A method for selecting the launch vehicle fairing environmental system

Abstract

The invention discloses a carrier rocket fairing environment system selection method, which belongs to the field of rocket launch technology, comprising: determining design parameters of the carrier rocket fairing environment system according to the operating requirements and environmental conditions of the carrier rocket fairing; determining the pipeline connection form and air-conditioning connector form of the carrier rocket fairing environment system; calculating the selection parameters of the carrier rocket fairing environment system; selecting the carrier rocket fairing environment system according to the calculated carrier rocket fairing environment system selection parameters; the selection method of the invention can accurately calculate various parameters in the carrier rocket fairing environment system according to the operating conditions of the carrier rocket, and then determine the selection standards of various components, thereby realizing the effective selection of the carrier rocket fairing environment system and improving the accuracy of the selection.

Description

Technical Field

[0001] The invention relates to the technical field of rocket launching, and in particular to a method for selecting a launch vehicle fairing environment system. Background Art

[0002] Before modern rocket launches, air conditioning systems are required to control the temperature, humidity, air quality, and other environmental conditions. At the moment of rocket ignition or within the set time before launch, the environmental system must always be connected to the inside of the fairing to ensure that the fairing can meet the corresponding environmental requirements.

[0003] When determining the launch vehicle fairing environment, the selection is generally based on expert experience. Inaccurate selection may result in the internal environment of the fairing not meeting the requirements or causing excessive redundancy in the environmental system, resulting in overproduction. This also causes the existing launch vehicle fairing environmental system selection method to fail to meet the requirements of commercial aerospace.

[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0005] In order to solve the above technical problems, the present application provides a method for selecting a launch vehicle fairing environment system, which can realize the selection of the launch vehicle fairing environment system and effectively improve the accuracy of the selection.

[0006] A method for selecting a launch vehicle fairing environment system, comprising:

[0007] Determine the design parameters of the launch vehicle fairing environmental system according to the launch vehicle fairing operating requirements and environmental conditions;

[0008] Determine the piping connection form and air conditioning connector form of the launch vehicle fairing environment system;

[0009] Calculate the selection parameters of the launch vehicle fairing environmental system;

[0010] According to the calculated launch vehicle fairing environment system selection parameters, the launch vehicle fairing environment system is selected;

[0011] Among them, the selection parameters of the launch vehicle fairing environment system include: cooling capacity, cooling fresh air volume, heating capacity, humidification capacity, unit static pressure, air leakage rate and duct heat dissipation.

[0012] Preferably, the operating requirements and environmental conditions include temperature, relative humidity, ground wind speed and salt spray environment.

[0013] Preferably, the design parameters include ventilation cleanliness, temperature in the instrument cabin, humidity in the instrument cabin, air supply form, electrical system, effective air exchange volume of the fairing, cross-section of the fairing ventilation inlet, diameter of the ventilation hose and total fresh air volume.

[0014] Preferably, the calculation formula for the cooling capacity in the rocket fairing environmental system is:

[0015] Q C =(k1A1+K2A2+k3A3)×△T C ;

[0016] In the formula, Q C is the cooling capacity; k1 is the comprehensive heat transfer coefficient of the front cone section of the fairing; A1 is the comprehensive heat transfer area of ​​the front cone section of the fairing; k2 is the comprehensive heat transfer coefficient of the column section of the fairing; A2 is the comprehensive heat transfer area of ​​the column section of the fairing; k3 is the comprehensive heat transfer coefficient of the inverted cone section of the fairing; A3 is the comprehensive heat transfer area of ​​the inverted cone section of the fairing; △T C Target temperature drop.

[0017] Preferably, the calculation formula for the cooling fresh air volume in the rocket fairing environmental system is:

[0018]

[0019] Where V x is the cooling fresh air volume; ρ is the supply air density; h c h is the air supply enthalpy of air conditioning; i is the enthalpy of the control point inside the launch vehicle fairing.

[0020] Preferably, the humidification amount calculation formula in the rocket fairing environmental system is:

[0021]

[0022] Where G is the humidification amount; d i is the humidity content at the air supply point; d c is the humidity content at the air inlet point.

