Carrier rocket fairing protection method based on air cavity

Abstract

The invention provides a carrier rocket fairing protection method based on an air cavity. The carrier rocket fairing protection method comprises the following steps that a fairing cover material is selected; an adjustable air cavity is formed in the fairing cover; a portable operation requirement is set on the fairing overclothes; and analyzing the dynamic balance of the gas flow of the air cavity. The device has the beneficial effects that exhaust of the fairing air conditioner is used as a power source, a controllable air cavity is formed between the fairing and the fairing cover, then product state protection of the carrier rocket fairing in the high-salt and high-humidity environment is achieved, the influence of condensate water on the carrier rocket fairing is avoided, the product quality is guaranteed, and the service life of the carrier rocket fairing is prolonged. And therefore, the protection effect on the load is realized. Meanwhile, due to the light-weight and portable design of the fairing overclothes, the quick disassembly and assembly function of the fairing overclothes is achieved, and the operation portability of the fairing overclothes is improved on the basis that the use requirement is met.

Description

Technical Field

[0001] The invention belongs to the field of rocket fairings, and in particular relates to a carrier rocket fairing protection method based on an air cavity. Background Art

[0002] The main function of the payload fairing is to improve the aerodynamic performance of the rocket and provide a good working environment for the payload. The launch vehicle transports the payload to the predetermined orbit. When passing through the dense atmosphere, the fairing protects the payload from safe passage and protects the payload from airflow scouring and aerodynamic heating. Therefore, the fairing should be kept in good product condition before passing through the atmosphere. In a high temperature and high humidity environment, the surface temperature of the fairing is lower than the dew point to form a large amount of condensed water. The condensed water is easy to infiltrate and reach the adhesive layer on the inside of the cork. The long-term action of water vapor will cause the bonding strength between the cork and the outer panel of the fairing to decrease significantly. There is a hidden danger of large-scale peeling of cork during flight. At present, the treatment of condensed water mainly relies on wiping by personnel. Disadvantages of the existing technology: (1) The coverage and timeliness of personnel's work in wiping condensed water from the fairing are poor. The condensed water is handled by personnel using tools to wipe it, and the personnel's operating range and operating time are limited, which makes it impossible to achieve all-round real-time protection of the fairing; (2) Existing fairing covers are heavy and inconvenient to operate. The covers currently used are all rocket body protective covers to prevent the product from being physically damaged during transportation and parking. They are heavy and increase the quality risk of product damage when the launch platform is operated in multiple layers; (3) The existing fairing cover has poor adaptability. The existing fairing cover has a single design in appearance, structure and function, which cannot meet the specific needs of multi-position operation of the fairing, and lacks adaptability to conventional positions such as air conditioning ports and operation ports; (4) The existing fairing cover disassembly and assembly takes up a lot of launch process. The existing fairing cover will take up a lot of launch day time for disassembly and assembly before and after use on the launch day, affecting the continuity of the launch day process. Summary of the invention

[0003] In view of this, the present invention aims to propose a launch vehicle fairing protection method based on an air cavity to solve at least one problem existing in the above-mentioned prior art.

[0004] To achieve the above object, the technical solution of the present invention is achieved as follows: A launch vehicle fairing protection method based on an air cavity comprises the following steps: Step 1: Select the material of the fairing cover; Step 2, providing an adjustable air cavity on the fairing gown; Step 3: Set portable operation requirements on the fairing suit; Step 4: Analyze the dynamic balance of gas flow in the air cavity.

[0005] Furthermore, in step 1, the fairing cover material selection includes: In the selection of the fairing coverall, the performance is waterproof, and the material is 290T nylon spunlace, which is lightweight, with a weight per square meter of 40g / m2~80g / m2; and a PU waterproof coating is added to the inner surface of the material.

[0006] Furthermore, in step 2, an adjustable air cavity is provided on the fairing cover, including: An air cavity with adjustable air volume is formed between the fairing and the fairing cover, wherein: In terms of the power source of the air cavity, the exhaust volume of the fairing air conditioner is used. In terms of structure, the edge of the fairing cover covers the exhaust hole of the fairing. When the air conditioner is in use, the gas discharged through the exhaust hole is used as the power source of the air cavity; In terms of air cavity adjustment, a fixed margin is reserved outward along the pipeline at the air conditioning inlet and outlet to adjust the gas discharge volume in the air cavity. Zipper adjustment holes are evenly arranged along the circumference at the upper and lower ends of the fairing cover to assist in regulating the exhaust flow in the air cavity. In terms of fixing the fairing cover, fixed buckles and parachute ropes are evenly distributed on the top, and pre-buried elastic ropes are used at the end of the fairing cover to ensure the adjustment of the fit with the surface of the arrow body.

