Carrier rocket landing recovery device

Abstract

The invention discloses a carrier rocket landing recovery device, and relates to the technical field of rocket recovery, the carrier rocket landing recovery device comprises a rocket body, an adjusting mechanism is arranged on the surface of the rocket body, and a supporting mechanism is arranged at the bottom end of the adjusting mechanism. The landing legs are connected with the movable rods, the ground contact legs are as high as the bottom of an engine of the rocket body in the initial state, and the six ground contact legs are compactly spliced in the ununfolded state, so that the minimum space is occupied when the landing legs are not used, and it is ensured that the bottom of the rocket body can be effectively deployed in the limited space; the grounding legs are one-sixth sector rings, the cross sections of the grounding legs are round, the grounding legs are made of high-strength materials to support the stability of the grounding legs, the six groups of grounding legs form an annular structure, a plurality of contact points are provided for the rocket body, the stability during landing is enhanced, and the design of terminals among the grounding legs can effectively disperse impact force during landing. And the risk that the bottom of the rocket is damaged is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket recovery, and particularly relates to a landing recovery device for a launch vehicle. Background Art

[0002] With the development of space technology, especially the continuous progress of reusable rockets, how to provide sufficient stability during the rocket landing stage has become a key issue. In the recovery of medium and small rockets, how to achieve stable landing, especially in the case of relatively insufficient rocket attitude control systems, has become a technical challenge.

[0003] Patent Publication No. CN208278353U discloses a vertical landing recovery device for a launch vehicle, including a rocket body. A strengthening frame is installed below the rocket body, a stabilizer is installed below the strengthening frame, wings are installed outside the stabilizer, an engine nozzle is installed at the bottom end of the stabilizer, recovery holes are provided at the bottom ends of the wings, landing legs are installed in the recovery holes through bolts, a telescopic rod is installed at one end of the landing leg, and a support foot is installed at one end of the telescopic rod.

[0004] To solve the problem of poor stability, the prior art is to use a stabilizer to accommodate the landing legs, which not only protects the landing legs from being ablated by high-temperature gas flow but also provides a stability control force for the rocket. However, there will still be situations where precise adjustment cannot be achieved and the stability of the landing legs is poor, resulting in poor adjustment ability of the rocket body and prone to tipping problems. Summary of the Invention

[0005] The purpose of the present invention is to provide a landing recovery device for a launch vehicle to solve the problems raised in the above background art.

[0006] To solve the above technical problems, the technical solution adopted by the present invention is:

[0007] A landing recovery device for a launch vehicle, including a rocket body, an adjustment mechanism is arranged on the surface of the rocket body, and a support mechanism is arranged at the bottom end of the adjustment mechanism.

[0008] The adjustment mechanism includes a housing, the housing is movably installed on the surface of the rocket body, there are six groups of the housing, the housing is evenly distributed on the surface of the rocket body, a groove is arranged at the top end of the housing, a movable connecting piece is fixedly installed on the surface of the groove, and a first fixing seat is movably installed on the surface of the movable connecting piece. The first fixing seat is fixedly installed on the surface of the rocket body.

[0009] A further improvement of the technical solution of the present invention is that: a vertical groove is arranged on one side of the housing close to the rocket body, a movable block two is fixedly installed on the surface of the vertical groove, and a first hydraulic cylinder is movably installed on the surface of the movable block two.

[0010] A further improvement of the technical solution of the present invention lies in that: the diameter of the first hydraulic cylinder is smaller than the diameter of the vertical groove, and a first movable block is movably installed at the top end of the first hydraulic cylinder, and the first movable block is fixedly installed on the surface of the rocket body.

[0011] A further improvement of the technical solution of the present invention lies in that: a second hydraulic cylinder is fixedly installed inside the outer shell, there are two groups of the second hydraulic cylinders, and the second hydraulic cylinders are symmetrically distributed inside the outer shell and the telescopic ends of the second hydraulic cylinders extend to the outside of the outer shell.

[0012] A further improvement of the technical solution of the present invention lies in that: the second hydraulic cylinder includes a cylinder body, a first valve is fixedly installed at the top end of the cylinder body, and a second valve is fixedly installed on the lower surface of the second hydraulic cylinder.