[0023] Preferably, the heating amount calculation formula in the rocket fairing environmental system is:

[0024]

[0025] In the formula, Q h is the heating capacity; c is the specific heat capacity at constant pressure; △T h is the target temperature rise.

[0026] Preferably, the calculation formula for the static pressure of the unit in the rocket fairing environment system is:

[0027] ΔP=ΔP1+ΔP2+ΔP3+ΔP4+ΔP5+ΔP6+ΔP7;

[0028] In the formula, ΔP is the static pressure of the unit; ΔP1 is the resistance along the air duct; ΔP2 is the elbow resistance; ΔP3 is the wind resistance of the evaporator module; ΔP4 is the resistance of the salt spray filter; ΔP5 is the resistance of the high-efficiency filter; ΔP6 is the resistance of the shutter; ΔP7 is the air supply pressure;

[0029] The calculation formula of the resistance along the duct is:

[0030] ΔP1=L×R;

[0031] In the formula, L is the length of the duct; R is the specific friction resistance in the duct;

[0032] The calculation formula of elbow resistance is:

[0033]

[0034] Where ΔP2 is the elbow resistance; n is the number of elbows; ξ is the local resistance coefficient; V a is the air speed;

[0035] The calculation formula of the wind resistance of the evaporator module is:

[0036] ΔP3=ΔP′+ΔP″;

[0037] Wherein, ΔP3 is the wind resistance of the evaporator module; ΔP' is the dynamic pressure; ΔP" is the static pressure;

[0038] in,

[0039] Where, ω is the dynamic drag coefficient of the generator module;

[0040]

[0041] Where A1 is the influence coefficient of the condenser corrugated sheet; A2 is the influence coefficient of the cross row; A3 is the influence coefficient of the water film formed by dehumidification on the resistance; d eq is the equivalent diameter of the evaporator module; ω max is the static drag coefficient of the engine module.

[0042] Preferably, the heat dissipation calculation formula of the air duct in the rocket fairing environment system is:

[0043] Q f =k s s(t2-t1);

[0044] In the formula, Q f k is the heat dissipation of the duct; s is the thermal conductivity of the insulation material; s is the heat dissipation geometric area; t2 is the maximum external temperature; t1 is the calculated working temperature in the insulation layer.

[0045] Preferably, when selecting the launch vehicle fairing environmental system, filter selection calculation and unit vibration analysis are also required.

[0046] Compared with the prior art, this application has at least the following beneficial effects:

[0047] The selection method of the present invention can accurately calculate various parameters in the launch vehicle fairing environment system according to the operating conditions of the launch vehicle, and then determine the selection criteria of each component, thereby achieving effective selection of the launch vehicle fairing environment system and improving the accuracy of the selection. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0049] Figure 1 It is a schematic diagram of the overall process of the present invention. DETAILED DESCRIPTION

[0050] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0051] like Figure 1 As shown, a method for selecting a launch vehicle fairing environment system includes:

[0052] Step S1, determining the design parameters of the launch vehicle fairing environment system according to the operating requirements and environmental conditions of the launch vehicle fairing;

[0053] Step S2, determining the pipeline connection form and air conditioning connector form of the launch vehicle fairing environment system;

[0054] Step S3, calculating the selection parameters of the launch vehicle fairing environment system;

[0055] Step S4: selecting the launch vehicle fairing environment system according to the calculated launch vehicle fairing environment system selection parameters.

[0056] The launch vehicle fairing environment system includes an air conditioning unit, a generator unit, and pipes and air conditioning connectors connecting the air conditioning unit and the fairing. The air conditioning connector is preferably a ball lock pull-unlock type connector. The fairing flange is fixed to the fairing, and the air conditioning connector is assembled with the flange fastener. After the rocket body takes off, the fairing flange flies away with the arrow.

[0057] Among them, the selection parameters of the launch vehicle fairing environment system include: cooling capacity, cooling fresh air volume, heating capacity, humidification capacity, unit static pressure, air leakage rate and duct heat dissipation.

[0058] Among them, the working conditions and environmental conditions include temperature, relative humidity, ground wind speed and salt spray environment.

