CN115108054A - Lightweight air rudder for rocket - Google Patents
Lightweight air rudder for rocket Download PDFInfo
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- CN115108054A CN115108054A CN202210978588.2A CN202210978588A CN115108054A CN 115108054 A CN115108054 A CN 115108054A CN 202210978588 A CN202210978588 A CN 202210978588A CN 115108054 A CN115108054 A CN 115108054A
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 103
- 238000005728 strengthening Methods 0.000 claims description 14
- 235000015842 Hesperis Nutrition 0.000 claims description 9
- 235000012633 Iberis amara Nutrition 0.000 claims description 9
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 230000002349 favourable effect Effects 0.000 abstract description 4
- 239000003351 stiffener Substances 0.000 description 6
- 239000011324 bead Substances 0.000 description 4
- 239000000956 alloy Substances 0.000 description 3
- 230000001737 promoting effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011056 performance test Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 230000014509 gene expression Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
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Abstract
The application provides a lightweight air rudder for a rocket, which comprises a rudder body, wherein the rudder body comprises an upper rudder plate, a lower rudder plate and a connecting frame; the connecting frame comprises a first side edge, a second side edge, a third side edge and a fourth side edge which are sequentially connected end to end; the first side edge and the third side edge are parallel to each other and are respectively perpendicular to the second side edge; the length of the first side edge is less than that of the fourth side edge; the third side edge is sunken towards the direction of the first side edge to form a groove; the reinforcing rib group comprises a first reinforcing rib, a second reinforcing rib and a third reinforcing rib; one end of the first reinforcing rib is connected with the second side edge, and the other end of the first reinforcing rib is connected with the bottom edge of the groove; one end of the second reinforcing rib is connected with the first side edge, and the other end of the second reinforcing rib is connected with the bottom edge of the groove; one end of the third reinforcing rib is connected with the fourth side edge, and the other end of the third reinforcing rib is connected with the bottom edge of the groove. The light-weight air rudder for the rocket not only meets the requirement of light weight, but also meets the requirement of high rigidity and strength, and is favorable for improving the carrying capacity of the rocket.
Description
Technical Field
The application relates to the technical field of rockets, in particular to a lightweight air rudder for a rocket.
Background
The air rudder is a structure for controlling the flying attitude of the rocket, is usually arranged outside the tail section of the rocket body, and bears large pneumatic load and generates certain control force when in use.
Grid formula structure is adopted usually to the inside of traditional air vane structure, strengthening rib through grid formula structure promotes rigid strength, but hardly find a balance point between rigid strength and quality, when the number that forms grid formula structure's strengthening rib is too much promptly, air vane structure's quality is often great, when the number that forms grid formula structure's strengthening rib is less, air vane structure's rigidity is often less, this just makes traditional air vane structure hardly balance between rigid strength and quality, traditional air vane structure is unfavorable for rocket carrying capacity's promotion, for this reason, this application provides a lightweight air vane for the rocket.
Disclosure of Invention
The present application aims to solve the above problems and provide a lightweight air vane for a rocket.
The application provides a lightweight air vane for rocket includes:
the rudder body comprises an upper rudder plate, a lower rudder plate and a connecting frame connected between the upper rudder plate and the lower rudder plate; the connecting frame comprises a first side edge, a second side edge, a third side edge and a fourth side edge which are sequentially connected end to end; the first side edge and the third side edge are parallel to each other and are respectively perpendicular to the second side edge; the length of the first side edge is smaller than that of the fourth side edge; the third side edge is sunken towards the direction of the first side edge to form a groove;
the reinforcing rib group comprises a first reinforcing rib, a second reinforcing rib and a third reinforcing rib; one end of the first reinforcing rib is connected with the second side edge, and the other end of the first reinforcing rib is connected with the bottom edge of the groove; one end of the second reinforcing rib is connected with the first side edge, and the other end of the second reinforcing rib is connected with the bottom edge of the groove; one end of the third reinforcing rib is connected with the fourth side edge, and the other end of the third reinforcing rib is connected with the bottom edge of the groove.
According to the technical scheme provided by some embodiments of the present application, one end of the first reinforcing rib is connected to one third of the second side edge near the third side edge, and the other end of the first reinforcing rib is connected to the end of the bottom edge of the groove near the second side edge; one end of the second reinforcing rib is connected to the middle of the first side edge, and the other end of the second reinforcing rib is connected to the middle of the bottom edge of the groove; one end of the third reinforcing rib is connected to the middle of the fourth side edge, and the other end of the third reinforcing rib is connected to the end portion, close to the fourth side edge, of the bottom edge of the groove.