[0013] A further improvement of the technical solution of the present invention lies in that: hydraulic oil is arranged inside the cylinder body, a piston is movably installed inside the cylinder body, a movable rod is fixedly installed at the bottom end of the piston, a sealing gasket is movably installed on the surface of the movable rod, and the sealing gasket is fixedly installed on the surface of the cylinder body.

[0014] A further improvement of the technical solution of the present invention lies in that: the support mechanism includes landing legs, the landing legs are fixedly installed at the bottom end of the movable rod, a touchdown leg is fixedly installed at the bottom end of the landing legs, and a pressure sensor is fixedly installed at the bottom end of the touchdown leg.

[0015] Due to the adoption of the above technical solution, the technical progress achieved by the present invention compared with the prior art is:

[0016] 1. The present invention provides a landing and recovery device for a launch vehicle, which uses the cooperation of a housing, a groove, a first fixing seat, a movable connecting piece, a vertical groove, a first hydraulic cylinder, a first movable block, a second movable block, a second hydraulic cylinder, a cylinder body, a first valve, a second valve, a piston, hydraulic oil, a movable rod, and a sealing gasket. By arranging six groups of housings on the surface of the rocket body, a thermal insulation layer and a protective coating are arranged on the surface of the housing to ensure that the first hydraulic cylinder and the second hydraulic cylinder are not affected by extreme temperature differences. When the rocket body lands, the first valve injects hydraulic oil, so that the hydraulic oil pushes the piston to displace downward and pushes the movable rod to extend outward. The hydraulic oil on the other side of the piston is discharged through the second valve, so that the support mechanism supports the ground. The cylinder body is made of high-strength alloy steel, the cylinder diameter is set to 50 mm, and its working pressure reaches 1.5 Mpa. The hydraulic oil is high-temperature hydraulic oil, which has thermal stability and low-temperature fluidity. A sealing gasket is arranged on the surface of the cylinder body to effectively prevent hydraulic oil leakage. Through the redundant design of arranging two groups of second hydraulic cylinders, when one group of second hydraulic cylinders fails, the other group of second hydraulic cylinders can still continue to work, ensuring that the support mechanism can be deployed stably. The first fixing seat is connected to the movable connecting piece on the surface of the groove. When the angle of the housing needs to be adjusted, the first movable block is connected to the first hydraulic cylinder inside the vertical groove. The first hydraulic cylinder pushes the second movable block, so that the housing draws an arc with the first fixing seat as the center of the circle, and the bottom end of the housing expands outward, so that the extending angle of the second hydraulic cylinder changes, thereby adjusting the support angle of the support mechanism. Each group of adjustment mechanisms is connected to the first fixing seat through the first movable block and is covered by the housing. While ensuring its connection stability, the adjustment mechanism also forms a modular component, which is convenient for later maintenance and replacement. At the same time, the housing has a shape that is pointed at the top and wide at the bottom, reducing wind resistance when the rocket body ascends. When descending, a resistance is formed through the wide-bottom design at the lower end, slowing down the descending speed and making it easier to land smoothly.

[0017] 2. The present invention provides a landing and recovery device for a launch vehicle, which uses the cooperation of landing legs, touchdown legs, and pressure sensors. The landing legs are connected to the movable rod. In the initial state, the touchdown legs are at the same height as the bottom of the rocket body engine. And in the undeployed state, the six groups of touchdown legs are tightly assembled, so that the minimum space is occupied when not in use, ensuring that the bottom of the rocket body can also be effectively deployed in a limited space. The touchdown legs are one-sixth of an annular shape, with a circular cross-section, and their material is high-strength material to support their stability. An annular structure is formed by six groups of touchdown legs, providing multiple contact points for the rocket body and enhancing the stability during landing. The terminal design between the touchdown legs can effectively disperse the impact force during landing, reducing the risk of damage to the bottom of the rocket. And through the pressure sensors at the bottom end, the contact situation between the touchdown legs and the ground is monitored in real time and quickly adjusted to ensure that the rocket lands vertically and stably. Description of the Drawings

[0018] Figure 1Schematic diagram of the three-dimensional structure of the present invention;

[0019] Figure 2 Schematic diagram of the axonometric view structure of the present invention;

[0020] Figure 3 Schematic diagram of the adjustment mechanism of the present invention;

[0021] Figure 4 Schematic diagram of the housing of the present invention;

[0022] Figure 5 Schematic diagram of the second hydraulic cylinder of the present invention;

[0023] Figure 6 Schematic diagram of the support mechanism of the present invention.