[0059] In this embodiment, the working conditions and environmental conditions are as follows:

[0060] Temperature: -25℃—40℃;

[0061] Relative humidity: 25% - 98%;

[0062] Ground wind speed: no more than 15m / s;

[0063] Salt spray environment: The area meets the severe severity requirements specified in GB / T4797.6-2013 "Environmental Conditions Classification Natural Environmental Conditions Dust, Sand, Salt Spray".

[0064] Among them, the design parameters include ventilation cleanliness, temperature in the instrument cabin, humidity in the instrument cabin, air supply form, electrical system, effective air exchange volume of the fairing, fairing ventilation inlet cross-section, ventilation hose diameter and total fresh air volume.

[0065] In this embodiment, the design parameter requirements are as follows:

[0066] Ventilation cleanliness: Class 100,000;

[0067] Temperature in the instrument cabin: 20℃±5℃, constant temperature;

[0068] Humidity in the instrument cabin: 35% to 55%, constant humidity;

[0069] Air supply form: full supply and full exhaust;

[0070] Power system: 380V / 3 phase / 5 wire / 50Hz;

[0071] Fairing effective air exchange volume: 80m3;

[0072] Fairing ventilation inlet section φ300mm;

[0073] The diameter of the ventilation hose is φ300mm;

[0074] Total fresh air volume: 2500m3 / h.

[0075] Furthermore, in order to ensure the launch success rate of the carrier rocket and meet the corresponding environmental requirements, the following requirements are also required:

[0076] The air conditioner can automatically adjust the temperature and humidity according to the temperature and humidity at the fairing air inlet, and is compatible with manual adjustment;

[0077] The fan, humidification, cooling and heating in the unit should have redundant design;

[0078] Air conditioning unit noise: ≤80dB;

[0079] The air conditioning unit should be equipped with lifting points and forklift fork points;

[0080] The air conditioning system needs to have a backup power supply and consider redundant design;

[0081] The air conditioning system is equipped with a shelter, which should meet the requirements of vehicle-mounted, long-distance transportation and outdoor long-term storage;

[0082] The air conditioning system adopts a branch multi-level control mode, and the multiple levels do not interfere with each other;

[0083] System components, circuits, functional boards and computer combinations should preferably be relatively mature products and technologies;

[0084] Consider the heat dissipation environment to avoid excessive equipment temperature, and provide necessary early warning and alarm measures;

[0085] Strong current and weak current should be routed separately, and communication lines should use twisted pair shielded wires to minimize interference;

[0086] The air conditioner should have the ability to store and record relevant data during the transition process, which can be easily read;

[0087] Air conditioning operation mode, status, fairing temperature and other parameters can be monitored and controlled in real time;

[0088] The air conditioner must work continuously and effectively during the transfer, and there should be no problems such as shutdown or overload protection during operation;

[0089] Cooperate to complete vehicle installation, commissioning, testing, problem investigation and rectification;

[0090] Cooperate to complete the whole process simulation test of transition;

[0091] Cooperate and provide transportation guarantee for the entire arrow transfer.

[0092] When selecting a launch vehicle fairing environmental system based on the calculated launch vehicle fairing environmental system selection parameters, the calculated launch vehicle fairing environmental system selection parameters can be compared with commercially available air-conditioning units and generator sets to screen out a launch vehicle fairing environmental system that meets the requirements.

[0093] At the same time, in the process of rocket transfer, the launch vehicle fairing environment system needs to continuously and uninterruptedly provide the required suitable temperature, humidity and clean air and other environmental requirements for the inside of the fairing. Its operating conditions are as follows:

[0094] Factory parking conditions;

[0095] From satellite plants to final assembly plants;

[0096] The transportation phase from the final assembly plant to the launch site;

[0097] Enter the process and launch phase (1 hour before launch).

