CN115325889B - Leaf surface rotating grid rudder control system - Google Patents
Leaf surface rotating grid rudder control system Download PDFInfo
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- CN115325889B CN115325889B CN202211064263.XA CN202211064263A CN115325889B CN 115325889 B CN115325889 B CN 115325889B CN 202211064263 A CN202211064263 A CN 202211064263A CN 115325889 B CN115325889 B CN 115325889B
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- rudder piece
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
Abstract
The application provides a blade surface rotating grid rudder control system, which comprises two blade surface rotating grid rudders symmetrically arranged at two sides of a rocket; the blade surface rotating grid rudder comprises a fixed frame, rudder pieces and a rudder piece angle adjusting mechanism; the fixed frame is fixed on the side wall of the rocket recovery section; the rudder piece is rotationally connected in the fixed frame; the rudder piece angle adjusting mechanism is connected to the fixed frame and connected with the rudder piece; the rudder piece angle adjusting mechanism is used for adjusting the rotating angle of the rudder piece in the fixed frame. The application increases the angle adjusting range of the grid rudder, precisely recovers the rocket recovery section and reduces the structural quality.
Description
Technical Field
The application relates to the technical field of rocket recovery, in particular to a blade surface rotating grid rudder control system.
Background
The grid rudder is a rocket flight attitude control device, plays an important role in a rocket recovery accurate landing zone, and can control the attitude during recovery through the grid rudder so as to ensure that rocket debris can fall in a set area. The grid rudder of the rocket utilizes the principle of aerodynamic characteristics, and the rocket debris is guided to fly towards a target point through the thrust with different sizes and different directions generated by the wind acting on the control surface. Wherein, factors such as the control surface size, the grid number and the thickness of the grid rudder affect the aerodynamic characteristics of the grid rudder. As shown in fig. 1, the grid rudder in the prior art has a mounting hole 1 and grid rudder blades 2, and the grid rudder blades 2 are fixed and cannot adjust the angle thereof. The fixed control pin is connected in the mounting hole 1, the grid rudder is connected to the outer wall of the rocket through the fixed control pin, the fixed control pin is connected with the stepping motor, the angle of the current rocket body grid rudder is adjusted under the action of the stepping motor, and the angle of the grid rudder is limited when the direction is adjusted due to the limited total adjustment angle of the grid rudder.
Currently, the grille rudder has the following defects:
1. at present, a grid rudder is used, the rotating angle cannot be accurately controlled by the structure, and the rocket recovery section cannot be accurately recovered.
2. The angle of the grille rudder is limited and the control angle is limited.
3. The arrow body needs a plurality of grid rudders to control, generally 4, and the number is large, and the structural quality is improved.
Therefore, the technical problems to be solved are: how to accurately recycle the rocket recycling section, the angle adjustment range of the grid rudder is increased, and the structural quality is reduced.
Disclosure of Invention
The application aims to provide a leaf surface rotating grid rudder control system which increases the angle adjustment range of a grid rudder, accurately recovers a rocket recovery section and reduces the structural quality.
In order to achieve the above purpose, the application provides a blade surface rotating grid rudder control system, which comprises two blade surface rotating grid rudders symmetrically arranged at two sides of a rocket; the blade surface rotating grid rudder comprises a fixed frame, rudder pieces and rudder piece angle adjusting mechanisms; the fixed frame is fixed on the side wall of the rocket recycling section; the rudder piece is rotationally connected in the fixed frame; the rudder blade angle adjusting mechanism is connected to the fixed frame and is connected with the rudder blade; the rudder blade angle adjusting mechanism is used for adjusting the rotation angle of the rudder blade in the fixed frame.
According to the blade surface rotating grid rudder control system, two ends of the rudder piece are rotatably connected to the fixed frame through the rotating shafts.
