CN113212812B - Self-dropping type lightning protection diversion strip of solid rocket - Google Patents
Self-dropping type lightning protection diversion strip of solid rocket Download PDFInfo
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- CN113212812B CN113212812B CN202110477749.5A CN202110477749A CN113212812B CN 113212812 B CN113212812 B CN 113212812B CN 202110477749 A CN202110477749 A CN 202110477749A CN 113212812 B CN113212812 B CN 113212812B
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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
- B64G1/52—Protection, safety or emergency devices; Survival aids
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B5/00—Non-insulated conductors or conductive bodies characterised by their form
- H01B5/02—Single bars, rods, wires, or strips
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Abstract
The invention relates to a solid rocket self-dropping type lightning protection diversion strip which comprises a diversion strip main body, a transition structure, an overlapping structure and a spraying layer, wherein the diversion strip main body is provided with a transition structure; the thickness of the diversion strip main body, the thickness of the transition structure and the thickness of the lap joint structure are the same, the diversion strip main body, the transition structure and the lap joint structure are bonded on the heat-proof layer of the solid rocket head cover, and the bonding surface and the heat-proof layer are in a common shape; at least four diversion strip main bodies are uniformly arranged along the circumferential direction of the head cover, a distance is reserved between one end of each diversion strip main body and the top point of the head cover, and a transition structure and a lap joint structure are sequentially arranged at the other end of each diversion strip main body; gaps are reserved between the diversion strip main body and the transition structure and between the transition structure and the lap joint structure, and the gaps are filled with the static-free paint; the end face of the lap joint structure is connected with the butt joint face of the shell body through a spraying layer.
Description
Technical Field
The invention belongs to the field of electromagnetic compatibility in space transporters in an aerospace system.
Background
The solid rocket has a physical mechanism of inducing thunder due to the long rocket body, certain conductivity of tail flame and high flying speed. The solid rocket needs to have all-weather launching capability and protection capability of direct lightning discharge.
The solid rocket shell is generally made of aluminum/carbon fiber composite materials and is made of conductive materials. In order to prevent the influence of pneumatic heating on the shell of the carrier rocket in the flying process, the shell of the rocket is also covered with a thicker special heat-proof coating, and the coatings used at present are all non-conductive materials. After lightning strikes on the carrier rocket, current as high as 200kA can be generated on the surface of the rocket body. The heating effect produced by the current will seriously damage the thermal protection coating. Once the heat-proof layer is broken down by thunder, the formed meter-level holes can cause the shell of the spacecraft to be broken through by pneumatic heating in the subsequent flying process, and finally the rocket explodes and fails to launch.
In order to avoid the ablation of the spacecraft launch vehicle structure by the lightning arc, the installation of the air guide strips (i.e. continuous or discontinuous metal strips) is an important protection method, i.e. the lightning discharge leader is formed on the air guide strips instead of the shell body by the air guide strips. At the end and front section of the launch vehicle, the air guide strips have advantages over the protection method (such as hot-pressing metal net or metal spraying) of forming a metal layer on the surface, because: the cross section of the flow guide strip is thick, the pneumatic heating resistance is high, and ablation before passing through a troposphere can be prevented; the second and most spacecrafts have a vertical flight section in the carrier rocket, so that thunder and lightning can be attached to the head of the aircraft rocket for a long time in the section, and the thick section of the flow guide strip enables the aircraft rocket to bear total transfer charges up to 200 coulombs more easily; thirdly, the process difficulty of hot-pressing a metal net or metal flame spraying on the surface of the heat-proof material of the integral cylindrical shell section with the diameter of one meter or two meters is high, and the flow guide strip is relatively easy to install.
However, the conventional air guide strips mounted on the aircraft radome cannot be applied to the solid rocket mainly due to the following reasons: (1) different discharging processes: the head of the solid rocket is usually an aluminum or carbon fiber shell with a heat-proof layer, namely a conductor-insulator double-layer structure, but not a pure insulator of an airplane radome, so that the electric arc generation process is different; (2) different fixing modes: in order to meet the heat-proof requirement of the solid rocket, the diversion strips can only be bonded on the heat-proof layer and cannot be riveted on the shell; (3) different thermal environmental conditions: the heat flow and the pneumatic shearing force of the head of the solid rocket are large, and the diversion strips need not to fall off before the rocket reaches the main lightning generation height; as the total heat flow further increases to the point that the adhesive is debonded, the flow guide strips should effectively fall off and not become abnormal protrusions which affect the pneumatic characteristics; (4) different lightning environments: the solid rocket has a vertical flight section, the head of the rocket is a long-time attachment point of thunder, the thunder energy generated by unit resistance is strong, while the airplane only flies horizontally, and the thunder only stays in the nose for a short time due to the sweeping channel effect, so that the energy is relatively small.
