CN216283053U

CN216283053U - Recovery structure of carrier rocket radome fairing

Info

Publication number: CN216283053U
Application number: CN202122753370.0U
Authority: CN
Inventors: 楚龙飞; 胡振宇; 吴晓飞
Original assignee: Beijing Lulk Spaceflight Technology Co ltd
Current assignee: Beijing Lulk Spaceflight Technology Co ltd
Priority date: 2021-11-11
Filing date: 2021-11-11
Publication date: 2022-04-12
Anticipated expiration: 2031-11-11

Abstract

The utility model discloses a recovery structure of a carrier rocket fairing, which comprises a fairing half cover, wherein two far sides of the fairing half cover are fixedly connected with two far mounting plates, one near side of the two mounting plates is rotatably connected with a same first rotating shaft, a resistance plate is fixedly sleeved on the outer wall of the first rotating shaft, and a driving assembly for rotating the two first rotating shafts is arranged in the fairing half cover; the utility model has simple structure and convenient use, can buffer the half fairing to a certain extent through the bottom plate so as to protect the half fairing and prevent the half fairing from being damaged when the half fairing descends, and can increase the resistance generated when the half fairing descends through the resistance plate so as to reduce the descending speed of the half fairing and protect the half fairing to a certain extent.

Description

Recovery structure of carrier rocket radome fairing

Technical Field

The utility model relates to the technical field of fairings, in particular to a recovery structure of a fairing of a carrier rocket.

Background

The fairing is used for protecting the satellite and other effective loads to prevent the satellite from being influenced by harmful environments such as aerodynamic force, pneumatic heating, sound vibration and the like, is an important component of the carrier rocket, and can be separated from the carrier rocket when the carrier rocket is lifted into space.

When the traditional fairing is separated from the rocket and descends to a designated height, the fairing descends through a parachute, the descending speed of the fairing is reduced only through the parachute, the fairing is easy to damage when descending, meanwhile, the fairing is usually in direct contact with the ground when descending, and the fairing is easy to damage due to the gravity of the fairing and the descending speed, so that a recovery structure of the fairing of the carrier rocket is provided for solving the problems.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the defects that the fairing is easy to damage when falling and is usually directly contacted with the ground when falling in the prior art, so that the fairing is easy to damage due to the self gravity and the falling speed, and the recovery structure of the fairing of the carrier rocket is provided.

In order to achieve the purpose, the utility model adopts the following technical scheme:

the utility model provides a recovery structure of carrier rocket radome fairing, includes half cover of radome fairing, the equal two mounting panels of keeping away from mutually of the equal fixed connection in both sides that half cover of radome fairing kept away from mutually, two one side that the mounting panel is close to mutually rotates and is connected with same first pivot, the fixed cover of outer wall of first pivot is equipped with the resistance plate, the inside of half cover of radome fairing is provided with makes two first pivot pivoted drive assembly, one of them one side of mounting panel is provided with makes the spacing subassembly of first pivot.

Preferably, the driving assembly comprises a driving groove formed in the inner part of the half cowling of the fairing, a motor is fixedly connected to the inner wall of one side of the driving groove, a second rotating shaft is fixedly connected to an output shaft of the motor, two steel wire ropes are wound on the outer wall of the second rotating shaft, and one ends, far away from the two steel wire ropes, of the two steel wire ropes penetrate through the half cowling of the fairing and are fixedly connected with the outer walls of the two first rotating shafts respectively.

Preferably, the limiting assembly comprises a positioning plate fixedly connected to one side of the mounting plate, the positioning groove is formed in one side of the positioning plate, two sliding grooves located on two sides of the positioning groove are formed in the positioning plate, a sliding plate is slidably connected to the inner wall of each sliding groove, a second spring is fixedly connected to one end of each sliding plate, the other end of each second spring is fixedly connected to the inner wall of one side of each sliding groove, the end, close to each sliding plate, of each sliding plate extends into the corresponding positioning groove and is provided with an arc edge, a limiting plate is fixedly connected to the outer wall of the first rotating shaft, and limiting grooves matched with the two sliding plates are formed in two sides, far away from the limiting plates, of each limiting plate.