The blade surface rotating grid rudder control system comprises a transverse rudder piece and a longitudinal rudder piece; the rudder blade angle adjusting mechanism comprises a horizontal rudder blade angle adjusting mechanism and a vertical rudder blade angle adjusting mechanism; the transverse rudder piece and the longitudinal rudder piece are in cross connection in the fixed frame; the angle adjusting mechanism of the horizontal rudder piece is connected with the horizontal rudder piece; the longitudinal rudder blade angle adjusting mechanism is connected with the longitudinal rudder blade, and the transverse rudder blade angle adjusting mechanism is used for adjusting the rotation angle of the transverse rudder blade; the angle adjusting mechanism of the longitudinal rudder piece is used for adjusting the rotation angle of the longitudinal rudder piece.
The blade surface rotating grid rudder control system comprises a blade surface rotating grid rudder control system body, wherein the side edge of the transverse rudder piece is internally provided with a first V-shaped open slot, and the longitudinal rudder piece is perpendicular to the transverse rudder piece and limited in the first V-shaped open slot; the longitudinal rudder blade angle adjusting mechanism drives the longitudinal rudder blade to swing in the first V-shaped opening groove.
The blade surface rotating grid rudder control system comprises a blade surface rotating grid rudder control system body, wherein the side edge of the longitudinal rudder piece is provided with a second V-shaped open groove inwards; the transverse rudder piece is limited in the second V-shaped opening groove; the angle adjusting mechanism of the horizontal rudder piece drives the horizontal rudder piece to swing in the second V-shaped opening groove.
The blade surface rotating grid rudder control system comprises a plurality of transverse rudder pieces and longitudinal rudder pieces, wherein the transverse rudder pieces and the longitudinal rudder pieces are arranged in parallel at intervals; the plurality of longitudinal rudder pieces are arranged in parallel at intervals.
The blade surface rotating grid rudder control system, wherein the side edge of the transverse rudder piece is provided with a plurality of first V-shaped open grooves at intervals along the length direction; the side edges of the longitudinal rudder piece are provided with a plurality of second V-shaped open grooves at intervals along the length direction of the longitudinal rudder piece.
The blade surface rotating grid rudder control system comprises a transverse rudder piece angle adjusting mechanism, a first rudder piece connecting mechanism and a first push-pull driving mechanism, wherein the transverse rudder piece angle adjusting mechanism comprises a first rudder piece connecting mechanism and a first push-pull driving mechanism; the first rudder piece connecting mechanism is connected with the transverse rudder piece; the first push-pull driving mechanism is connected with the first rudder piece connecting mechanism and is used for providing push-pull force for the first rudder piece connecting mechanism so as to drive the first rudder piece connecting mechanism to move along the length direction; the first rudder piece connecting mechanism drives the transverse rudder piece to swing.
The blade surface rotating grid rudder control system comprises a longitudinal rudder piece angle adjusting mechanism, a first rudder piece connecting mechanism and a first push-pull driving mechanism, wherein the longitudinal rudder piece angle adjusting mechanism comprises a first rudder piece connecting mechanism and a first push-pull driving mechanism;
the second rudder piece connecting mechanism is connected with the transverse rudder piece;
the second push-pull driving mechanism is connected with the second rudder piece connecting mechanism and is used for providing push-pull force for the second rudder piece connecting mechanism so as to drive the second rudder piece connecting mechanism to move along the length direction;
the second rudder piece connecting mechanism drives the longitudinal rudder piece to swing.
The blade face rotating grid rudder control system as described above, wherein the first rudder piece connecting mechanism includes a link and a pivot connecting member; a plurality of pivot connecting parts are arranged on the connecting rod at intervals along the length direction of the connecting rod; each pivotal connection member is connected to one of the cross rudder pieces.
The beneficial effects achieved by the application are as follows:
(1) The grating rudder comprises the transverse rudder piece and the longitudinal rudder piece, the transverse rudder piece and the longitudinal rudder piece are arranged in a crossed and matched mode, the transverse rudder piece and the longitudinal rudder piece are precisely matched to rotate, the inclination angles of the transverse rudder piece and the longitudinal rudder piece can be precisely controlled, the range which can be swept by fluid flowing through the transverse rudder piece 4 and the longitudinal rudder piece 5 is 360 degrees, the adjustable range of the control angle of the grating rudder is increased, and the recovery precision of a rocket recovery section is improved.