Disclosure of Invention
The technical problem solved by the invention is as follows: overcomes the defects of the prior art and provides a solid rocket self-dropping type lightning protection diversion strip.
The technical scheme of the invention is as follows: the solid rocket self-dropping type lightning protection diversion strip comprises a diversion strip main body, a transition structure, an overlapping structure and a spraying layer; the thickness of the diversion strip main body, the thickness of the transition structure and the thickness of the lap joint structure are the same, the diversion strip main body, the transition structure and the lap joint structure are bonded on the heat-proof layer of the solid rocket head cover, and the bonding surface and the heat-proof layer are in a common shape;
at least four diversion strip main bodies are uniformly arranged along the circumferential direction of the head cover, a distance is reserved between one end of each diversion strip main body and the top point of the head cover, and a transition structure and a lap joint structure are sequentially arranged at the other end of each diversion strip main body; gaps are reserved between the diversion strip main body and the transition structure and between the transition structure and the lap joint structure, and the gaps are filled with the antistatic coating; the end face of the lap joint structure is connected with the butt joint face of the shell body through a spraying layer.
Further, the cross-sectional area of each guide strip main body, which is perpendicular to the axial direction of the solid rocket nose cover, is selected according to the following relation:
wherein S is a sectional area; a is the total action time integral of the lightning pulse; rho is the density of the main material of the flow guide strip, c is the specific heat capacity of the main material of the flow guide strip, sigma is the conductivity of the main material of the flow guide strip, delta T is the temperature rise allowed by the adhesive used in the bonding process, and k is the safety coefficient.
Further, the distance between one end of the diversion strip main body and the vertex of the solid rocket nose cover and the distance between the diversion strip main bodies both satisfy the following relational expression:
wherein E is the insulation strength of the heat-proof layer material, and is represented by V/m, and t is the thickness of the heat-proof layer, and is represented by m; d represents a distance.
Furthermore, the transition structure is used for reducing the current density flowing into the rocket body base body from the butt joint surface of the head cover, the maximum width of the transition structure is not less than 50mm, the edges of the transition structure are in smooth transition with different widths, and the width is along the circumferential direction of the solid rocket head cover.
Furthermore, the lapping structure is used for providing ablation amount of lightning attached for a long time in a vertical flight section of the rocket, the length of the lapping structure is not less than 10mm, and the length is along the axial direction of the solid rocket nose cover.
Furthermore, the temperature resistance of the adhesive used for bonding is not lower than 250 ℃.
Further, when the heat-proof layer is an organic silicon heat-proof coating, the heat-proof coating is bonded by the viscosity of the heat-proof coating; when the heat-proof layer is made of phenolic aldehyde-based composite materials, epoxy resin glue is used for bonding and fixing.
Furthermore, the gap between the diversion strip main body and the transition structure and the gap between the transition structure and the lap joint structure are less than 0.5mm.
Furthermore, the antistatic coating can resist the temperature of not less than 250 ℃ and has the resistivity of not more than 10 3 Omega m antistatic coating.
Further, arc aluminum spraying or flame aluminum spraying is adopted to connect the butt joint surface of the shell body with the lap joint structure, and after aluminum spraying, appearance leveling is carried out, wherein the aluminum spraying thickness is not less than 0.5mm.
Furthermore, the thickness of the diversion strip main body, the transition structure and the lap joint structure ranges from 0.5mm to 2mm.
Furthermore, the material of the main body, the transition structure and the lap joint structure of the flow guide strip is industrial pure aluminum 1050 or aluminum alloy.
Furthermore, the resistivity of the spraying body on the flow guide strip body is not more than 10 3 Omega m of antistatic paint, and spraying three-proofing paint on the rest parts of the head cover.
The invention is suitable for the arrow body with the heat-proof layer as the insulator.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a self-dropping type lightning protection diversion strip of a solid rocket. Lightning protection is provided for the rocket body (generally silicone, high silica, phenolic quartz fiber composite materials and the like) with the heat-proof layer as an insulator. The main body of the structure is adhered to the heat-proof layer, does not fall off before the rocket reaches the main lightning generation height, and can bear the lightning current waveform of the lightning long-time attachment part specified by GJB8848 with light weight, namely the combination of four current components of A + B + C + D in the standard can also bear certain heat flow and pneumatic shearing force; the structure also comprises a termination structure of the flow guide strip and the shell section, so that effective lap joint is realized, the flow guide strip can be automatically peeled off after the accumulated heat flow is further increased along with the flight time, and the pneumatic characteristic is prevented from being influenced because the flow guide strip cannot be separated after the adhesive fails.