Preferably, a first spring is fixedly connected to the bottom of the half cowl of the fairing, and a bottom plate is fixedly connected to the bottom end of the first spring.

Preferably, the bottom of the half cowling of radome fairing is fixedly connected with the elasticity frame, the bottom and the outer wall fixed connection of bottom plate of elasticity frame.

Preferably, the outer wall cover of first pivot is equipped with the torsional spring, the both ends of torsional spring respectively with one side of mounting panel and the outer wall fixed connection of first pivot.

Preferably, the elastic frame is made of rubber.

Compared with the prior art, the utility model has the beneficial effects that:

1. according to the utility model, the starting motor drives the second rotating shaft to rotate, the second rotating shaft can pull the first rotating shaft to rotate through the steel wire rope when rotating, the first rotating shaft can drive the resistance plate to rotate when rotating, the first rotating shaft can drive the limiting plate to rotate when rotating, the limiting plate can extrude the sliding plate when rotating into the positioning groove, the sliding plate can compress the second spring when being extruded, when the resistance plate rotates to a specified position, the limiting groove corresponds to the sliding plate, and the sliding plate extends to the position of the limiting plate fixed in the limiting groove through the elasticity of the second spring.

2. According to the utility model, the bottom plate can extrude the first spring, and meanwhile, the elastic frame can be deformed, so that the half cover of the fairing is buffered to a certain extent, and the half cover of the fairing is prevented from being damaged.

The utility model has simple structure and convenient use, can buffer the half fairing to a certain extent through the bottom plate so as to protect the half fairing and prevent the half fairing from being damaged when the half fairing descends, can increase the resistance generated when the half fairing descends through the resistance plate so as to reduce the descending speed of the half fairing and protect the half fairing to a certain extent, and can limit the first rotating shaft through the matching between the limiting plate and the sliding plate so as to improve the stability of the first rotating shaft.

Drawings

FIG. 1 is a schematic sectional front view of a recovery structure for a launch vehicle fairing according to the present invention;

FIG. 2 is a schematic side cross-sectional structural view of a recovery structure for a launch vehicle fairing according to the present invention;

FIG. 3 is an enlarged schematic view of part A of a recovery structure of a launch vehicle fairing according to the present invention;

FIG. 4 is a schematic sectional view of a positioning slot of a recovery structure of a launch vehicle fairing according to the present invention;

fig. 5 is a schematic perspective view of a sliding plate of a recovery structure of a launch vehicle fairing according to the present invention.

In the figure: 1. a cowl half; 2. a first spring; 3. a base plate; 4. a drive slot; 5. an elastic frame; 6. mounting a plate; 7. a first rotating shaft; 8. a resistance plate; 9. a torsion spring; 10. a limiting plate; 11. a motor; 12. a second rotating shaft; 13. a wire rope; 14. a limiting groove; 15. positioning a plate; 16. positioning a groove; 17. a sliding groove; 18. a sliding plate; 19. a second spring.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

Example one

Referring to fig. 1-5, a recovery structure of carrier rocket radome fairing includes half cover 1 of radome fairing, the equal fixed connection two mounting panels 6 of keeping away from mutually of both sides that half cover 1 of radome fairing kept away from mutually, two one sides that mounting panels 6 were close to mutually rotate and are connected with same first pivot 7, the fixed cover of outer wall of first pivot 7 is equipped with resistance plate 8, the inside of half cover 1 of radome fairing is provided with makes two first pivot 7 pivoted drive assembly, one side of one of them mounting panel 6 is provided with makes the spacing subassembly of first pivot 7.