(2) Compared with 4 grid rudders arranged on the side wall of the rocket recovery section in the prior art, the application reduces the number of the grid rudders, reduces the additional weight and saves the cost.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings may be obtained according to these drawings to those skilled in the art.
Fig. 1 is a schematic view of a grid rudder in the prior art.
Fig. 2 is a schematic structural diagram of a blade surface rotating grid rudder control system according to an embodiment of the present application.
Fig. 3 is a schematic structural view of a rudder blade angle adjusting mechanism according to an embodiment of the present application.
Fig. 4 is a schematic structural view of a first rudder blade connecting mechanism according to an embodiment of the present application.
Fig. 5 is a schematic structural diagram of a wobble block according to an embodiment of the present application.
Fig. 6 is a schematic structural diagram of a transmission mechanism according to an embodiment of the present application.
Fig. 7 is a schematic structural view of the embodiment of the present application, in which only the rudder sheet is installed.
Fig. 8 is a schematic structural view of a rudder sheet according to an embodiment of the present application.
Fig. 9 is a schematic structural view of the embodiment of the present application in which only the rudder sheet is installed.
Fig. 10 is a schematic view of an embodiment of the present application after swinging a rudder blade.
Fig. 11 is a schematic diagram of the embodiment of the application after swinging the horizontal rudder blade and the vertical rudder blade.
Fig. 12 is a schematic view illustrating a swing angle range of a rudder blade according to an embodiment of the present application.
FIG. 13 is a schematic view of a 360 degree rotation of a rudder in which fluid may sweep in a direction according to an embodiment of the present application.
Fig. 14 is a schematic view of a configuration of a blade-surface rotary grid rudder control system according to an embodiment of the present application mounted on a rocket.
Reference numerals: 1-mounting holes; 2-grid rudder blades; 3-fixing the frame; 4-arranging rudder pieces; 5-longitudinally arranging rudder pieces; 6-a rudder piece angle adjusting mechanism; 7-a rudder piece angle adjusting mechanism; 31-a fixing mechanism; 32-rotating shaft; 33-a first bezel; 34-a second bezel; 41-a first V-shaped open slot; 51-a second V-shaped open slot; 52-a concave groove; 61-a first rudder piece connecting mechanism; 62-a first push-pull drive mechanism; 71-a second rudder piece connecting mechanism; 72-a second push-pull drive mechanism; 611-a pivotal connection; 612-connecting rod; 621-controlling the motor; 622-a reduction mechanism; 623-a transmission; 6111—a connection frame; 6112-swinging block; 6113-connecting shaft; 6231-rack; 6232-gear; 6233-a reduction mechanism output shaft; 6234 guide rails; 61121-connecting holes.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
As shown in fig. 2, the application provides a blade surface rotating grid rudder control system, which comprises two blade surface rotating grid rudders symmetrically arranged at two sides of a rocket; the blade surface rotating grid rudder comprises a fixed frame 3, rudder pieces and a rudder piece angle adjusting mechanism; the fixed frame 3 is fixed on the side wall of the rocket recycling section through a fixing mechanism 31; the rudder piece is rotationally connected in the fixed frame 3; the rudder piece angle adjusting mechanism is connected to the fixed frame 3 and is connected with the rudder piece; the rudder piece angle adjusting mechanism is used for adjusting the rotating angle of the rudder piece in the fixed frame 3. The two ends of the rudder piece are rotatably connected to the fixed frame 3 through a rotating shaft 32. The rudder piece comprises a transverse rudder piece 4 and a longitudinal rudder piece 5; the rudder piece angle adjusting mechanism comprises a transverse rudder piece angle adjusting mechanism 6 and a longitudinal rudder piece angle adjusting mechanism 7; the transverse rudder piece 4 and the longitudinal rudder piece 5 are in cross connection in the fixed frame 3; the horizontal rudder piece angle adjusting mechanism 6 is connected with the horizontal rudder piece 4; the longitudinal rudder piece angle adjusting mechanism 7 is connected with the longitudinal rudder piece 5, and the transverse rudder piece angle adjusting mechanism 6 is used for adjusting the rotation angle of the transverse rudder piece 4; the rudder blade angle adjusting mechanism 7 is used for adjusting the rotation angle of the rudder blade 5. The horizontal rudder piece 4 and the vertical rudder piece 5 are precisely matched to rotate, the rudder piece angle of the grid rudder is precisely adjusted, the track recovered by the rocket recovery section is further enabled to accord with the track planned in advance, and the recovery precision of the rocket recovery section is improved.