According to the technical scheme provided by some embodiments of the present application, the thickness of the third reinforcing rib is larger than the thicknesses of the first reinforcing rib and the second reinforcing rib.
According to the technical scheme provided by some embodiments of the application, at least one lightening hole is formed in the third reinforcing rib.
According to the technical scheme provided by some embodiments of the application, the third reinforcing rib is provided with two lightening holes; the two lightening holes are distributed along the length direction of the third reinforcing rib.
According to the technical scheme provided by some embodiments of the present application, the reinforcing rib group further includes a fourth reinforcing rib; the fourth reinforcing rib is arranged in an area surrounded by the third reinforcing rib, the fourth side edge, the third side edge and the side edge of the groove; one end of the fourth reinforcing rib is connected with the fourth side edge, and the other end of the fourth reinforcing rib is connected with the side edge of the groove.
According to the technical scheme provided by some embodiments of the application, the reinforcing rib group further comprises fifth reinforcing ribs; the fifth reinforcing ribs are arranged in an area surrounded by the first reinforcing ribs, the second side edges, the third side edges and the side edges of the grooves; one end of the fifth strengthening rib is connected with the second side edge, and the other end of the fifth strengthening rib is connected with the third side edge.
According to the technical scheme provided by some embodiments of the application, the rudder body and the reinforcing rib group are both made of aluminum alloy materials.
According to the technical scheme provided by some embodiments of the application, a mounting plate is fixedly arranged in the groove; a rudder shaft is arranged on the mounting plate; the rudder shaft comprises a clamping part fixed with the mounting plate and a connecting part fixedly connected with the clamping part; the connecting part is used for being connected with the rocket body.
Compared with the prior art, the beneficial effect of this application: this lightweight air rudder for rocket has adopted less rib on the one hand for it has the light characteristics of quality, and on the other hand, three ribs are the form of dispersing and distribute, and it is dispersed to the outside from the recess bottom, makes this air rudder have better rigidity intensity, and the air rudder that this application provided promptly had both satisfied the light requirement of quality, satisfied the big requirement of rigidity intensity again, also found the balance between rigidity intensity and quality promptly, was favorable to promoting the carrying capacity of rocket.
According to some embodiments of the application, the connecting positions of the three reinforcing ribs are designed, the inside of the connecting frame is divided into four areas, the areas of the three areas are approximately equal, the area of the area surrounded by the lower bottom and the height of the right trapezoid is slightly smaller, the uniformity of the integral rigidity of the air rudder is guaranteed, meanwhile, the rigidity of the root of the air rudder is increased by increasing the rigidity strength of the first reinforcing rib, and the actual requirement that the rigidity of the lower portion of the air rudder is relatively larger in practical application is met.
Drawings
Fig. 1 is a schematic structural view of a lightweight air rudder for rockets provided in an embodiment of the present application;
fig. 2 is a schematic structural diagram of a lower rudder plate of a lightweight air rudder for rockets according to an embodiment of the present application;
fig. 3 is a schematic structural diagram of a reinforcing rib group of a lightweight air rudder for a rocket according to an embodiment of the present application;
fig. 4 is a schematic structural view of a rudder shaft of a lightweight air rudder for a rocket according to an embodiment of the present application.
The text labels in the figures are represented as:
1. a rudder body; 101. an upper rudder plate; 102. a lower rudder plate; 103. a first side edge; 104. a second side edge; 105. a third side; 106. a fourth side; 107. mounting a plate;
201. a first reinforcing rib; 202. a second reinforcing rib; 203. a third reinforcing rib; 204. lightening holes; 205. a fourth reinforcing rib; 206. fifthly, strengthening the tendons;
3. a rudder shaft; 301. a clamping portion; 302. a connecting portion.
Detailed Description
The following detailed description of the present application is given for the purpose of enabling those skilled in the art to better understand the technical solutions of the present application, and the description in this section is only exemplary and explanatory, and should not be taken as limiting the scope of the present application in any way.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined or explained in subsequent figures.
