods 31, and a retracted state in which it retracts into the mounting groove 511 under the push of an external force. The structural design of installing the locking block structure on the first connecting ring 51 and then connecting the first connecting ring 51 to the end of a hollow support rod 31 with a larger diameter is more convenient to manufacture than the method of directly processing the installation groove 511 on the inner wall of the hollow support rod 31 and installing the locking block structure. On the other hand, since the part of the hollow support rod 31 where the locking block structure is installed needs to withstand greater pressure than other parts, the requirements for the structural strength and thickness of this part are higher. The method of separately manufacturing the first connecting ring 51 and the hollow support rod 31 can reduce the weight of the telescopic rod structure 3 as much as possible while meeting the requirements for the structural strength of each part of the telescopic rod structure 3. Specifically, the elastic member 54 is a spring; the first connecting ring 51 and the locking block 53 are both made of titanium alloy material; and the hollow support rod 31 is made of carbon fiber material. In other embodiments, the locking block structure can also be directly installed inside a hollow support rod 31 with a larger diameter, and the locking block structure can also be replaced by an elastic block with its own elasticity.

[0076] like Figure 5 and Figure 6 As shown, in this embodiment, a gas generator (not shown) is provided in the telescopic rod structure 3, and the gas generator pushes the telescopic rod structure 3 to extend through the gas generated by the gas generator to maintain the rigid state of the telescopic rod structure 3 after the extension, and the interstage locking component 5 also includes a sealing structure sleeved on the end of a hollow support rod 31 with a larger diameter. One end of the sealing structure is against a hollow support rod 31 with a smaller diameter, which is used to close the gap between two adjacent hollow support rods 31. The setting of the sealing structure can ensure the airtightness of the telescopic rod structure 3 during the extension process, thereby ensuring that the telescopic rod structure 3 can maintain a stable rigid state, providing a stable and reliable support for the landing of the rocket body 1.

[0077] Specifically, the sealing structure includes a set 55 and a sealing member 56. The set 55 includes a first ring 551 sleeved on the end of a hollow support rod 31 with a larger diameter and a second ring 552 connected to the first ring 551. The inner wall of the second ring 552 is provided with an annular groove 553 with an opening radially inward; the sealing member 56 is embedded in the annular groove 553, and one end thereof extending out of the annular groove 553 is tightly fitted with the outer wall of a hollow support rod 31 with a smaller diameter. Specifically, the sealing member 56 is made of rubber, a flexible sealing gasket or other materials, as long as the sealing member 56 can seal the gap between the second ring 552 and the hollow support rod 31 with a smaller diameter and does not completely hinder the relative movement between the two.

[0078] like Figure 6 As shown, in this embodiment, the connection surface between the first connection ring 51 and the hollow support rod 31 with a larger diameter is a wedge surface. The wedge-shaped connection surface can increase the connection area between the first connection ring 51 and the hollow support rod 31, thereby improving the connection reliability of the first connection ring 51.

[0079] like Figure 6 As shown, in this embodiment, a first protruding structure 522 is further provided on the outer wall of a hollow support rod 31 with a smaller diameter, which is located on the outer side of the locking groove 521. The first protruding structure 522 can cooperate with the outer side of the locking block structure to prevent the hollow support rod 31 with a smaller diameter from shrinking inward, thereby improving the locking effect of the inter-stage locking component 5. Specifically, the first protruding structure 522 is a first boss protruding on the outer wall of the hollow support rod 31 with a smaller diameter; during the telescopic process of the telescopic rod structure 3, a first inclined guide surface is provided on the side of the first boss facing the locking block 53, and a second inclined guide surface matching the shape of the first inclined guide surface is provided on the locking block 53. The provision of the first inclined guide surface and the second inclined guide surface facilitates the first boss and the locking block 53 to push the locking block 53 to shrink into the installation groove 511 during the relative movement, and after the thrust of the first boss on the locking block 53 disappears, the locking block 53 can be better extended into the locking groove 521 under the action of the elastic member 54 to achieve the locking of the two positions. Furthermore, the second collar 552 has a limiting end that cooperates with the first protruding structure 522 so that a hollow support rod 31 with a smaller diameter is at least partially limited in the inner cavity of a hollow support rod 31 with a larger diameter. The limiting end can limit the first protruding structure 522 from another side, thereby improving the reliability of the inter-stage locking component 5.