As a specific embodiment of the present application, the fixing mechanism 31 is fixed to the side wall of the rocket recovery section by a fixing bolt, and there is no limitation on how the fixing mechanism 31 is fixed to the side wall of the rocket recovery section, and other fixing methods are also possible.
As shown in fig. 2, the fixed frame 3 is a quadrangular frame body; the rudder blade comprises two parallel first frames 33 and two parallel second frames 34 which are arranged at intervals, wherein the first frames 33 are perpendicular to the second frames 34, and a space for installing the transverse rudder blade 4 and the longitudinal rudder blade 5 is enclosed between the first frames 33 and the second frames 34.
As shown in fig. 2, the fixing mechanism 31 is fixedly connected to the first frame 33, the fixing mechanism 31 is vertically and fixedly connected to the outer wall of the rocket recovery section, and the fixing mechanism 31 is used for transmitting force between the grid rudder and the rocket recovery section, so as to realize attitude control of the rocket recovery section. The second rim 34 is perpendicular to the outer wall of the rocket recovery section. Two ends of the horizontal rudder piece 4 are respectively connected to two second frames 34 in a rotating way through a rotating shaft 32; both ends of the rudder piece 5 are rotatably connected to two first frames 33 through rotation shafts 32, respectively. When the rudder piece angle adjusting mechanism is pushed and pulled, the rudder piece rotates around the rotating shaft 32, so that the rudder piece angle adjustment is realized.
As shown in fig. 2, the horizontal rudder piece angle adjusting mechanism 6 is parallel to the second frame 34 and is arranged above the second frame 34, and the horizontal rudder piece angle adjusting mechanism 6 is used for connecting the horizontal rudder piece 4; the longitudinal rudder piece angle adjusting mechanism 7 is parallel to the first frame 33, is arranged below the first frame 33, and is used for connecting the longitudinal rudder piece 5.
As shown in fig. 2 and 9, a first V-shaped open groove 41 is formed inwards at the side edge of the horizontal rudder piece 4, and the vertical rudder piece 5 is perpendicular to the horizontal rudder piece 4 and is limited in the first V-shaped open groove 41; the rudder piece angle adjusting mechanism 7 drives the rudder piece 5 to swing in the first V-shaped open groove 41. Preferably, the opening angle of the first V-shaped opening groove 41 is 60 degrees, so that the swinging angle range of the longitudinal rudder piece 5 is limited to 60 degrees, and the swinging angle of the longitudinal rudder piece 5 is accurately controlled by the longitudinal rudder piece angle adjusting mechanism 7.
As shown in fig. 2, 7 and 8, the side edge of the rudder piece 5 is provided with a second V-shaped open groove 51 inwards; the transverse rudder piece 4 is limited in the second V-shaped opening groove 51; the horizontal rudder piece angle adjusting mechanism 6 drives the horizontal rudder piece 4 to swing in the second V-shaped opening groove 51. Preferably, the opening angle of the second V-shaped opening groove 51 is 60 degrees, so that the swinging angle range of the horizontal rudder piece 4 is limited to 60 degrees, and the swinging angle of the horizontal rudder piece 4 is accurately controlled through the horizontal rudder piece angle adjusting mechanism 6.
As shown in fig. 7 and 9, the first V-shaped open groove 41 is opened downward, and the second V-shaped open groove 51 is opened upward, thereby realizing the butt joint of the first V-shaped open groove 41 and the second V-shaped open groove 51.