Example two

The embodiment is improved on the basis of the first embodiment: referring to fig. 1-5, a recovery structure of a fairing of a carrier rocket comprises a fairing half-cover 1, two far-away sides of the fairing half-cover 1 are fixedly connected with two far-away mounting plates 6, one near side of the two mounting plates 6 is rotatably connected with a same first rotating shaft 7, a resistance plate 8 is fixedly sleeved on the outer wall of the first rotating shaft 7, a driving component for rotating the two first rotating shafts 7 is arranged in the fairing half-cover 1 and comprises a driving groove 4 arranged in the fairing half-cover 1, a motor 11 is fixedly connected with the inner wall of one side of the driving groove 4, an output shaft of the motor 11 is fixedly connected with a second rotating shaft 12, two steel wire ropes 13 are wound on the outer wall of the second rotating shaft 12, and the far-away ends of the two steel wire ropes 13 penetrate through the fairing half-cover 1 and are fixedly connected with the outer walls of the two first rotating shafts 7 respectively, and are matched with each other through the motor 11 and the steel wire ropes 13, can make the first rotating shaft 7 rotate, thereby being convenient for adjusting the angle of the resistance plate 8, thereby protecting the half-cover 1 of the fairing to a certain extent, one side of one of the mounting plates 6 is provided with a limiting component which can limit the first rotating shaft 7, the limiting component comprises a positioning plate 15 fixedly connected with one side of the mounting plate 6, one side of the positioning plate 15 is provided with a positioning groove 16, the inside of the positioning plate 15 is provided with two sliding grooves 17 respectively positioned at two sides of the positioning groove 16, the inner wall of the sliding groove 17 is connected with a sliding plate 18 in a sliding manner, one end of the sliding plate 18 is fixedly connected with a second spring 19, the other end of the second spring 19 is fixedly connected with the inner wall of one side of the sliding groove 17, the adjacent ends of the two sliding plates 18 extend into the positioning groove 16 and are provided with arc edges, the outer wall of the first rotating shaft 7 is fixedly connected with a limiting plate 10, the two sides far away from the limiting plate 10 are provided with limiting grooves 14 respectively matched with the two sliding plates 18, the first rotating shaft 7 can be limited through the matching between the limiting plate 10 and the sliding plate 18, so that the resistance plate 8 is limited, the stability of the resistance plate 8 is improved, the first spring 2 is fixedly connected to the bottom of the half-cowl 1 of the fairing, the bottom end of the first spring 2 is fixedly connected with the bottom plate 3, the half-cowl 1 of the fairing is buffered to a certain extent through the mutual matching between the first spring 2 and the bottom plate 3, so that the half-cowl 1 of the fairing is protected, the bottom of the half-cowl 1 of the fairing is fixedly connected with the elastic frame 5, the bottom of the elastic frame 5 is fixedly connected with the outer wall of the bottom plate 3, the first spring 2 and the bottom plate 3 can be shielded through the elastic frame 5, the attractiveness of the half-cowl is ensured, the outer wall of the first rotating shaft 7 is sleeved with the torsion spring 9, two ends of the torsion spring 9 are fixedly connected with one side of the mounting plate 6 and the outer wall of the first rotating shaft 7 respectively, the first rotating shaft 7 can be fixed through the torsion spring 9, the elastic frame 5 can be made of rubber, and the elastic frame 5 can be given certain elasticity through the rubber, so that the resistance of the bottom plate 3 rising when falling is increased, wherein the materials of the components can be made of high-temperature resistant materials, and the technical personnel in the field can carry out optional matching according to the needs or convenience of the technical personnel, and the specific materials are not specified in the application.