[0080] In this embodiment, a hollow support rod 31 with a smaller diameter includes a rod body and a second connecting ring 52 connected to the rod body, and the locking groove 521 and the first protruding structure 522 are both formed on the outer wall of the second connecting ring 52. Since the portion of the hollow support rod 31 where the locking groove 521 and the first protruding structure 522 are provided needs to withstand greater pressure than other portions, the requirements for the structural strength and thickness of this portion are higher. The second connecting ring 52 and the hollow support rod 31 are made separately, which can reduce the weight of the telescopic rod structure 3 as much as possible while meeting the requirements for the structural strength of each portion of the telescopic rod structure 3. Specifically, the second connecting ring 52 is made of titanium alloy material; the rod body of the hollow support rod 31 is made of carbon fiber material.

[0081] like Figure 7 and Figure 8 As shown, in the present embodiment, a plurality of mounting grooves 511 are evenly spaced along the circumferential direction of the first connecting ring 51, and a locking block 53 is correspondingly arranged in each mounting groove 511; the inter-stage locking component 5 composed of a plurality of locking blocks 53 can not only make the locking between the two adjacent hollow support rods 31 more secure, but also make the consistency of the gap between the two adjacent hollow support rods 31 higher, thereby ensuring the sealing of the telescopic rod structure 3 after the inter-stage locking.

[0082] like Figure 6 and Figure 8 As shown, the connection surface between the second connection ring 52 and the rod body of the hollow support rod 31 is a wedge surface, and the inner wall of the second connection ring 52 and the inner wall of the rod body together constitute the inner wall of the hollow support rod 31. The wedge-shaped connection surface can increase the connection area between the second connection ring 52 and the rod body, thereby improving the connection reliability of the second connection ring 52. Specifically, both sides of the second connection ring 52 are provided with wedge surfaces matching the rod body.

[0083] like Figure 7 As shown, in this embodiment, a second protrusion structure 57 is provided on the outer wall of a hollow support rod 31 with a smaller diameter located inside a hollow support rod 31 with a larger diameter. The second protrusion structure 57 guides the telescopic movement of the hollow support rod 31, and can ensure that the hollow support rod 31 performs telescopic movement along its axial direction, thereby reducing the influence of the movement deviation of the hollow support rod 31 on the sealing property of the telescopic rod structure 3.

[0084] In this embodiment, the support rods of the conformal support structure 2 and the telescopic rod structure 3 are made of carbon fiber materials, and the first connecting ring 51, the locking block structure, the second connecting ring 52, the kit 55 and other components of the interstage locking structure are made of titanium alloy materials. Carbon fiber materials have the advantages of high strength, good heat resistance and impact resistance, and light weight, which can effectively reduce the overall weight of the rocket recovery landing device and enhance the carrying capacity of the rocket. Titanium alloy has high strength and good heat resistance, which can ensure the stability of the interstage locking structure.