[0024] In the figure: 1, rocket body; 2, adjustment mechanism; 201, housing; 202, groove; 203, fixed seat 1; 204, movable connecting piece; 205, vertical groove; 206, first hydraulic cylinder; 207, movable block 1; 208, movable block 2; 209, second hydraulic cylinder; 2091, cylinder block; 2092, valve 1; 2093, valve 2; 2094, piston; 2095, hydraulic oil; 2096, movable rod; 2097, sealing washer; 3, support mechanism; 301, landing leg; 302, ground-touching leg; 303, pressure sensor. Specific embodiments

[0025] The present invention will be further described in detail below with reference to the embodiments:

[0026] Embodiment 1

[0027] As Figure 1-6As shown in the figure, the present invention provides a landing and recovery device for a launch vehicle, which includes a rocket body 1. An adjustment mechanism 2 is arranged on the surface of the rocket body 1, and a support mechanism 3 is arranged at the bottom end of the adjustment mechanism 2. The adjustment mechanism 2 includes a housing 201, and the housing 201 is movably installed on the surface of the rocket body 1. There are six groups of the housing 201, and the housing 201 is evenly distributed on the surface of the rocket body 1. A groove 202 is arranged at the top end of the housing 201, and a movable connecting piece 204 is fixedly installed on the surface of the groove 202. A first fixed seat 203 is movably installed on the surface of the movable connecting piece 204, and the first fixed seat 203 is fixedly installed on the surface of the rocket body 1. A vertical groove 205 is arranged on one side of the housing 201 close to the rocket body 1, and a second movable block 208 is fixedly installed on the surface of the vertical groove 205. A first hydraulic cylinder 206 is movably installed on the surface of the second movable block 208. The diameter of the first hydraulic cylinder 206 is smaller than the diameter of the vertical groove 205. The top end of the first hydraulic cylinder 206 is movably installed with a first movable block 207, and the first movable block 207 is fixedly installed on the surface of the rocket body 1. A second hydraulic cylinder 209 is fixedly installed inside the housing 201. There are two groups of the second hydraulic cylinder 209, and the second hydraulic cylinder 209 is symmetrically distributed inside the housing 201 and the telescopic end of the second hydraulic cylinder 209 extends to the outside of the housing 201. The second hydraulic cylinder 209 includes a cylinder body 2091, a first valve 2092 is fixedly installed at the top end of the cylinder body 2091, a second valve 2093 is fixedly installed on the lower surface of the second hydraulic cylinder 209. Hydraulic oil 2095 is arranged inside the cylinder body 2091, and a piston 2094 is movably installed inside the cylinder body 2091. A movable rod 2096 is fixedly installed at the bottom end of the piston 2094, and a sealing washer 2097 is movably installed on the surface of the movable rod 2096, and the sealing washer 2097 is fixedly installed on the surface of the cylinder body 2091.

[0028] In this embodiment, by arranging six groups of outer shells 201 on the surface of the rocket body 1, a thermal insulation layer and a protective coating are arranged on the surface of the outer shell 201 to ensure that the first hydraulic cylinder 206 and the second hydraulic cylinder 209 are not affected by extreme temperature differences. When the rocket body 1 lands, the first valve 2092 injects hydraulic oil 2095, so that the hydraulic oil 2095 pushes the piston 2094 to displace downward and pushes the movable rod 2096 to extend outward. The hydraulic oil 2095 on the other side of the piston 2094 is discharged through the second valve 2093, so that the support mechanism 3 supports the ground. The cylinder block 2091 is made of high-strength alloy steel, the cylinder diameter is set to 50 mm, and its working pressure reaches 1.5 Mpa. The hydraulic oil 2095 is a high-temperature hydraulic oil, which has thermal stability and low-temperature fluidity. A sealing gasket 2097 is arranged on the surface of the cylinder block 2091 to effectively prevent the leakage of the hydraulic oil 2095. Through the redundant design of arranging two groups of second hydraulic cylinders 209, when one group of second hydraulic cylinders 209 fails, the other group of second hydraulic cylinders 209 can still continue to work, ensuring that the support mechanism 3 can be stably deployed. The first fixing seat 203 is connected to the surface of the groove 202 through the movable connecting piece 204. When the angle of the outer shell 201 needs to be adjusted, the first hydraulic cylinder 206 inside the vertical groove 205 is connected to the movable block 207. The first hydraulic cylinder 206 pushes the movable block 208, so that the outer shell 201 draws an arc with the first fixing seat 203 as the center of the circle, and the bottom end of the outer shell 201 expands outward, so that the extending angle of the second hydraulic cylinder 209 changes, thereby adjusting the support angle of the support mechanism 3. And each group of adjusting mechanisms 2 is connected to the first fixing seat 203 through the movable block 207 and is covered by the outer shell 201. While ensuring its connection stability, it also makes the adjusting mechanism 2 form a modular component, which is convenient for later maintenance and replacement. At the same time, the outer shell 201 has a shape with a pointed top and a wide bottom, which reduces the wind resistance when the rocket body 1 ascends. When descending, a resistance is formed through the wide-bottom design at the lower end, slowing down the descending speed and making it easier to land smoothly.

