SAE AIR 1343B-2013 Liquid Propellant Gas Generation Systems《液体推进剂气体发生系统》.pdf

《SAE AIR 1343B-2013 Liquid Propellant Gas Generation Systems《液体推进剂气体发生系统》.pdf》由会员分享，可在线阅读，更多相关《SAE AIR 1343B-2013 Liquid Propellant Gas Generation Systems《液体推进剂气体发生系统》.pdf（53页珍藏版）》请在麦多课文档分享上搜索。

1、 _ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising ther

2、efrom, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2013 SAE International All rights reserved. No part of this

3、publication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-49

4、70 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AIR1343BAEROSPACE INFORMATION REPORT AIR1343 REV. B Issued 1981-11 Revised 1992-

5、03 Reaffirmed 2007-11 Stabilized 2013-06Superseding AIR1343A Liquid Propellant Gas Generation Systems RATIONALE This document has been determined to contain basic and stable technology which is not dynamic in nature. STABILIZED NOTICE This document has been declared “Stabilized“ by the A-6C6 Power S

6、ources Committee, and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability of technical requirements. Newer technology may exist. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo repro

7、duction or networking permitted without license from IHS-,-,-TABLE OF CONTENTS1. SCOPE .42. REFERENCES .43. SYSTEM CONSIDERATIONS74. LIQUID PROPELLANTS.84.1 Monopropellants 84.2 Bipropellants 154.3 Safety and Handling.155. PROPELLANT TANKS.155.1 Positive Expulsion Devices 175.1.1 Elastomeric Bladder

8、s .175.1.2 Metallic Bladders175.1.3 Bellows Tanks 175.1.4 Piston Tanks 186. PROPELLANT EXPULSION SYSTEMS 186.1 Stored Pressurized Gas System 186.1.1 Pressurization Gas.196.1.2 Pressurant Storage Bottle196.1.3 Pressurization Gas Valve.206.1.4 Pressurant Regulator .206.1.5 Advantages and Disadvantages

9、 206.2 Propellant Pump 216.2.1 Positive Displacement Propellant Pump 216.2.2 Hydrodynamic Fuel Pump21SAE AIR1343B Page 1 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE OF CONTENTS (Cont

10、inued)6.2.3 Advantages and Disadvantages of Pumps 236.3 Solid Propellant Gas Pressurization.236.3.1 Advantages and Disadvantages of Solid Propellant Pressurization 246.4 Differential Area Piston Fuel Tank Gas Generator System246.4.1 Advantages and Disadvantages 266.5 Cryogenic Storage .266.6 Hyperbo

11、lic Propellant Injection.287. PROPELLANT CONTROLS .297.1 Pressure Modulated Control 297.2 Pulse Modulated Control318. DECOMPOSITION (COMBUSTION) CHAMBER AND INITIATION SYSTEM 318.1 Monopropellant Decomposition Chamber318.1.1 Solid Propellant Initiators .328.1.2 Hyperbolic Start Systems.328.1.3 Therm

12、al Start Systems.358.1.4 Catalytic Initiators.358.2 Bipropellant Combustion Chamber 378.2.1 Hyperbolic Combustion378.2.2 Spark Ignitions .379. SIZING METHODS.389.1 Propellant Consumption.389.1.1 Specific Propellant Consumption (SPC) 399.1.2 Part Load Propellant Consumption 399.1.3 Specific Impulse (

13、ISP).409.1.4 Characteristic Exhaust Velocity (C*) 409.2 Propellant Tank Sizing .409.2.1 Spherical Tank .419.2.2 Cylindrical Tank429.3 Propellant Expulsion System Sizing.459.3.1 Cold Gas Expulsion .459.3.2 Solid Propellant Gas Generator Expulsion System479.4 Decomposition Chamber Sizing.52TABLE 1 Mon

14、opropellant Characteristics9TABLE 2 Constituents of Hydrazine Blends With Depressed Freezing Points .12TABLE 3 Physical and Chemical Properties of Hydrazine Monopropellants.13TABLE 4 Typical Bipropellant Characteristics .16TABLE 5 Characteristics of Typical Propellant51SAE AIR1343B Page 2 of 52_ Cop

15、yright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE OF CONTENTS (Continued)FIGURE 1 LPGG System Block Diagram.4FIGURE 2 Freezing Point Versus Percent H2O in N2H4/H2O Blend 11FIGURE 3 Storage Data on H

16、ydrazine Blends.14FIGURE 4 Pressurized Propellant Expulsion System Block Diagram 18FIGURE 5 Pumped Propellant System.22FIGURE 6 Solid Propellant Expulsion System .23FIGURE 7 Variable Demand Prepackaged Gas Generator .25FIGURE 8 Supercritical Storage System26FIGURE 9 Subcritical Storage System .27FIG