Referring to fig. 1 to 3, the present embodiment provides a lightweight air rudder for a rocket, including:
the rudder body 1 comprises an upper rudder plate 101, a lower rudder plate 102 and a connecting frame connected between the upper rudder plate 101 and the lower rudder plate 102; the connecting frame comprises a first side edge 103, a second side edge 104, a third side edge 105 and a fourth side edge 106 which are sequentially connected end to end; the first side 103 and the third side 105 are parallel to each other and perpendicular to the second side 104; the length of the first side 103 is less than the length of the fourth side 106; the third side 105 is recessed toward the first side 103 to form a groove;
a set of ribs comprising a first rib 201, a second rib 202 and a third rib 203; one end of the first reinforcing rib 201 is connected with the second side edge 104, and the other end is connected with the bottom edge of the groove; one end of the second reinforcing rib 202 is connected with the first side edge 103, and the other end is connected with the bottom edge of the groove; one end of the third rib 203 is connected to the fourth side 106, and the other end is connected to the bottom side of the groove.
Specifically, the outer contour of the upper rudder plate 101 is a right trapezoid, a rectangular notch is formed in the middle of the bottom edge of the upper rudder plate, and the outer contour of the connecting frame is also a right trapezoid; the upper rudder plate 101 and the connecting frame are fixedly connected, and can be welded or integrally formed; the structural shape of the lower rudder plate 102 is the same as that of the upper rudder plate 101, and the lower rudder plate 102 is fixedly connected with the connecting frame through screws; the first reinforcing rib 201, the second reinforcing rib 202 and the third reinforcing rib 203 are three main ribs; the middle part of the second reinforcing rib 202 is relatively thick, and a threaded hole for fixedly connecting with the lower rudder plate 102 is formed in the middle part; the first side 103 is the upper bottom of the right trapezoid, the second side 104 is the height of the right trapezoid, the third side 105 is the lower bottom of the right trapezoid, and the fourth side 106 is the waist of the right trapezoid; the reinforcing rib group is arranged in an inner space surrounded by the outer contour of the connecting frame and comprises a first reinforcing rib 201, a second reinforcing rib 202 and a third reinforcing rib 203, one end of each of the three reinforcing ribs is connected to the bottom edge of the corresponding groove, and the other end of each of the three reinforcing ribs is connected to the first side edge 103, the second side edge 104 and the fourth side edge 106 respectively.
This air vane structure has adopted less rib on the one hand for it has the light characteristics of quality, and on the other hand, three ribs are the form distribution of dispersing, and it is dispersed to the outside from the recess bottom, makes this air vane have better rigidity intensity, and the air vane that this application provided promptly has both satisfied the light requirement of quality, satisfies the big requirement of rigidity intensity again, also has found the balance between rigidity intensity and quality promptly, is favorable to promoting the carrying capacity of rocket.
Further, one end of the first reinforcing rib 201 is connected to one third of the end of the second side edge 104 close to the third side edge 105, and the other end is connected to the end of the bottom edge of the groove close to the second side edge 104; one end of the second reinforcing rib 202 is connected to the middle of the first side edge 103, and the other end is connected to the middle of the bottom edge of the groove; one end of the third rib 203 is connected to the middle of the fourth side 106, and the other end is connected to the end of the bottom edge of the groove close to the fourth side 106.
Specifically, the three ribs 201, the second rib 202 and the third rib 203 divide the internal space enclosed by the outer contour of the connecting frame into four regions, in order to ensure uniformity of the overall rigidity, three of the four regions have substantially the same area, the other region has a slightly smaller area than the other region, and the region having the smallest area is the region enclosed by the first rib 201, the second side 104, the third side 105 and the right side of the groove, the reason for adopting the above structure is to make the first rib 201 have higher rigidity strength, that is, the length of the first rib 201 is shortened to make the first rib have higher rigidity strength, that is, the end far away from the groove is connected to one third of the second side 104 near the third side 105, so the rigidity strength of the first rib 201 is reinforced, in practical application, the upper part of the air rudder bears smaller load and stress, the lower part of the air rudder bears larger load and stress, and the rigidity of the lower part of the air rudder needs to be stronger according to the principle of an equal stress beam, so that the purpose is achieved by designing the connecting position of the first reinforcing rib 201.
Further, the thickness of the third reinforcing bead 203 is greater than the thickness of the first reinforcing bead 201 and the second reinforcing bead 202.
Specifically, the thickness of the rib refers to the thickness of the rib, because the fourth side 106 is the main windward side of the air vane structure, and the third rib 203 is the main rib at the main windward position, the thickness of the rib is larger than the thickness of the other main ribs.
Further, in order to increase the rigidity of the third reinforcing rib 203 and ensure that the mass of the third reinforcing rib is not too large, the third reinforcing rib is designed to be thicker at two ends and thinner at the middle, that is, the connecting area between the fourth side 106 and the bottom edge of the groove is relatively larger.