[0007] Further, in step three, portable operation requirements are set on the fairing suit, including: In the selection of the fairing gown, the unit weight of the overall gown after molding is controlled within 20Kg; In the portable operation of the fairing suit, the fairing suit is installed in the form of a single-sided zipper. A zipper is installed on the lower side of the air-conditioning port from the bottom to the top for fixing and assembling the fairing suit. A 3-meter auxiliary rope is installed at the lock position for the transfer of the launch platform's different-level brackets. An opening is reserved in advance at the load operation port of the fairing suit. To protect the fairing coverall from scratches, an anti-scratch fabric strip is added to the inside of the zipper at the one-side disassembly position.

[0008] Furthermore, in step 4, the dynamic balance analysis of the gas flow in the air cavity includes: The power source of the entire air cavity comes from the air conditioning wind in the fairing. The fairing air source flow is Q1, the air source flow of the air cavity is Q2, the air source air inlet area is S1, and the air outlet structure on the fairing structure is divided into the main air outlet of the inverted cone section, the column section exhaust hole, and the hanging point process bolt hole. The corresponding exhaust areas are S21, S22, and S23 respectively. The relationship between the air cavity air source flow and the fairing air source flow is expressed as Formula 1; The volume of gas provided by the air source in the air cavity per unit time t is calculated by formula 2; The number of gas molecules generated per unit time t is calculated by formula 3; The relationship between the pressure P2, gas volume V2, number of gas molecules n2, ideal gas thermodynamic temperature T, and ideal gas constant R generated per unit time t is calculated by formula 4; Set the equivalent cross-sectional diameter of the fairing cover to d 罩 , the weight of the fairing suit is m 罩 , if the fairing cover can be supported by the air cavity, the relational expression that meets the requirements is Formula 5: Substituting the relevant parameters into Formula 5, we can obtain the requirements that need to be met for the dynamic balance of the air cavity outside the fairing.

[0009] Furthermore, the expression of Formula 1 is: = .

[0010] Furthermore, the expression of Formula 2 is: V2=Q2·t.

[0011] Furthermore, the expression of Formula 3 is: n2= .

[0012] Furthermore, the expression of Formula 4 is: P2V2=n2RT.

[0013] Furthermore, the expression of Formula 5 is: P2 πd 罩 2 ≥m 罩 .

[0014] Compared with the prior art, the air cavity-based launch vehicle fairing protection method of the present invention has the following advantages: The present invention discloses a method for protecting a launch vehicle fairing based on an air cavity. The present invention utilizes the exhaust gas of the fairing air conditioner as a power source to form a controllable air cavity between the fairing and the fairing cover, thereby realizing the product state protection of the launch vehicle fairing in a high-salt and high-humidity environment, avoiding the influence of condensed water on the launch vehicle fairing, ensuring product quality, and realizing the protection of the load. At the same time, the lightweight and portable design of the fairing cover realizes the rapid disassembly and assembly function of the fairing cover, and increases the portability of the operation of the fairing cover on the basis of meeting the use requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 This is a schematic diagram of the terminal position design according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the main body design described in an embodiment of the present invention; Figure 3 A schematic diagram of the installation and use process of the fairing gown according to an embodiment of the present invention; Figure 4 The figure is a schematic diagram of the process of removing the fairing cover according to an embodiment of the present invention. DETAILED DESCRIPTION

[0016] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0017] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0018] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0019] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0020] Glossary: Fairing: External structure used to protect the load.

[0021] Fairing coverall: used to isolate from the external environment.

[0022] like Figure 1 As shown in the figure, a launch vehicle fairing protection method based on an air cavity comprises the following steps: Step 1: Select the material of the fairing cover; Step 2, providing an adjustable air cavity on the fairing gown; Step 3: Set portable operation requirements on the fairing suit; Step 4: Analyze the dynamic balance of gas flow in the air cavity.

[0023] The present invention uses the exhaust of the fairing air conditioner as the power source, forms a controllable air cavity between the fairing and the fairing cover, thereby realizing the product state protection of the launch vehicle fairing in a high-salt and high-humidity environment, avoiding the influence of condensed water on the launch vehicle fairing, ensuring product quality, and realizing the protection of the load. At the same time, the lightweight and portable design of the fairing cover realizes the rapid disassembly and assembly function of the fairing cover, and increases the portability of the operation of the fairing cover on the basis of meeting the use requirements.

[0024] In a preferred embodiment of the present invention, the fairing cover material is selected.

[0025] (1) In the selection of fairing coveralls, the main performance is waterproof performance, which can isolate external condensation water. Secondly, the material selection should pay attention to wear resistance and deadweight, so that personnel can easily unfold and fold them. The material selected is 290T nylon.