As shown in fig. 8, the bottom of the second V-shaped open groove 51 is provided with a concave groove 52, and the concave groove 52 at the bottom of the second V-shaped open groove 51 is used for clamping the rudder blade 4. Similarly, the bottom of the first V-shaped open groove 41 is also provided with a concave groove 52, and the concave groove 52 at the bottom of the first V-shaped open groove 41 is used for clamping the rudder blade 5. Preferably, the concave groove 52 at the bottom of the first V-shaped open groove 41 is butted with the concave groove 52 at the bottom of the second V-shaped open groove 51, so as to realize compact matching connection of the transverse rudder piece 4 and the longitudinal rudder piece 5.
As a specific embodiment of the application, the transverse rudder piece 4 and the longitudinal rudder piece 5 comprise a plurality of transverse rudder pieces 4 which are arranged in parallel and at intervals; the plurality of rudder pieces 5 are arranged in parallel at a distance. The longitudinal rudder pieces 5 and the longitudinal rudder pieces 5 are arranged in a crossing manner, the inclination angles of the longitudinal rudder pieces 5 and the longitudinal rudder pieces 5 can be adjusted, so that the fluid direction flowing through the longitudinal rudder pieces 5 and the longitudinal rudder pieces 5 is adjusted, the recovery direction of a rocket recovery section is changed, and the recovery of the rocket recovery section is accurately controlled.
As a specific embodiment of the present application, the side edges of the rudder piece 4 are provided with a plurality of first V-shaped open grooves 41 spaced apart in the length direction thereof; the side edges of the longitudinal rudder piece 5 are provided with a plurality of second V-shaped open grooves 51 at intervals along the length direction, each first V-shaped open groove 41 is matched and butted with one second V-shaped open groove 51, the limitation of the angle range of the transverse rudder piece 4 and the longitudinal rudder piece 5 is better realized, and the angle adjustment precision of the transverse rudder piece 4 and the longitudinal rudder piece 5 is improved.
As shown in fig. 3, the horizontal rudder piece angle adjusting mechanism 6 includes a first rudder piece connecting mechanism 61 and a first push-pull driving mechanism 62; the first rudder piece connecting mechanism 61 is connected with the transverse rudder piece 4; the first push-pull driving mechanism 62 is connected to the first rudder piece connecting mechanism 61 and is used for providing a push-pull force for the first rudder piece connecting mechanism 61 so as to drive the first rudder piece connecting mechanism 61 to move along the length direction thereof; the first rudder piece connecting mechanism 61 drives the transverse rudder piece 4 to swing.
As shown in fig. 3, the rudder blade angle adjusting mechanism 7 includes a second rudder blade connecting mechanism 71 and a second push-pull driving mechanism 72.
As shown in fig. 2 and 3, the second rudder piece connecting mechanism 71 is connected with the rudder piece 5; the second push-pull driving mechanism 72 is connected with the second rudder piece connecting mechanism 71 and is used for providing push-pull force for the second rudder piece connecting mechanism 71 so as to drive the second rudder piece connecting mechanism 71 to move along the length direction thereof; the second rudder piece connecting mechanism 71 drives the longitudinal rudder piece 5 to swing.
As shown in fig. 3, the first rudder piece connection mechanism 61 includes a link 612 and a pivot connection member 611; the link 612 is provided with a plurality of pivotal connection members 611 at intervals along the length direction thereof; a transverse rudder piece 4 is connected to each pivot connection 611. The end of the first rudder piece connecting mechanism 61 connected with the first push-pull driving mechanism 62 is a connecting rod 612, so that the first push-pull driving mechanism 62 can conveniently push and pull the first rudder piece connecting mechanism 61 through the connecting rod 612.