Drawings
FIG. 1 is a schematic view of the structure of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a self-dropping type lightning protection diversion strip structure of a solid rocket. The device can: (1) Guiding lightning attachment points to be generated on the air guide strips but not on the heat-proof layer on the conductor-insulator double-layer structure; (2) The main body of the structure is adhered to the heat-proof layer and does not fall off before the rocket reaches the main lightning generation height; (3) As the total heat flow further increases to debond the adhesive, the tie bars should effectively fall off; (4) The current guiding strips are able to withstand the heat generated by the lightning discharge current.
The device consists of a flow guide strip body, a transition structure, a lap joint structure and a spraying layer. The structural plan view and the side view are seen in the attached figure 1.
The air guide strips in fig. 1 are mounted on the head cover of an arrow structure, and the arrow structure consists of a matrix (aluminum alloy or carbon fiber composite) and a heat-proof layer on the matrix. The structure of the nose cover is generally a cylinder, a cone or a combination of the cylinder and the cone or a similar curved surface structure, and the curvature of the structure is omitted in the figure because the radius is far larger than the width of the flow guide strip. The left side in the figure is the arrow body head direction, and the right side is the butt joint surface of the head cover and other arrow body sections.
The main body of the guide strip in figure 1 is industrial pure aluminum or aluminum alloy. The cross section of the flow guide strip ensures that the temperature rise generated by the through-flow of the lightning current is within a specified value, namely, a smaller value meeting the following formula is taken to reduce the weight of the flow guide strip as much as possible,
wherein S is a sectional area; a is the total action time integral of the lightning pulse, and the numerical value of A is the sum of the total action time integral of the lightning discharge waveform A and the lightning discharge waveform D in GJB8848, namely A =2.25 MJ/omega; rho is the density of the material, c is the specific heat capacity of the material, sigma is the conductivity of the material, delta T is the temperature rise allowed by the adhesive or a small empirical value (such as 250 ℃), the average value of the temperature from normal temperature to the material parameter is considered, k is a safety coefficient, and 1.5 and other empirical values can be taken as required. The aspect ratio of the tie bar body is not specified and can be determined by the bonding process (e.g., for 1050 industrial pure aluminum, a useful size is 8mm x 1mm).
The number of the guide strip main bodies in fig. 1 is uniformly arranged along the circumferential direction of the hood, the distance between the tail end (namely, the left edge in the figure) of the guide strip main bodies and the vertex of the hood and the distance between the guide strip main bodies are not more than the following numerical values (namely, the guide strip main bodies are selected according to a formula 2, and the values of the guide strip main bodies and the guide strip main bodies are not required to be the same), and the total number of the guide strip main bodies is not less than 4.
Wherein E is the insulation strength of the heat-proof material and is in the unit of V/m, and t is the thickness of the heat-proof layer and is in the unit of m. This distance is used to ensure the ability of the conducting strip to guide the lightning attachment point.
The transition structure of fig. 1 is used to reduce the current density flowing from the mask interface into the arrow body base, and has a maximum width of no less than 50mm. The thickness is the same as the main body of the guide strip. The transition structure should be pre-formed to the same curvature as the hood surface after cutting.
The lap joint structure in fig. 1 is used for providing ablation (namely, C component of GJB8848 lightning current waveform) of lightning attaching for a long time in a rocket vertical flight section, and the length of the lap joint structure is not less than 10mm. The lap joint structure is also pre-formed to the same curvature of the hood surface after cutting.
The diversion strip main body, the transition structure and the lap joint structure in the figure 1 are all bonded on the heat-proof layer by using a high-temperature-resistant adhesive. The temperature resistance of the adhesive is not lower than 250 ℃. For example, when the heat-shielding layer is a silicone heat-shielding coating, bonding can be performed with the viscosity of the coating itself; when the heat-proof layer is a phenolic-based composite material, high-temperature-resistant epoxy resin glue can be used for fixing. When bonded, one end of the bridging structure should be aligned with the abutting face of the hood.
Gaps between the diversion strip main body and the transition structure and between the transition structure and the lap joint structure in the picture 1 are smaller than 0.5mm, so that the gaps can be effectively discharged under the action of thunder and lightning.