[0085] In summary, the sub-stage recovery and landing mechanism of the launch vehicle provided in the embodiment of the present invention is a landing mechanism for recovering the first stage of the launch vehicle, which is attached to the surface of the rocket body 1 (such as the landing mechanism of the first stage of the launch vehicle) under the action of the conformal support structure 2 during the ascending stage and the descending stage of the launch vehicle before landing. Figure 1 As shown in the figure, during this process, the conformal support structure 2 mainly plays the role of rectifying and protecting the internal mechanism from heat flow interference; before the rocket sub-stage lands, the initial unlocking structure is opened, and the conformal support structure 2 rotates around the lower shaft 9 under the action of the thrust piece 6, and the telescopic rod structure 3 rotates around the upper shaft 8, and at the same time, the various levels of the telescopic rod structure 3 slide relative to each other. When the conformal support structure 2 moves to the final position, the telescopic rod structure 3 also moves to the extreme position, so that the telescopic rod structure 3 becomes a rigid rod, and a stable triangular structure is formed between the rocket body 1, the conformal support structure 2 and the telescopic rod structure 3. The telescopic rod structure 3 can provide strong and reliable support for the conformal support structure 2, so that the sub-stage of the carrier rocket can land smoothly and provide strong support. This recovery and landing mechanism solves the problem of sub-stage recovery after the separation of the first stage of the carrier rocket. After the separation of the first and second stages of the carrier rocket, the first stage can smoothly return to the ground recovery site when landing, which provides guarantees for the reuse of the first stage product, reduces costs, and shortens the production and launch cycle.

[0086] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A substage recovery and landing mechanism for a launch vehicle, characterized in that: include: Arrow body (1); A plurality of shape-preserving support structures (2) are provided around the circumference of the arrow body (1), one end of which is rotatably connected to the arrow body (1) around a first axis; the shape-preserving support structure (2) has a retracted state in which it is retracted to the outer surface of the arrow body (1) when locked by an initial locking structure, and a landing support state in which it is extended outward after the initial locking structure is unlocked; A telescopic rod structure (3), one end of which is hinged to the arrow body (1) and the other end of which is hinged to the shape-preserving support structure (2), comprising at least two hollow support rods (31) that are movably sleeved in sequence; an inter-stage locking component (5) disposed at a connection node between two adjacent hollow support rods (31) and used for locking the two adjacent hollow support rods (31) after being extended to an extreme position, so that the telescopic rod structure (3), the conformal support structure (2) in the landing support state, and the rocket body (1) form a triangular structure; The inter-stage locking component (5) comprises: A locking groove (521) is arranged on the outer wall of the hollow support rod (31) with a smaller diameter; A locking block structure connected to the hollow support rod (31) with a larger diameter, when two adjacent hollow support rods (31) are extended to an extreme position, the locking block structure extends into the locking groove (521) to lock the two adjacent hollow support rods (31); The end of the hollow support rod (31) with a larger diameter is connected to a first connecting ring (51), and the inner wall surface of the first connecting ring (51) is provided with a mounting groove (511) opening radially inward; the locking block structure comprises: A locking block (53) is slidably connected to the installation slot (511) along the radial direction of the telescopic rod structure (3), and has an extended state in which at least part of the locking block extends out of the installation slot (511) to cooperate with the locking slot (521) to lock two adjacent hollow support rods (31), and a retracted state in which the locking block is retracted into the installation slot (511); An elastic member (54) elastically connected between the bottom of the installation slot (511) and the locking block (53), and whose elastic force drives the locking block (53) to extend out of the opening of the installation slot (511); A first protruding structure (522) is also provided on the outer wall of the hollow support rod (31) with a smaller diameter and located on the outer side of the locking groove (521), and the first protruding structure (522) is used to cooperate with the outer side of the locking block structure to prevent the hollow support rod (31) with a smaller diameter from shrinking inwards; The inter-stage locking component (5) further comprises: A sealing structure, which is sleeved on the end of a hollow support rod (31) with a larger diameter and abuts against a hollow support rod (31) with a smaller diameter, and is used to close the gap between two adjacent hollow support rods (31); The sealing structure comprises: The set (55) comprises a first sleeve ring (551) sleeved on the end of a hollow support rod (31) with a larger diameter and a second sleeve ring (552) connected to the first sleeve ring (551), wherein the inner wall of the second sleeve ring (552) is provided with an annular groove (553) with an opening radially inward; A sealing member (56) is embedded in the annular embedding groove (553), and one end of the sealing member extending out of the annular embedding groove (553) is tightly fitted with the outer wall of a hollow support rod (31) with a smaller diameter; The second collar (552) has a limiting end that cooperates with the first protruding structure (522) so that a hollow support rod (31) with a smaller diameter is at least partially restricted in the inner cavity of a hollow support rod (31) with a larger diameter.