As a specific embodiment of the present application, the second rudder blade connecting mechanism 71 has the same structure as the first rudder blade connecting mechanism 61. The application connects a plurality of pivoting connecting parts 611 through the connecting rod 612, each pivoting connecting part 611 is respectively connected with one transverse rudder piece 4, so that the connection of a plurality of transverse rudder pieces 4 together is realized, a hinge is formed, linkage is formed, the swinging angles of the plurality of transverse rudder pieces 4 can be integrally adjusted through the first rudder piece connecting mechanism 61, and the swinging angles of the plurality of transverse rudder pieces 4 are consistent.
As shown in fig. 3-5, the pivot connection part 611 in the first rudder blade connecting mechanism 61 includes a connection frame 6111, a swinging block 6112, and a connection shaft 6113; the swinging block 6112 is provided with a connecting hole 61121; the connecting frame 6111 is fixedly connected with the connecting rod 612, the connecting shaft 6113 is fixedly connected on the connecting frame 6111, the connecting shaft 6113 penetrates into a connecting hole 61121 of the swinging block 6112, the swinging block 6112 is rotatably connected on the connecting shaft 6113, and the bottom of the swinging block 6112 is fixedly connected with the transverse rudder piece 4. The link 612 realizes the function of pulling or pushing the pivotal connection member 611 to move along the length direction of the link 612 under the push-pull force of the first push-pull driving mechanism 62, the force of the link 612 pulling (or pushing) the pivotal connection member 611 acts on the connection frame 6111, and the link 612 pulls (or pushes) the connection frame 6111 to move; because the bottom of the swinging block 6112 is fixedly connected with the horizontal rudder piece 4, and the horizontal rudder piece 4 is rotationally connected to the fixed frame 3, after the connecting frame 6111 moves, the connecting shaft 6113 is driven to move, and the swinging block 6112 swings for a certain angle under the pulling action of the connecting shaft 6113, so that the horizontal rudder piece 4 is driven to swing for a certain angle.
As shown in fig. 5, the connection hole 61121 of the swing block 6112 is long, or the connection hole 61121 is long; when the swing block 6112 swings, the connecting shaft 6113 can slide in the long-strip-shaped connecting hole 61121, so that the transverse rudder piece 4 swings smoothly.
As a specific embodiment of the present application, the bottom of the swinging block 6112 in the second rudder blade connecting mechanism 71 is fixedly connected with the longitudinal rudder blade 5.
As shown in fig. 3 and 6, the first push-pull driving mechanism 62 includes a control motor 621, a reduction mechanism 622, and a transmission mechanism 623; an output shaft of the control motor 621 is connected with an input shaft of the reduction mechanism 622; an output shaft of the speed reduction mechanism 622 is connected with an input shaft of the transmission mechanism 623; the transmission mechanism 623 is connected with the connecting rod 612, and the reduction mechanism 622 is used for reducing the rotation speed output by the control motor 621; the transmission mechanism 623 is used to convert the rotation of the control motor 621 into linear motion of the link 612.
Preferably, the control motor 621 is a stepping motor, and realizes speed reduction under the action of the speed reduction mechanism 622, and converts the torque of the stepping motor into the push-pull force of the connecting mechanism, so as to realize control of the rudder piece.
As shown in fig. 6, the transmission mechanism 623 is a rack and pinion mechanism, which precisely adjusts the moving distance of the link 612, thereby precisely adjusting the swing angle of the rudder blade. The transmission mechanism 623 includes a gear 6232 and a rack 6231 in meshed connection. The rack 6231 is slidingly connected to the guide rail 6234; the guide rail 6234 is fixed on the fixed frame 3; rack 6231 is fixedly connected to link 612. A reduction mechanism output shaft 6233 is connected to the gear 6232; the motor 621 is controlled to rotate to drive the speed reducing mechanism 622 to rotate, the speed reducing mechanism 622 drives the gear 6232 to rotate, and the gear 6232 drives the rack 6231 to linearly move along the length direction; the rack 6231 drives the link 612 to move linearly along its length, and the link 612 drives the pivotal connection member 611 to move.