In the figure 1, a small amount of temperature resistance is applied to the gap between the guide strip main body and the transition structure and the gap between the transition structure and the lap joint structure, the temperature resistance is not less than 250 ℃, and the resistivity is not more than 10 3 Omega m antistatic coatings (e.g. four-component paints) caulk. So that the time constant is not more than 10 -8 And s, namely the whole guide strip is basically equipotential under the action of an electrostatic field before lightning occurs.
The spraying connecting part in the figure 1 is implemented after the diversion strip main body, the transition structure and the lap joint structure are bonded and cured, the butt joint surface of the shell body in the figure 1 is connected with the lap joint structure in the figure 1 by adopting electric arc aluminum spraying or flame aluminum spraying, the appearance is leveled after the aluminum spraying, and the aluminum spraying thickness is not less than 0.5mm.
The principle of the solid rocket self-dropping type lightning protection guide strip is shown in the attached figure 1.
(1) Calculating the sectional area of the flow guide strip according to a formula (1), and determining the length and width value of the sectional area according to the process requirement;
(2) Calculating the distance between the vertex of the guide strip and the vertex of the head cover according to a formula (2) so as to obtain the length of the guide strip; and (4) calculating the gaps of the guide strips according to a formula (2) so as to obtain the number of the guide strips.
(3) Processing the diversion strip main body, the transition structure and the lap joint structure in the figure 1. The material is industrial pure aluminum 1050, or aluminum alloy.
(4) And performing the transition structure and the lap joint structure according to the curvature of the hood.
(5) The diversion strip main body, the transition structure and the lap joint structure in the figure 1 are all bonded on the heat-proof layer by using a high-temperature-resistant adhesive. The temperature resistance of the adhesive is not lower than 250 ℃. For example, when the heat-shielding layer is a silicone heat-shielding coating, bonding can be performed with the viscosity of the coating itself; when the heat-proof layer is a phenolic-based composite material, high-temperature-resistant epoxy resin glue can be used for fixing. During bonding, one end of the overlapping structure should be aligned with the abutting face of the hood. The clearance of water conservancy diversion strip main part and transition structure, the clearance of transition structure and overlap joint structure should be less than 0.5mm to guarantee that the clearance can effectively discharge under the thunder and lightning effect.
(6) The gap between the main body and the transition structure, and the gap between the transition structure and the lap joint structure in FIG. 1 can resist a small amount of temperature not less than 250 deg.C, and has a bulk resistivity not greater than 10 3 Omega m antistatic coatings (e.g. four-component paints) caulk.
(7) And (3) adopting electric arc aluminum spraying or flame aluminum spraying to connect the butt joint surface of the shell substrate in the figure 1 with the lap joint structure in the figure 1, and leveling the appearance after aluminum spraying, wherein the aluminum spraying thickness is not less than 0.5mm.
(8) The surface of the constructed hood can be sprayed with three-proofing paint and can not be sprayed with four-proofing paint. If the spray painting is needed, the volume resistivity of the diversion strip body is not more than 10 3 Omega m antistatic paint.
The invention is used for providing lightning protection for the arrow body (generally organosilicon, high silica, phenolic quartz fiber composite material and the like) with the heat-proof layer as the insulator, and the heat-proof layer is made of materials with certain conductivity, such as C/SiC and the like, and is out of the application range of the invention due to the other protection scheme.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make possible variations and modifications of the present invention using the method and the technical contents disclosed above without departing from the spirit and scope of the present invention, and therefore, any simple modifications, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention are all within the scope of the present invention.
The invention has not been described in detail in part in the common general knowledge of a person skilled in the art.
Claims (11)
1. The solid rocket self-dropping type lightning protection diversion strip is characterized in that: comprises a diversion strip main body, a transition structure, a lap joint structure and a spraying layer; the thickness of the diversion strip main body, the thickness of the transition structure and the thickness of the lap joint structure are the same, the diversion strip main body, the transition structure and the lap joint structure are bonded on the heat-proof layer of the solid rocket head cover, and the bonding surface and the heat-proof layer are in a common shape;
at least four diversion strip main bodies are uniformly arranged along the circumferential direction of the head cover, a distance is reserved between one end of each diversion strip main body and the top point of the head cover, and a transition structure and a lap joint structure are sequentially arranged at the other end of each diversion strip main body; gaps are reserved between the diversion strip main body and the transition structure and between the transition structure and the lap joint structure, and the gaps are filled with the static-free paint; the end face of the lap joint structure is connected with the butt joint face of the shell body through a spraying layer;
the transition structure is used for reducing the current density flowing into the rocket body base body from the butt joint surface of the head cover, the maximum width of the transition structure is not less than 50mm, the edges of the transition structure are in smooth transition among different widths, and the width is along the circumferential direction of the solid rocket head cover; the lap joint structure is used for providing ablation amount of lightning attached for a long time in a vertical flight section of the rocket, the length of the lap joint structure is not less than 10mm, and the length of the lap joint structure is along the axial direction of the solid rocket head cover; the temperature resistance of the adhesive used for bonding is not lower than 250 ℃.