[0098] The calculation formula for the cooling capacity in the rocket fairing environmental system is:

[0099] Q C =(k1A1+k2A2+k3A3)×△T C ;

[0100] In the formula, Q C is the cooling capacity; k1 is the comprehensive heat transfer coefficient of the front cone section of the fairing; A1 is the comprehensive heat transfer area of ​​the front cone section of the fairing; k2 is the comprehensive heat transfer coefficient of the column section of the fairing; A2 is the comprehensive heat transfer area of ​​the column section of the fairing; k3 is the comprehensive heat transfer coefficient of the inverted cone section of the fairing; A3 is the comprehensive heat transfer area of ​​the inverted cone section of the fairing; △T C Target temperature drop.

[0101] Table 1 Rocket fairing environmental system estimated usage data table

[0102]

[0103] The heat transfer coefficient of the fairing structure is calculated according to the following formula:

[0104]

[0105] In the formula,

[0106] k: fairing comprehensive heat transfer coefficient, unit W / (m 2 K);

[0107] α1: Heat transfer coefficient of the inner surface of the fairing, unit: W / (m 2 ·K), here we take 8W / (m 2 K);

[0108] α2: Heat transfer coefficient of the outer surface of the fairing, unit: W / (m 2 ·K), here we take 23W / (m 2 K);

[0109] δ i : thickness of the i-th layer structure of the fairing, unit: m;

[0110] λ i : Thermal conductivity of the i-th layer of the fairing, unit: W / (m 2 ·K).

[0111] The calculated comprehensive heat transfer coefficient of the front cone and column section of the fairing is 5.305W / (m 2 ·K), the inverted cone section is 5.934W / (m 2 ·K).

[0112] For hot environment conditions, air conditioning is required for cooling. The outside environment temperature is 35°C, and the target control temperature inside the fairing is 20°C, so the temperature difference is 15 degrees.

[0113] After calculation, the cooling capacity of the rocket fairing environment system is: Q C =14.2KW.

[0114] The calculation formula for the cooling fresh air volume in the rocket fairing environmental system is:

[0115]

[0116] Where V x is the cooling fresh air volume; ρ is the air supply density, unit: kg / m 2 ;h c h is the air supply enthalpy of air conditioning; i is the enthalpy of the control point inside the launch vehicle fairing.

[0117] In this embodiment, ρ is 1.225 kg / m 2 Assuming that the control point in the fairing is 20℃, 45% humidity, and the air supply temperature of the air conditioner is 15℃, 10% humidity, the corresponding enthalpy values ​​can be obtained through the calculation formula: 37.6kJ / kg, 17.9kJ / kg.

[0118] The calculated air supply volume is 2118m 3 / h, considering the redundant design, the high pressure fan is 2500m 3 / h selection.

[0119] The calculation formula for the humidification amount in the rocket fairing environmental system is:

[0120]

[0121] Where G is the humidification amount; d i is the humidity content at the air supply point; d c is the humidity content at the air inlet point.

[0122] With low temperature of 5℃, relative humidity of 25%, and moisture content of 1.41g / kg as the air inlet point, air supply parameters of 20℃, 45%, moisture content of 6.84g / kg, air supply volume of 2500m3 / h, and air supply density of 1.225kg / m3, the humidification amount is calculated as follows:

[0123] G=(6.84-1.41)×2500×1.225 / 1000=16.6kg / h.

[0124] The calculation formula for the heating capacity in the rocket fairing environmental system is:

[0125]

[0126] In the formula, Q h is the heating capacity; c is the specific heat capacity at constant pressure; △T h is the target temperature rise.

[0127] Electric heating has two functions, namely, it is used to warm up the air during refrigeration and dehumidification and to heat the air in a low temperature environment. Considering the heating condition of the service platform, during low temperature heating, taking the outside temperature of 5°C as an example, the air is heated to 20°C, and the constant pressure specific heat capacity c is taken as 1.01Kj / (kg·K).

[0128] The maximum heating capacity is: Q h =10.5KW.

[0129] The calculation formula for the static pressure of the rocket fairing environment system is:

[0130] ΔP=ΔP1+ΔP2+ΔP3+ΔP4+ΔP5+ΔP6+ΔP7;

[0131] In the formula, ΔP is the static pressure of the unit, in Pa; ΔP1 is the resistance along the air duct, in Pa; ΔP2 is the elbow resistance, in Pa; ΔP3 is the wind resistance of the evaporator module, in Pa; ΔP4 is the resistance of the salt spray filter, in Pa; ΔP5 is the resistance of the high-efficiency filter, in Pa; ΔP6 is the louver resistance, in Pa; ΔP7 is the supply air pressure, in Pa.