As other embodiments of the present application, the first push-pull driving mechanism 62 and the second push-pull driving mechanism 72 may be other mechanisms capable of providing push-pull force to the link 612, such as a cylinder driving mechanism or a cylinder driving mechanism. Here, the structure of the first push-pull driving mechanism 62 and the second push-pull driving mechanism 72 is not limited, and other mechanisms capable of providing a push-pull force to the link 612 may be used.
As shown in fig. 10, the rudder blade 5 is shown in a state of being swung alone. The swing angles of the plurality of longitudinal rudder pieces 5 are consistent, fluid flows along the leaf surfaces of the longitudinal rudder pieces 5, and after the longitudinal rudder pieces 5 swing, the direction of the fluid flowing through the longitudinal rudder pieces 5 is regulated, so that the recovery direction of the rocket recovery section is regulated.
As shown in fig. 11, the longitudinal rudder blade 5 and the transverse rudder blade 4 are both swung. Through the swinging of the two groups of rudder pieces, namely the longitudinal rudder piece 5 and the transverse rudder piece 4, the direction adjustable range of fluid passing through the grid rudder is improved, and further, the recovery precision of the rocket recovery section is improved.
As shown in fig. 12, the swing angle ranges of the rudder blade 4 are all 60 degrees. As a specific embodiment of the present application, the swing angle ranges of the horizontal rudder blade 4 and the vertical rudder blade 5 are both 60 degrees. The two blades of the horizontal rudder piece 4 and the vertical rudder piece 5 are precisely matched to rotate, and 360-degree rotation control can be realized.
As shown in fig. 13, after the two blades of the horizontal rudder piece 4 and the vertical rudder piece 5 are precisely matched to rotate, the fluid flowing through the horizontal rudder piece 4 and the vertical rudder piece 5 can sweep 360 degrees, so that the adjustable range of the control angle of the grid rudder is increased, and the recovery precision of the rocket recovery section is improved.
As shown in fig. 14, two blade surface rotating grid rudders are symmetrically arranged on two sides of the rocket, the fixed frame 3 is perpendicular to the side wall of the rocket recovery section, and in the rocket launching flight and recovery process, the air flow direction flowing through the transverse rudder piece 4 and the longitudinal rudder piece 5 can be changed by adjusting the inclination angles of the transverse rudder piece 4 and the longitudinal rudder piece 5, so that the flight direction of the rocket is changed, the accurate rocket flight is realized, and the recovery precision of the rocket recovery section is improved.
The beneficial effects achieved by the application are as follows:
(1) The grating rudder comprises the transverse rudder piece and the longitudinal rudder piece, the transverse rudder piece and the longitudinal rudder piece are arranged in a crossed and matched mode, the transverse rudder piece and the longitudinal rudder piece are precisely matched to rotate, the inclination angles of the transverse rudder piece and the longitudinal rudder piece can be precisely controlled, the range which can be swept by fluid flowing through the transverse rudder piece 4 and the longitudinal rudder piece 5 is 360 degrees, the adjustable range of the control angle of the grating rudder is increased, and the recovery precision of a rocket recovery section is improved.
(2) Compared with 4 grid rudders arranged on the side wall of the rocket recovery section in the prior art, the application reduces the number of the grid rudders, reduces the additional weight of the rocket, and saves the cost.
The foregoing description is only illustrative of the application and is not to be construed as limiting the application. Various modifications and variations of the present application will be apparent to those skilled in the art. Any modifications, equivalent substitutions, improvements, etc. which are within the spirit and principles of the present application are intended to be included within the scope of the claims of the present application.