2. The gib of claim 1, wherein: the cross section area of each flow guide strip main body, which is vertical to the axial direction of the solid rocket nose cover, is selected according to the following relation:
wherein S is a sectional area; a is the total action time integral of the lightning pulse; rho is the density of the main material of the flow guide strip, c is the specific heat capacity of the main material of the flow guide strip, sigma is the conductivity of the main material of the flow guide strip, delta T is the temperature rise allowed by the adhesive used in the bonding process, and k is the safety coefficient.
3. The gib of claim 1, wherein: the distance between one end of the diversion strip main body and the top point of the solid rocket nose cover and the distance between the diversion strip main bodies both satisfy the following relational expression:
wherein E is the insulation strength of the heat-proof layer material, and the unit is V/m, and t is the thickness of the heat-proof layer, and the unit is m; d represents a distance.
4. The gib of claim 1, wherein: when the heat-proof layer is an organic silicon heat-proof coating, the heat-proof coating is bonded by the viscosity of the heat-proof coating; when the heat-proof layer is a phenolic aldehyde-based composite material, epoxy resin glue is used for bonding and fixing.
5. The gib of claim 1, wherein: the gap between the diversion strip main body and the transition structure and the gap between the transition structure and the lap joint structure are less than 0.5mm.
6. The gib of claim 1, wherein: the antistatic coating has the temperature resistance of not less than 250 ℃ and the resistivity of not more than 10 3 Omega m antistatic coating.
7. The gib of claim 1, wherein: and adopting electric arc aluminum spraying or flame aluminum spraying to connect the butt joint surface of the shell base body with the lap joint structure, and leveling the appearance after aluminum spraying, wherein the aluminum spraying thickness is not less than 0.5mm.
8. The gib of claim 1, wherein: the thickness of the diversion strip main body, the transition structure and the lap joint structure ranges from 0.5mm to 2mm.
9. The gib of claim 1, wherein: the material of the diversion strip main body, the transition structure and the lap joint structure is industrial pure aluminum 1050 or aluminum alloy.
10. The gib of claim 1, wherein: the resistivity of the spraying body on the flow guide strip body is not more than 10 3 Omega m antistatic paint and headSpraying three-proofing paint on the rest parts of the cover.
11. The weatherstrip of any one of claims 1 to 10, wherein: the heat-proof layer is suitable for the arrow body with the heat-proof layer being an insulator.
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| CN202110477749.5A CN113212812B (en) | 2021-04-30 | 2021-04-30 | Self-dropping type lightning protection diversion strip of solid rocket |
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| CN202110477749.5A CN113212812B (en) | 2021-04-30 | 2021-04-30 | Self-dropping type lightning protection diversion strip of solid rocket |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3965285A (en) * | 1974-07-08 | 1976-06-22 | Robert Dickson Hill | Electrically conductive object having an ablative layer thereon for protecting the same from damage by an electrical discharge |
| CA2125378A1 (en) * | 1993-06-09 | 1994-12-10 | James A. E. Bell | Composition for lightning strike protection and improved electrical conductivity |
| US7120004B2 (en) * | 2003-08-18 | 2006-10-10 | Hall Allen L | Current diverter strip and methods |
| FR2940927B1 (en) * | 2009-01-09 | 2013-01-04 | Eads Europ Aeronautic Defence | COMPOSITE MATERIAL STRUCTURE PROTECTED FROM LIGHTNING EFFECTS |
| US9928939B1 (en) * | 2016-12-12 | 2018-03-27 | Delphi Technologies, Inc. | Device and method for splicing shielded wire cables |
| US10875663B2 (en) * | 2017-12-11 | 2020-12-29 | The Boeing Company | Lightning protection in aircrafts constructed with carbon fiber reinforced plastic |
| CN110556779A (en) * | 2019-07-26 | 2019-12-10 | 中国航空工业集团公司济南特种结构研究所 | Modular reposition of redundant personnel strip is hit in lightning protection |
| CN111237124B (en) * | 2020-02-19 | 2021-11-05 | 上海电气风电集团股份有限公司 | System integrating wind power blade leading edge protection and lightning stroke protection |
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