[0029] Embodiment 2

[0030] As Figure 1-6 shown, on the basis of Embodiment 1, the present invention provides a technical solution: Preferably, the support mechanism 3 includes a landing leg 301, the landing leg 301 is fixedly installed at the bottom end of the movable rod 2096, a grounding leg 302 is fixedly installed at the bottom end of the landing leg 301, and a pressure sensor 303 is fixedly installed at the bottom end of the grounding leg 302.

[0031] In this embodiment, the landing leg 301 is connected to the movable rod 2096. In the initial state, the touchdown leg 302 is at the same height as the bottom of the rocket body 1 engine. And in the undeployed state, the six groups of touchdown legs 302 are tightly fitted together, so that the minimum space is occupied when not in use, ensuring that the bottom of the rocket body 1 can also be effectively deployed in a limited space. The touchdown leg 302 is a one-sixth sector ring, its cross-section is circular, and its material is a high-strength material to support its stability. The six groups of touchdown legs 302 form an annular structure to provide multiple contact points for the rocket body 1, enhancing the stability during landing. The interruption design between the touchdown legs 302 can effectively disperse the impact force during landing, reducing the risk of damage to the bottom of the rocket. And through the bottom pressure sensor 303, the contact situation between the touchdown leg 302 and the ground is monitored in real time and quickly adjusted to ensure that the rocket lands vertically and stably.

[0032] Next, the working principle of the landing and recovery device of the launch vehicle will be specifically described.

[0033] As Figure 1-6As shown in the figure, by setting six groups of outer shells 201 on the surface of the rocket body 1, a thermal insulation layer and a protective coating are provided on the surface of the outer shell 201 to ensure that the first hydraulic cylinder 206 and the second hydraulic cylinder 209 are not affected by extreme temperature differences. When the rocket body 1 lands, the first valve 2092 injects hydraulic oil 2095, causing the hydraulic oil 2095 to push the piston 2094 to displace downward and push the movable rod 2096 to extend outward. The hydraulic oil 2095 on the other side of the piston 2094 is discharged through the second valve 2093, enabling the support mechanism 3 to support the ground. The cylinder block 2091 is made of high-strength alloy steel, with a cylinder diameter of 50 mm and a working pressure reaching 1.5 Mpa. The hydraulic oil 2095 is high-temperature hydraulic oil, having thermal stability and low-temperature fluidity. A sealing gasket 2097 is provided on the surface of the cylinder block 2091 to effectively prevent the leakage of the hydraulic oil 2095. Through the redundant design of setting two groups of second hydraulic cylinders 209, when one group of second hydraulic cylinders 209 fails, the other group of second hydraulic cylinders 209 can still continue to work, ensuring that the support mechanism 3 can be stably deployed. The fixed seat 203 is connected to the surface of the groove 202 through the movable connecting piece 204. When the angle of the outer shell 201 needs to be adjusted, the movable block 207 is connected to the first hydraulic cylinder 206 inside the vertical groove 205. The first hydraulic cylinder 206 pushes the movable block 208, causing the outer shell 201 to draw an arc with the fixed seat 203 as the center. The bottom end of the outer shell 201 expands outward, causing the extension angle of the second hydraulic cylinder 209 to change, thereby adjusting the support angle of the support mechanism 3. Each group of adjustment mechanisms 2 is connected to the fixed seat 203 through the movable block 207 and is covered by the outer shell 201. While ensuring its connection stability, it also makes the adjustment mechanism 2 form a modular component, facilitating later maintenance and replacement. At the same time, the outer shell 201 has a shape with a pointed top and a wide bottom, reducing wind resistance when the rocket body 1 ascends. When descending, a resistance is formed through the wide-bottom design at the lower end, slowing down the descending speed and making it easier to land smoothly. At the same time, the landing leg 301 is connected to the movable rod 2096. In the initial state, the ground-touching leg 302 is at the same height as the bottom of the rocket body 1's engine. And in the non-deployed state, the six groups of ground-touching legs 302 are tightly assembled, occupying the smallest space when not in use and ensuring that the bottom of the rocket body 1 can also be effectively deployed in a limited space. The ground-touching leg 302 is one-sixth of an annular sector, with a circular cross-section, and its material is a high-strength material to support its stability. The six groups of ground-touching legs 302 form an annular structure, providing multiple contact points for the rocket body 1 and enhancing the stability during landing. The interrupted design between the ground-touching legs 302 can effectively disperse the impact force during landing, reducing the risk of damage to the bottom of the rocket. And through the bottom pressure sensor 303, the contact situation between the ground-touching leg 302 and the ground is monitored in real time and quickly adjusted to ensure that the rocket lands vertically and stably.