Further, at least one lightening hole 204 is formed on the third reinforcing rib 203.
In this embodiment, the third reinforcing rib 203 is provided with two weight-reducing holes 204; a threaded hole for fixedly connecting with the lower rudder plate 102 is formed at the joint of the two lightening holes 204; the two lightening holes 204 are distributed along the length direction of the third reinforcing rib 203, so that the third reinforcing rib 203 adopts a bifurcated structure according to a neuron form, the rigidity and the strength of the third reinforcing rib 203 are enhanced, and the sufficient light weight is ensured.
Further, the reinforcing rib group further comprises a fourth reinforcing rib 205; the fourth reinforcing ribs 205 are arranged in the area surrounded by the third reinforcing ribs 203, the fourth side 106, the third side 105 and the side of the groove; one end of the fourth reinforcing bead 205 is connected to the fourth side 106, and the other end is connected to the side of the groove.
Considering that the bottom of the air rudder is subjected to larger load and stress, and therefore the rigidity of the bottom needs to be strengthened, in this embodiment, to further increase the stability, a fourth rib 205 is provided, where the fourth rib 205 is an auxiliary rib, and divides the region enclosed by the third rib 203, the fourth side 106, the third side 105, and the groove side into two parts, and the division principle is a middle division principle, that is, the fourth rib 205 divides the region into two parts with approximately equal areas, and one end of the part is connected to the middle of the groove side, and the other end of the part is connected to approximately one fourth of the end of the fourth side 106 close to the third side 105.
Further, the rib group further includes fifth reinforcing ribs 206; the fifth reinforcing rib 206 is disposed in an area surrounded by the first reinforcing rib 201, the second side 104, the third side 105, and the side of the groove; one end of the fifth strengthening rib 206 is connected to the second side edge 104, and the other end is connected to the third side edge 105.
Considering that the bottom of the air rudder is subjected to a larger load and a larger stress, and therefore, the rigidity of the bottom needs to be emphasized, in the present embodiment, in order to further increase the stability, a fifth strengthening rib 206 is provided, the fifth strengthening rib 206 is an auxiliary strengthening rib which divides an area enclosed by the first strengthening rib 201, the second side edge 104, the third side edge 105 and the groove side edge into two parts, the fifth strengthening rib 206 is connected to the two side edges perpendicular to each other, and each end is connected to a relative middle position of the corresponding side edge.
Further, the rudder body 1 and the stiffener group are made of an aluminum alloy material, specifically, the rudder body 1, the first stiffener 201, the second stiffener 202, the third stiffener 203, the fourth stiffener 205, and the fifth stiffener 206 are made of an aluminum alloy material.
Referring further to fig. 4, a mounting plate 107 is fixedly disposed in the groove; the mounting plate 107 is provided with a rudder shaft 3; the rudder shaft 3 includes a clamping portion 301 fixed to the mounting plate 107 and a connecting portion 302 fixedly connected to the clamping portion 301; the connecting portion 302 is used for connecting with an rocket body of a rocket.
Specifically, the cross section of the clamping portion 301 is U-shaped, a space for clamping the mounting plate 107 is formed inside the clamping portion, when the mounting plate is mounted, the mounting plate 107 is inserted into the U-shaped space, and the clamping portion 301 and the mounting plate 107 are fixedly connected through bolts.
Performance test
When a performance test experiment is carried out on the air rudder provided by the embodiment, aerodynamic load is applied to the outer surface of the air rudder to observe the overall deformation condition of the air rudder, the maximum deformation amount is used for representing the rigidity of the air rudder, the smaller the deformation amount is under a certain load condition, the higher the rigidity is, and the deformation amount mainly refers to the deformation of two vertex angles at the two ends of the upper bottom of the right trapezoid.
The design principle of this application air vane is: considering the carrying capacity of the rocket, the allowable maximum deformation amount is set to be 3mm, and under the constraint condition, the rib structure with the lightest overall mass is sought.
Through carrying out the capability test experiment, the air vane that this embodiment provided has reached the design requirement, has adopted the biggest reduction of less strengthening rib quantity promptly whole quality, and the maximum deformation control has been controlled within 3mm simultaneously.
The application provides a light-weight air rudder for rocket adopts special rib mode of laying, adopts less rib, has obtained higher rigidity intensity, has both satisfied the light requirement of quality promptly, satisfies the big requirement of rigidity intensity again, also finds the balance between rigidity intensity and quality promptly, is favorable to promoting the carrying capacity of rocket.