[0132] The calculation formula of the resistance along the duct is:

[0133] ΔP1=L×R;

[0134] Where, L is the length of the duct; R is the specific friction resistance in the duct;

[0135] The calculation formula of elbow resistance is:

[0136]

[0137] Where ΔP2 is the elbow resistance; n is the number of elbows; ξ is the local resistance coefficient; V a is the air speed;

[0138] The calculation formula of the wind resistance of the evaporator module is:

[0139] ΔP3=ΔP′+ΔP″;

[0140] Wherein, ΔP3 is the wind resistance of the evaporator module; ΔP' is the dynamic pressure; ΔP" is the static pressure;

[0141] in,

[0142] Where, ω is the dynamic drag coefficient of the generator module;

[0143]

[0144] Where A1 is the influence coefficient of the condenser corrugated sheet; A2 is the influence coefficient of the cross row; A3 is the influence coefficient of the water film formed by dehumidification on the resistance; d eq is the equivalent diameter of the evaporator module; ω max is the static drag coefficient of the engine module.

[0145] In this embodiment, the calculation process is as follows:

[0146] (a) Calculation of resistance along the duct

[0147] 1) Parameter selection

[0148] Two air ducts, each with a diameter of d = 300 mm and a length of L = 40 meters;

[0149] Duct air volume: G = 2500m 3 / h;

[0150] Duct roughness K = 0.2 mm;

[0151] 2) Calculation formula

[0152] Along-the-path resistance: ΔP1=L×R;

[0153] L is the length of the duct, in m; R is the specific friction resistance in the duct, in Pa / m;

[0154] Among them, the specific friction resistance in the air duct is:

[0155]

[0156] d is the diameter of the duct, in meters; V is the air velocity, in meters per second; λ is the resistance coefficient, which is affected by the fluid morphology:

[0157] When Re≤2000, that is, the fluid belongs to laminar flow, λ=64 / Re;

[0158] When 2000<Re≤0.32(d / K)1.28, that is, the fluid belongs to the turbulent smooth zone, λ=0.3164 / Re0.25;

[0159] When 0.32(d / K)1.28<Re≤1000(d / K), that is, the fluid belongs to the turbulent transition zone,

[0160]

[0161] When Re>1000(d / K), that is, in the turbulent rough zone, λ=0.11(K / d)0.25.

[0162] 3) Calculation results

[0163] When V=9.8m / s, it belongs to the turbulent transition zone. According to the formula, λ=0.0198, the specific friction resistance in the tube R=3.5Pa / m, and the resistance ΔP1=140Pa. Considering redundancy, ΔP1=200Pa.

[0164] (b) Elbow resistance calculation

[0165] 1) Parameter selection

[0166] Two air ducts, each with a diameter of d = 300 mm;

[0167] Wind speed in the air duct V = 9.8m / s;

[0168] Assume there are 5 90° elbows on the duct

[0169] 2) Calculation formula

[0170]

[0171] 3) Calculation results

[0172] From the table, we can see that ξ=1, then ΔP2=288Pa. Considering redundancy, we take ΔP2=350Pa.

[0173] (c) Calculation of wind resistance of evaporator module

[0174] Wind speed: V = 1.5m / s;

[0175] Air density at average temperature: ρ = 1.2 kg / m3

[0176] Dynamic pressure:

[0177] Static Pressure:

[0178] Among them, 1.1 and 1.2 are the influence coefficients of the condenser corrugated sheets and cross-rows respectively; 1.5 is the influence coefficient of the water film formed by dehumidification on the resistance;

[0179] Total wind pressure: Δp = Δp' + Δp" = 24.5Pa. Considering the resistance and redundancy of electric heating, ΔP = 30Pa.

[0180] The evaporator module is divided into 3 layers, so the total resistance of the evaporator module ΔP 总 =3ΔP=90Pa.