2. The substage recovery and landing mechanism of a carrier rocket according to claim 1, characterized in that: There are a plurality of installation grooves (511), which are evenly spaced along the circumferential direction of the first connecting ring (51); and a locking block (53) is correspondingly arranged in each installation groove (511).

3. The substage recovery and landing mechanism of a carrier rocket according to claim 1, characterized in that: The connection surface between the first connection ring (51) and the hollow support rod (31) with a larger diameter is a wedge surface.

4. The substage recovery and landing mechanism of a carrier rocket according to claim 1, characterized in that: The hollow support rod (31) with a smaller diameter comprises a rod body and a second connecting ring (52) connected to the rod body, and the locking groove (521) and the first protruding structure (522) are both formed on the outer wall of the second connecting ring (52).

5. The sub-stage recovery and landing mechanism of a carrier rocket according to claim 4, characterized in that: The connecting surface between the second connecting ring (52) and the rod body is a wedge surface, and the inner wall of the second connecting ring (52) and the inner wall of the rod body together constitute the inner wall of the hollow support rod (31).

6. The sub-stage recovery and landing mechanism of a carrier rocket according to claim 1, characterized in that: A second protruding structure (57) is provided on the outer wall of the hollow support rod (31) with a smaller diameter and located inside the hollow support rod (31) with a larger diameter.

7. The substage recovery and landing mechanism of a carrier rocket according to any one of claims 1 to 6, characterized in that: The arrow body (1) is also connected to a thrust piece (6); the telescopic end of the thrust piece (6) is connected to the shape-conserving support structure (2), and the thrust piece (6) is used to drive the shape-conserving support structure (2) to rotate from the retracted state to the landing support state; the telescopic rod structure (3) realizes relative sliding of each section of the hollow support rod (31) during the rotation of the shape-conserving support structure (2).

8. The sub-stage recovery and landing mechanism of a carrier rocket according to any one of claims 1 to 6, characterized in that: A groove (21) is provided on the inward side of the shape-retaining support structure (2); when the shape-retaining support structure (2) is in the retracted state, the telescopic rod structure (3) is embedded in the groove (21).

9. The sub-stage recovery and landing mechanism of a carrier rocket according to claim 8, characterized in that: The initial locking structure is also embedded in the groove (21), and the connection between the initial locking structure and the shape-preserving support structure (2) is a detachable connection.

10. The sub-stage recovery and landing mechanism of a carrier rocket according to any one of claims 1 to 6, characterized in that: The outer shape of the side of the shape-retaining support structure (2) facing outward is streamlined.

11. The substage recovery and landing mechanism of a carrier rocket according to claim 10, characterized in that: In the circumferential direction of the arrow body (1), the conformal support structure (2) is an aerodynamic shape with low ends and a high middle; in the axial flight direction of the arrow body (1), the conformal support structure (2) is an aerodynamic shape with a pointed front and a wide rear.

12. The substage recovery and landing mechanism of a carrier rocket according to any one of claims 1 to 6, characterized in that: In the telescopic rod structure (3), the first section of the support rod is connected to the arrow body (1), and the last section of the support rod is connected to the shape-preserving support structure (2); an oil-gas buffer (7) is connected between the end of the last section of the support rod and the shape-preserving support structure (2).

13. The sub-stage recovery and landing mechanism of a carrier rocket according to any one of claims 1 to 6, characterized in that: The shape-preserving support structure (2) and the telescopic rod structure (3) are both made of carbon fiber material.

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