Claims (8)
1. The blade surface rotating grid rudder control system is characterized by comprising two blade surface rotating grid rudders symmetrically arranged at two sides of a rocket; the blade surface rotating grid rudder comprises a fixed frame, rudder pieces and rudder piece angle adjusting mechanisms;
the fixed frame is fixed on the side wall of the rocket recycling section;
the rudder piece is rotationally connected in the fixed frame;
the rudder blade angle adjusting mechanism is connected to the fixed frame and is connected with the rudder blade; the rudder blade angle adjusting mechanism is used for adjusting the rotation angle of the rudder blade in the fixed frame;
the two ends of the rudder piece are rotationally connected to the fixed frame through a rotating shaft;
the rudder piece comprises a transverse rudder piece and a longitudinal rudder piece; the rudder blade angle adjusting mechanism comprises a horizontal rudder blade angle adjusting mechanism and a vertical rudder blade angle adjusting mechanism;
the transverse rudder piece and the longitudinal rudder piece are in cross connection in the fixed frame;
the angle adjusting mechanism of the horizontal rudder piece is connected with the horizontal rudder piece; the longitudinal rudder blade angle adjusting mechanism is connected with the longitudinal rudder blade, and the transverse rudder blade angle adjusting mechanism is used for adjusting the rotation angle of the transverse rudder blade; the angle adjusting mechanism of the longitudinal rudder piece is used for adjusting the rotation angle of the longitudinal rudder piece.
2. The blade surface rotating grid rudder control system according to claim 1, wherein a first V-shaped open groove is formed in the side edge of the horizontal rudder piece inwards, and the vertical rudder piece is perpendicular to the horizontal rudder piece and limited in the first V-shaped open groove; the longitudinal rudder blade angle adjusting mechanism drives the longitudinal rudder blade to swing in the first V-shaped opening groove.
3. The blade surface rotating grid rudder control system according to claim 2, wherein the side edge of the longitudinal rudder piece is provided with a second V-shaped open groove inwards; the transverse rudder piece is limited in the second V-shaped opening groove; the angle adjusting mechanism of the horizontal rudder piece drives the horizontal rudder piece to swing in the second V-shaped opening groove.
4. The foliar rotary grid rudder control system of claim 3 wherein the cross rudder sheet and the longitudinal rudder sheet each include a plurality of the cross rudder sheets, the plurality of the cross rudder sheets being disposed in parallel spaced apart relation; the plurality of longitudinal rudder pieces are arranged in parallel at intervals.
5. The blade face rotating grid rudder control system according to claim 3, wherein the side edges of the horizontal rudder piece are provided with a plurality of the first V-shaped open grooves at intervals along the length direction thereof; the side edges of the longitudinal rudder piece are provided with a plurality of second V-shaped open grooves at intervals along the length direction of the longitudinal rudder piece.
6. The blade face rotating grid rudder control system of claim 3, wherein the lateral rudder blade angle adjustment mechanism comprises a first rudder blade connection mechanism and a first push-pull drive mechanism;
the first rudder piece connecting mechanism is connected with the transverse rudder piece;
the first push-pull driving mechanism is connected with the first rudder piece connecting mechanism and is used for providing push-pull force for the first rudder piece connecting mechanism so as to drive the first rudder piece connecting mechanism to move along the length direction;
the first rudder piece connecting mechanism drives the transverse rudder piece to swing.
7. The blade face rotating grid rudder control system according to claim 3, wherein the rudder blade angle adjusting mechanism includes a second rudder blade connecting mechanism and a second push-pull driving mechanism;
the second rudder piece connecting mechanism is connected with the transverse rudder piece;
the second push-pull driving mechanism is connected with the second rudder piece connecting mechanism and is used for providing push-pull force for the second rudder piece connecting mechanism so as to drive the second rudder piece connecting mechanism to move along the length direction;
the second rudder piece connecting mechanism drives the longitudinal rudder piece to swing.
8. The foliar rotary grid rudder control system of claim 6, wherein the first rudder blade connection mechanism includes a link and a pivot connection member;
a plurality of pivot connecting parts are arranged on the connecting rod at intervals along the length direction of the connecting rod;
each pivotal connection member is connected to one of the cross rudder pieces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211064263.XA CN115325889B (en) | 2022-09-01 | 2022-09-01 | Leaf surface rotating grid rudder control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211064263.XA CN115325889B (en) | 2022-09-01 | 2022-09-01 | Leaf surface rotating grid rudder control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115325889A CN115325889A (en) | 2022-11-11 |
| CN115325889B true CN115325889B (en) | 2023-09-29 |
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| CN115325889A (en) | 2022-11-11 |
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