[0181] (d) Other resistance statistics

[0182] Salt spray filter: According to the parameters provided by the manufacturer, the initial pressure loss is 70Pa, the final pressure loss is 400Pa, and 300Pa is taken.

[0183] High efficiency filter: According to the parameters provided by the manufacturer, the initial pressure loss is 270Pa, the final pressure loss is 600Pa, take 400Pa.

[0184] Shutter resistance: 30Pa.

[0185] Air supply pressure: 500Pa.

[0186] (e) Calculation of total resistance

[0187] ΔP=ΔP1+ΔP2+ΔP3+ΔP4+ΔP5+ΔP6+ΔP7=1420Pa;

[0188] Therefore, the static pressure of the unit should be guaranteed to be P≥1450Pa. Considering the redundant design, the static pressure index of the unit is 1600Pa.

[0189] In addition, an air leakage rate analysis is also required: when the static pressure inside the unit is maintained at 700Pa in the positive pressure section and -400Pa in the negative pressure section, the air leakage rate of the unit is ≤2%; when the static pressure inside the unit is maintained at 1000Pa, the air leakage rate of the unit is not greater than 1%.

[0190] The calculation formula for the heat dissipation of the air duct in the rocket fairing environmental system is:

[0191] Q f =k s s(t2-t1);

[0192] In the formula, Q f k is the heat dissipation of the duct; s is the thermal conductivity of the insulation material; s is the heat dissipation geometric area; t2 is the maximum external temperature; t1 is the calculated working temperature in the insulation layer.

[0193] Calculation of heat dissipation of the air duct in this embodiment:

[0194] Working condition 1:

[0195] The thermal conductivity k of the insulation material is 0.03W / (m·℃);

[0196] Heat dissipation geometric area (take the area of ​​the wind duct outside the swing arm), s = 23.87m 2 ;

[0197] Pipe wall thickness 0.0325m

[0198] The maximum external temperature, t2, is +40℃;

[0199] The calculated working temperature in the insulation layer is t1 +20℃.

[0200] Calculation result Q f1 =440W.

[0201] Condition 2:

[0202] The maximum external temperature, t2, is +40℃;

[0203] The calculated working temperature in the insulation layer is +25℃.

[0204] Calculation result Q f2 =330W.

[0205] In addition, when selecting the launch vehicle fairing environmental system, filter selection calculations and unit vibration analysis are also required.

[0206] Filter selection calculation:

[0207] In order to achieve the cleanliness level of 100,000, high-efficiency filters need to be arranged on the air duct of the system. High-efficiency filters are mainly used to capture dust particles below 0.5um and various suspended solids. Ultra-fine glass fiber paper is used as filter material, offset paper, aluminum film and other materials are used as partition boards, and are bonded with wooden frames and aluminum alloys.

[0208] In order to reduce the replacement of high-efficiency filters, this system is designed to add a medium-efficiency filter (salt spray filter) at the air inlet of the evaporator, which can effectively protect the high-efficiency filter. The medium-efficiency filter is arranged at the evaporator inlet, the high-efficiency filter is behind the evaporator, and the medium-efficiency filter is arranged at the air inlet, which is convenient for disassembly, cleaning and replacement.

[0209] The medium efficiency filter uses a fine pleated filter, and the high efficiency filter uses a high efficiency filter with a partition.

[0210] The filter is equipped with a filter pressure difference sensor. When the filter pressure difference exceeds the set value, the filter will be removed and replaced to avoid excessive resistance, which will affect the air supply volume and air cleanliness.

[0211] Unit vibration analysis:

[0212] Air supply volume 2500m 3 / h, the static pressure of the unit is 1600Pa. According to GB / T14294 Section 6.3.10, the sound pressure level of the unit is 76.8dB, and the unit design index should meet ≤80dB. In order to reduce the vibration of the unit, the following vibration reduction design is carried out:

[0213] The strong rigid structure design of the air conditioning unit's external bracket makes the overall structure have a higher natural frequency, which can improve the impact resistance;

[0214] The refrigeration pipeline of the unit adopts stainless steel hoses and shock-absorbing damping blocks with good shock-absorbing performance;

[0215] For the indoor unit of the control room refrigeration system, vibration isolators are installed at the bottom and back of the indoor unit;

[0216] Small and rigid design of electrical cabinet;

[0217] High-power electrical appliances are rationally designed and installed in lower locations.