[0026] (2) Lightweight: This type of material is a spun filament made of nylon filament. The fabric composition is 100% nylon, and the weight per square meter is 40g / m2~80g / m2, which can meet the needs of lightweight use.

[0027] (3) Waterproof performance: 290T nylon taffeta, T represents the sum of the number of warp and dimensional yarns per inch of nylon taffeta. The corresponding specifications can be found in the "Uniform Specifications for Chinese Export Silks". Adding PU waterproof coating on the inner surface can achieve the structural requirements of waterproof and sealing. (4) Wear resistance: 290T nylon spunlace has the advantages of being light, thin, strong, wear-resistant and easy to clean. Under the same specifications, its wear resistance is higher than that of polyester fiber material and can meet the use requirements.

[0028] It adopts waterproof, wear-resistant and lightweight fabric, made of 290T nylon taffeta or similar materials, and adds PU waterproof coating on the inside to meet the overall gas sealing requirements of the fairing cover; In a preferred embodiment of the present invention, an adjustable air cavity is designed on the fairing gown. Through the following related designs, an air cavity with adjustable air volume can be formed between the fairing and the fairing gown, and at the same time, the overall posture of the fairing gown is stable and reliable, achieving the purpose of isolating from the external high-salt and high-humidity environment.

[0029] (1) In terms of the power source of the air cavity, the design considers the use of the exhaust volume of the fairing air conditioner. In terms of structure, the edge of the fairing cover should cover the exhaust hole of the fairing. When the air conditioner is in use, the gas discharged through the exhaust hole serves as the power source of the air cavity; (2) In terms of air cavity adjustment, a fixed margin is reserved along the pipeline at the inlet and outlet of the air conditioner to adjust the gas discharge volume in the air cavity. Zipper adjustment holes are evenly distributed along the circumference at the upper and lower ends of the fairing cover to assist in regulating the exhaust flow in the air cavity. (3) In terms of fixing the fairing suit, the design evenly distributes the fixed lock buckles and parachute ropes on the top to ensure that the fairing suit can maintain a stable posture when the air cavity is stable. The pre-buried elastic rope is used at the end of the fairing suit to ensure the degree of fit with the surface of the arrow body. In a preferred embodiment of the present invention, portable operation requirements are designed on the fairing suit.

[0030] (1) In the selection of the fairing cover, the unit weight of the overall cover after molding is controlled within 20 kg, which can meet the needs of a single person to carry and operate; (2) In terms of the portable operation design of the fairing gown, the fairing gown is installed with a single-sided zipper. A zipper is installed on the lower side of the air-conditioning port from the bottom to the top for fixing and assembling the fairing gown. A 3-meter auxiliary rope is installed at the lock position for transferring the brackets on different levels of the launch platform. The fairing gown can be disassembled and installed in a short time. An opening is reserved in advance at the load operation port position of the fairing gown to meet the load operation requirements during the process. (3) In the anti-scratch design of the fairing cover, an anti-scratch cloth strip is added to the inside of the zipper at the one-side disassembly position to prevent the zipper from scratching the surface of the arrow body when the fairing cover is shaken.

[0031] In a preferred embodiment of the present invention, the gas flow in the air cavity is dynamically balanced and analyzed.

[0032] The power source of the entire air cavity comes from the air conditioning wind in the fairing. The fairing air source flow is Q1, the air source flow of the air cavity is Q2, the air source air inlet area is S1, and the air outlet structure of the fairing structure can be divided into the main air outlet of the inverted cone section, the column section exhaust hole, and the hanging point process bolt hole. The corresponding exhaust areas are S21, S22, and S23 respectively. The air cavity air source flow and the fairing air source flow satisfy the following relationship: = ; The volume of gas provided by the air cavity gas source per unit time t is: V2=Q2·t; The number of gas molecules produced per unit time t is: n2= ; The pressure P2, gas volume V2, number of gas molecules n2, ideal gas thermodynamic temperature T, and ideal gas constant R generated per unit time t satisfy the following relationship: P2V2=n2RT; The equivalent cross-sectional diameter of the fairing cover is d 罩 , the weight of the fairing suit is m 罩 If the fairing gown can be supported by the air cavity, the following requirements should be met: P2 πd 罩 2 ≥m 罩 ; By bringing in relevant parameters, we can obtain the requirements that need to be met for the dynamic balance of the air cavity outside the fairing.

[0033] The present invention achieves isolation and protection of the fairing from the external environment, and at the same time meets the demand for rapid disassembly and assembly of the fairing cover. By selecting materials and designing the appearance of the fairing cover, and using the exhaust air source of the air conditioner in the fairing, an adjustable air cavity is formed between the outer surface of the fairing and the fairing cover, which completely isolates the high-salt and high-humidity environment of the outside world. At the same time, through the structural design on the fairing cover, the filling amount of the air cavity can be adjusted to meet the use requirements under different air supply flow rates; at the same time, a lightweight and portable design is adopted in the structure of the fairing cover to avoid joint operation by multiple personnel and multiple platforms.