[0034] The above has generally described the present invention in detail. However, based on the present invention, some modifications or improvements can be made thereto, which are obvious to those of ordinary skill in the art. Therefore, modifications or improvements that do not depart from the spirit and idea of the present invention are within the protection scope of the present invention.

Claims

1. A launch vehicle landing recovery device, comprising a rocket body (1), characterized in that: The surface of the rocket body (1) is provided with an adjustment mechanism (2), and the bottom end of the adjustment mechanism (2) is provided with a support mechanism (3); The adjustment mechanism (2) includes a shell (201), and the shell (201) is movably mounted on the surface of the rocket body (1). The shell (201) is provided with six groups, and the shells (201) are evenly distributed on the surface of the rocket body (1). The top of the shell (201) is provided with a groove (202), and a movable connecting piece (204) is fixedly mounted on the surface of the groove (202). A fixed seat (203) is movably mounted on the surface of the movable connecting piece (204), and the fixed seat (203) is fixedly mounted on the surface of the rocket body (1).

2. A launch vehicle landing recovery device according to claim 1, characterized in that: A vertical groove (205) is provided on one side of the shell (201) close to the rocket body (1), a movable block 2 (208) is fixedly mounted on the surface of the vertical groove (205), and a first hydraulic cylinder (206) is movably mounted on the surface of the movable block 2 (208).

3. A launch vehicle landing recovery device according to claim 2, characterized in that: The diameter of the first hydraulic cylinder (206) is smaller than the diameter of the vertical slot (205), and a movable block 1 (207) is movably mounted on the top of the first hydraulic cylinder (206), and the movable block 1 (207) is fixedly mounted on the surface of the rocket body (1).

4. A launch vehicle landing recovery device according to claim 1, characterized in that: A second hydraulic cylinder (209) is fixedly installed inside the housing (201), and two groups of the second hydraulic cylinders (209) are provided. The second hydraulic cylinders (209) are symmetrically distributed inside the housing (201), and the telescopic ends of the second hydraulic cylinders (209) extend to the outside of the housing (201).

5. A launch vehicle landing recovery device according to claim 4, characterized in that: The second hydraulic cylinder (209) comprises a cylinder body (2091), a valve 1 (2092) is fixedly mounted on the top end of the cylinder body (2091), and a valve 2 (2093) is fixedly mounted on the lower end surface of the second hydraulic cylinder (209).

6. A launch vehicle landing recovery device according to claim 5, characterized in that: Hydraulic oil (2095) is arranged inside the cylinder body (2091), a piston (2094) is movably installed inside the cylinder body (2091), a movable rod (2096) is fixedly installed at the bottom end of the piston (2094), a sealing gasket (2097) is movably installed on the surface of the movable rod (2096), and the sealing gasket (2097) is fixedly installed on the surface of the cylinder body (2091).

7. A launch vehicle landing recovery device according to claim 6, characterized in that: The support mechanism (3) comprises a landing leg (301), wherein the landing leg (301) is fixedly mounted on the bottom end of the movable rod (2096), a ground contact leg (302) is fixedly mounted on the bottom end of the landing leg (301), and a pressure sensor (303) is fixedly mounted on the bottom end of the ground contact leg (302).

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