The principles and embodiments of the present application are explained herein using specific examples, which are provided only to help understand the method and the core idea of the present application. The foregoing is only a preferred embodiment of the present application, and it should be noted that there are no specific structures which are objectively limitless due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes can be made without departing from the principle of the present invention, and the technical features mentioned above can be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention in other instances, which may or may not be practiced, are intended to be within the scope of the present application.
Claims (9)
1. A lightweight air rudder for rockets, comprising:
the rudder body (1) comprises an upper rudder plate (101), a lower rudder plate (102) and a connecting frame connected between the upper rudder plate (101) and the lower rudder plate (102); the connecting frame comprises a first side edge (103), a second side edge (104), a third side edge (105) and a fourth side edge (106) which are sequentially connected end to end; the first side edge (103) and the third side edge (105) are parallel to each other and perpendicular to the second side edge (104); the length of the first side (103) is less than the length of the fourth side (106); the third side edge (105) is recessed towards the first side edge (103) to form a groove;
a set of ribs comprising a first rib (201), a second rib (202) and a third rib (203); one end of the first reinforcing rib (201) is connected with the second side edge (104), and the other end of the first reinforcing rib is connected with the bottom edge of the groove; one end of the second reinforcing rib (202) is connected with the first side edge (103), and the other end of the second reinforcing rib is connected with the bottom edge of the groove; one end of the third reinforcing rib (203) is connected with the fourth side edge (106), and the other end of the third reinforcing rib is connected with the bottom edge of the groove.
2. The lightweight air rudder for rockets according to claim 1, wherein one end of said first rib (201) is connected to one third of said second side edge (104) near said third side edge (105), and the other end is connected to the end of said groove bottom edge near said second side edge (104); one end of the second reinforcing rib (202) is connected to the middle of the first side edge (103), and the other end of the second reinforcing rib is connected to the middle of the bottom edge of the groove; one end of the third reinforcing rib (203) is connected to the middle part of the fourth side edge (106), and the other end of the third reinforcing rib is connected to the end part of the bottom edge of the groove close to the fourth side edge (106).
3. The lightweight air rudder for rockets according to claim 1, wherein a thickness of the third rib (203) is larger than thicknesses of the first rib (201) and the second rib (202).
4. The lightweight air rudder for rockets according to claim 3, wherein said third rib (203) has at least one lightening hole (204) formed therein.
5. The lightweight air rudder for rockets according to claim 4, wherein said third reinforcing rib (203) has two weight-reducing holes (204) formed therein; the two lightening holes (204) are distributed along the length direction of the third reinforcing rib (203).
6. The rocket-powered lightweight rudder according to claim 1, wherein said set of ribs further includes a fourth rib (205); the fourth reinforcing ribs (205) are arranged in an area surrounded by the third reinforcing ribs (203), the fourth side (106), the third side (105) and the side of the groove; one end of the fourth reinforcing rib (205) is connected with the fourth side edge (106), and the other end is connected with the side edge of the groove.
7. The rocket-used lightweight air rudder according to claim 1, wherein the rib group further includes fifth reinforcing ribs (206); the fifth reinforcing rib (206) is arranged in an area surrounded by the first reinforcing rib (201), the second side edge (104), the third side edge (105) and the side edge of the groove; one end of the fifth strengthening rib (206) is connected with the second side edge (104), and the other end is connected with the third side edge (105).
8. The rocket light-weight air rudder according to claim 1, wherein the rudder body (1) and the reinforcing rib group are both made of aluminum alloy.
9. The lightweight air rudder for rockets according to claim 1, wherein a mounting plate (107) is fixedly provided in said groove; a rudder shaft (3) is arranged on the mounting plate (107); the rudder shaft (3) comprises a clamping part (301) fixed with the mounting plate (107) and a connecting part (302) fixedly connected with the clamping part (301); the connecting part (302) is used for connecting with a rocket body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210978588.2A CN115108054A (en) | 2022-08-16 | 2022-08-16 | Lightweight air rudder for rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210978588.2A CN115108054A (en) | 2022-08-16 | 2022-08-16 | Lightweight air rudder for rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115108054A true CN115108054A (en) | 2022-09-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210978588.2A Pending CN115108054A (en) | 2022-08-16 | 2022-08-16 | Lightweight air rudder for rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115108054A (en) |
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2022
- 2022-08-16 CN CN202210978588.2A patent/CN115108054A/en active Pending
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