The working principle is as follows: when the parachute is used, when the fairing half cover 1 is separated from the rocket, when the parachute is opened, the parachute is arranged inside the fairing half cover 1, which is not described in detail in this document, the starting motor 11 drives the second rotating shaft 12 to rotate, the second rotating shaft 12 can drive the first rotating shaft 7 to rotate through the steel wire rope 13 when rotating, the first rotating shaft 7 can drive the resistance plate 8 to rotate when rotating, meanwhile, the torsion spring 9 can be deformed when the first rotating shaft 7 rotates, the first rotating shaft 7 can drive the limiting plate 10 to rotate when rotating, the sliding plate 18 can be extruded when the limiting plate 10 rotates into the positioning groove 16, the second spring 19 can be compressed when the sliding plate 18 is extruded, when the resistance plate 8 rotates to a specified position, the limiting groove 14 corresponds to the sliding plate 18 at this time, the sliding plate 18 extends to the position of the limiting groove 14 to fix the limiting plate 10 through the elasticity of the second spring 19, thereby fixed resistance board 8's angle to reduce the speed that half cover 1 of radome fairing descends through resistance board 8, when half cover 1 of radome fairing contacted with ground, bottom plate 3 can contact with ground, and bottom plate 3 can extrude first spring 2 this moment, and bottom plate 3 can make elastic frame 5 take place deformation simultaneously, thereby carries out certain buffering to half cover 1 of radome fairing, prevents that it from taking place to damage.

However, as is well known to those skilled in the art, the working principle and wiring method of the half cowl 1 and the motor 11 are common and are conventional means or common knowledge, and will not be described herein again, and those skilled in the art can make any choice according to their needs or convenience.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and equivalent alternatives or modifications according to the technical solution of the present invention and the inventive concept thereof should be covered by the scope of the present invention.

Claims

1. The utility model provides a recovery structure of carrier rocket radome fairing, includes half cover of radome fairing (1), its characterized in that, two mounting panel (6) of keeping away from mutually of the equal fixed connection in both sides that half cover of radome fairing (1) kept away from mutually, two one side that mounting panel (6) are close to mutually rotates and is connected with same first pivot (7), the fixed cover of outer wall of first pivot (7) is equipped with resistance plate (8), the inside of half cover of radome fairing (1) is provided with makes two first pivot (7) pivoted drive assembly, one of them one side of mounting panel (6) is provided with makes first pivot (7) spacing subassembly.

2. The recovery structure of carrier rocket fairing according to claim 1, wherein the driving assembly comprises a driving groove (4) formed in the interior of the fairing half-cover (1), a motor (11) is fixedly connected to the inner wall of one side of the driving groove (4), a second rotating shaft (12) is fixedly connected to the output shaft of the motor (11), two steel wire ropes (13) are wound on the outer wall of the second rotating shaft (12), and the ends of the two steel wire ropes (13) far away from each other all penetrate through the fairing half-cover (1) and are fixedly connected with the outer walls of the two first rotating shafts (7) respectively.

3. The recovery structure of a fairing of a launch vehicle according to claim 1, wherein the limiting component comprises a positioning plate (15) fixedly connected to one side of the mounting plate (6), a positioning slot (16) is formed on one side of the positioning plate (15), two sliding slots (17) respectively located at two sides of the positioning slot (16) are formed inside the positioning plate (15), a sliding plate (18) is slidably connected to an inner wall of the sliding slot (17), a second spring (19) is fixedly connected to one end of the sliding plate (18), the other end of the second spring (19) is fixedly connected to an inner wall of one side of the sliding slot (17), one ends of the two sliding plates (18) close to each other extend into the positioning slot (16) and are provided with arc edges, a limiting plate (10) is fixedly connected to an outer wall of the first rotating shaft (7), and two sides of the limiting plate (10) far away from each other are respectively provided with a limiting slot matched with the two sliding plates (18) (14).

4. A launch vehicle fairing recovery structure as recited in claim 1, characterised in that said fairing halves (1) are fixedly connected at their base with first springs (2), said first springs (2) being fixedly connected at their base with a base plate (3).

5. A recovery structure for fairing of a launch vehicle according to claim 1 characterised in that the bottom of said fairing half (1) is fixedly connected with an elastic frame (5), the bottom of said elastic frame (5) being fixedly connected with the outer wall of the base plate (3).

6. The recovery structure of carrier rocket fairing according to claim 1, wherein the outer wall of the first rotating shaft (7) is sleeved with a torsion spring (9), and two ends of the torsion spring (9) are respectively fixedly connected with one side of the mounting plate (6) and the outer wall of the first rotating shaft (7).