[0034] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A launch vehicle fairing protection method based on an air cavity, characterized in that: The following steps are involved: Step 1: Select the material of the fairing cover; Step 2, providing an adjustable air cavity on the fairing gown; Step 3: Set portable operation requirements on the fairing suit; Step 4: Analyze the dynamic balance of gas flow in the air cavity.

2. The air cavity-based launch vehicle fairing protection method according to claim 1, characterized in that: In step one, the fairing cover material selection includes: In the selection of the fairing coverall, the performance is waterproof, and the material is 290T nylon spunlace, which is lightweight, with a weight per square meter of 40g / m2~80g / m2; and a PU waterproof coating is added to the inner surface of the material.

3. The air cavity-based launch vehicle fairing protection method according to claim 1, characterized in that: In step 2, an adjustable air cavity is provided on the fairing suit, including: An air cavity with adjustable air volume is formed between the fairing and the fairing cover, wherein: In terms of the power source of the air cavity, the exhaust volume of the fairing air conditioner is used. In terms of structure, the edge of the fairing cover covers the exhaust hole of the fairing. When the air conditioner is in use, the gas discharged through the exhaust hole is used as the power source of the air cavity; In terms of air cavity adjustment, a fixed margin is reserved outward along the pipeline at the air conditioning inlet and outlet to adjust the gas discharge volume in the air cavity. Zipper adjustment holes are evenly arranged along the circumference at the upper and lower ends of the fairing cover to assist in regulating the exhaust flow in the air cavity. In terms of fixing the fairing cover, fixed buckles and parachute ropes are evenly distributed on the top, and pre-buried elastic ropes are used at the end of the fairing cover to ensure the adjustment of the fit with the surface of the arrow body.

4. The air cavity-based launch vehicle fairing protection method according to claim 1, characterized in that: In step three, set up portable operation requirements on the fairing suit, including: In the selection of the fairing gown, the unit weight of the overall gown after molding is controlled within 20Kg; In the portable operation of the fairing suit, the fairing suit is installed in the form of a single-sided zipper. A zipper is installed on the lower side of the air-conditioning port from the bottom to the top for fixing and assembling the fairing suit. A 3-meter auxiliary rope is installed at the lock position for the transfer of the launch platform's different-level brackets. An opening is reserved in advance at the load operation port of the fairing suit. To protect the fairing coverall from scratches, an anti-scratch fabric strip is added to the inside of the zipper at the one-side disassembly position.

5. The air cavity-based launch vehicle fairing protection method according to claim 1, characterized in that: In step 4, the dynamic balance analysis of the air cavity gas flow includes: The power source of the entire air cavity comes from the air conditioning wind in the fairing. The fairing air source flow is Q1, the air source flow of the air cavity is Q2, the air source air inlet area is S1, and the air outlet structure on the fairing structure is divided into the main air outlet of the inverted cone section, the column section exhaust hole, and the hanging point process bolt hole. The corresponding exhaust areas are S21, S22, and S23 respectively. The relationship between the air cavity air source flow and the fairing air source flow is expressed as Formula 1; The volume of gas provided by the air source in the air cavity per unit time t is calculated by formula 2; The number of gas molecules generated per unit time t is calculated by formula 3; The relationship between the pressure P2, gas volume V2, number of gas molecules n2, ideal gas thermodynamic temperature T, and ideal gas constant R generated per unit time t is calculated by formula 4; Assume the equivalent cross-sectional diameter of the fairing cover is d 罩 , the weight of the fairing suit is m 罩 , if the fairing cover can be supported by the air cavity, the relational expression that meets the requirements is Formula 5: Substituting the relevant parameters into Formula 5, we can obtain the requirements that need to be met for the dynamic balance of the air cavity outside the fairing.

6. The air cavity-based launch vehicle fairing protection method according to claim 5, characterized in that: The expression of Formula 1 is: = 。 7. The air cavity-based launch vehicle fairing protection method according to claim 5, characterized in that: The expression of Formula 2 is: V2=Q2·t.

8. The air cavity-based launch vehicle fairing protection method according to claim 5, characterized in that: The expression of Formula 3 is: n2= 。 9. The air cavity-based launch vehicle fairing protection method according to claim 5, characterized in that: The expression of Formula 4 is: P2V2=n2RT.

10. The air cavity-based launch vehicle fairing protection method according to claim 5, characterized in that: The expression of Formula 5 is: P2· πd 罩 2 ≥m 罩 。

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