[0218] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0219] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0220] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0221] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for selecting a launch vehicle fairing environment system, characterized in that: include: Determine the design parameters of the launch vehicle fairing environmental system according to the launch vehicle fairing operating requirements and environmental conditions; Determine the piping connection form and air conditioning connector form of the launch vehicle fairing environment system; Calculate the selection parameters of the launch vehicle fairing environmental system; According to the calculated launch vehicle fairing environment system selection parameters, the launch vehicle fairing environment system is selected; The selection parameters of the launch vehicle fairing environment system include: cooling capacity, cooling fresh air volume, heating capacity, humidification capacity, unit static pressure, air leakage rate and air duct heat dissipation; The calculation formula for the cooling capacity in the rocket fairing environmental system is: ； In the formula, is the cooling capacity; is the comprehensive heat transfer coefficient of the front cone section of the fairing; is the comprehensive heat exchange area of ​​the front cone section of the fairing; is the comprehensive heat transfer coefficient of the fairing column section; is the comprehensive heat exchange area of ​​the fairing column section; is the comprehensive heat transfer coefficient of the inverted cone section of the fairing; Comprehensive heat exchange area of ​​the inverted cone section of the fairing; The target temperature drop; The calculation formula for the cooling fresh air volume in the rocket fairing environmental system is: ； In the formula, Fresh air volume for cooling; is the air supply density; is the air supply enthalpy of the air conditioner; is the enthalpy of the control point inside the launch vehicle fairing; The calculation formula for the humidification amount in the rocket fairing environmental system is: ； In the formula, is the humidification amount; It is the humidity content at the air supply point; is the humidity content at the air inlet point; The calculation formula for the heating capacity in the rocket fairing environmental system is: ； In the formula, To generate heat; is the specific heat capacity at constant pressure; is the target temperature rise; The calculation formula for the static pressure of the rocket fairing environment system is: ； In the formula, is the static pressure of the unit; is the resistance along the duct; is the elbow resistance; is the wind resistance of the evaporator module; is the salt spray filter resistance; is the high efficiency filter resistance; is the shutter resistance; is the air supply pressure; The calculation formula of the resistance along the duct is: ； In the formula, is the length of the air duct; is the specific friction resistance in the air duct; The calculation formula of elbow resistance is: ； In the formula, is the elbow resistance; is the number of elbows; is the local resistance coefficient; is the air speed; The calculation formula of the wind resistance of the evaporator module is: ； In the formula, is the wind resistance of the evaporator module; is dynamic pressure; is the static pressure; in, ; In the formula, is the dynamic drag coefficient of the engine module; = ； In the formula, is the influence coefficient of the condenser corrugated sheet; is the influence coefficient of the cross row; is the influence coefficient of the water film formed by dehumidification on the resistance; is the equivalent diameter of the evaporator module; is the static drag coefficient of the engine module; The calculation formula for the heat dissipation of the air duct in the rocket fairing environmental system is: ； In the formula, The heat dissipation of the air duct; is the thermal conductivity of the insulation material; is the heat dissipation geometric area; is the maximum outside temperature; Calculate the operating temperature inside the insulation layer.

2. The launch vehicle fairing environment system selection method according to claim 1, characterized in that: The working requirements and environmental conditions include temperature, relative humidity, ground wind speed and salt spray environment.

3. The launch vehicle fairing environment system selection method according to claim 1, characterized in that: The design parameters include ventilation cleanliness, temperature in the instrument cabin, humidity in the instrument cabin, air supply form, electrical system, effective air exchange volume of the fairing, fairing ventilation inlet cross-section, ventilation hose diameter and total fresh air volume.

4. The launch vehicle fairing environment system selection method according to claim 1, characterized in that: When selecting the launch vehicle fairing environmental system, filter selection calculations and unit vibration analysis are also required.

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