17、URE 10 Hyperbolic Propellant Injection System.28FIGURE 11 Speed Control Systems Pulse and Pressure Modulated 30FIGURE 12 Solid Propellant Dual Start System .33FIGURE 13 Solid Oxidizer Decomposition Chamber .34FIGURE 14 Liquid Oxidizer Injection Systems .36FIGURE 15 Cylindrical Tank.42FIGURE 16 Cylin

18、drical Tank (Convex and Concave).43FIGURE 17 Grain Size .48FIGURE 18 Burning Rate and KnVersus Pressure Typical Propellant 50SAE AIR1343B Page 3 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,

19、-1. SCOPE:This information report presents a preliminary discussion of liquid propellant gas generation (LPGG) systems. A LPGG system, as used herein, is defined as a system which stores a liquid propellant and, on command, discharges and converts the liquid propellant to a gas. The LPGG system can

20、interface with a gas-to-mechanical energy conversion device to make up an auxiliary power system. Figure 1 shows a block diagram of LPGG system components which include a propellant tank, propellant expulsion system, propellant control and a decomposition (or combustion) chamber.FIGURE 1 - LPGG Syst

21、em Block DiagramThe purpose of this report is to provide general information on the variety of components and system arrangements which can be considered in LPGG design, summarize advantages and disadvantages of various approaches and provide basic sizing methods suitable for initial tradeoff purpos

22、es.2. REFERENCES:2.1 Compatibility of Hydrazine Blend Fuels in metal containers at elevated temperatures - CPIA Publication 160, December 19572.2 Thermal Stability of Mixed Hydrazine Fuels, CPIA Publication 160, December 19572.3 MHF-5 Storage Data - USAF Propellant Handbooks Hydrazine Fuels Vol. I A

23、FRPL-TR-69-149, March 19702.4 “Hydrogen Peroxide Handbook” AFRPL-TR-67-144, July, 1967 Rocketdyne, a Division of North American Aviation Inc., Canoga Park, CaliforniaAir Force Rocket Propulsion LaboratoryEdwards Air Force Base, California2.5 “USAF Propellant Handbooks Hydrazine Fuels” Volume I, Marc

24、h 1970 Contract No. F04611-69-C-0005Bell Aerospace CompanyDivision of Textron, Buffalo, N.Y.Air Force Rocket Propulsion LaboratoryEdwards Air Force Base, CaliforniaSAE AIR1343B Page 4 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking

25、 permitted without license from IHS-,-,-2.6 “Compatibility of Rocket Propellants with Materials of Construction”Defense Metals Information CenterBattelle Memorial InstituteColumbus 1, OhioOTSPB161215September 15, 1960 DMIC Memorandum 652.7 “The Handling and Storage of Liquid Propellants” March 1961O

26、ffice of the Director of Defense Research however, the possible toxicity of liquid hydrazine is a potential problem.SAE AIR1343B Page 8 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 1

27、- Monopropellant CharacteristicsViscosity, 77 F (25 C)SAE AIR1343B Page 9 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4.1 (Continued):Anhydrous hydrazine (N2H4) is a commonly used monoprop

28、ellant in aerospace applications. This monopropellant exemplifies all of the advantages listed in the above paragraph, and in addition it is readily decomposed upon contact with a spontaneous catalyst such as Shell 405. The major restriction to use of anhydrous hydrazine is its freezing point of app

29、roximately 34 F (1 C).The environmental requirements in many applications, therefore, eliminate the use of anhydrous hydrazine. To meet these requirements, a freezing point depressant is added to the hydrazine. These depressants include water, monomethyl hydrazine and hydrazine nitrate. Typical fuel

30、s with depressed freezing points, which contain these additives are Mixed Hydrazine Fuels (MHF) such as MHF-3, MHF-5 and Monopropellant Gas Generator Propellants (MGGP) such as MGGP-1, and hydrazine-water mixtures. The freezing point of hydrazine can be depressed to near -65 F (-54 C) by the additio

31、n of approximately 30% water. Figure 2 shows the freezing point as a function of water content. Hydrazine energy content decreases with water addition. As an example, a 70% hydrazine, 30% water blend has less than 65% of the available energy (BTU/lb) (J/kg) of undiluted anhydrous hydrazine. Table 2

32、shows constituents of various hydrazine blends with depressed freezing points and Table 3 shows their physical and chemical properties.MHF-3 and MHF-5 both contain monomethyl hydrazine, a carbon containing compound. These carbon containing compounds normally cannot be used with catalytic decompositi

33、on systems since the catalyst surface quickly becomes coated with carbon and is rendered useless for further reactivity with incoming propellant. MGGP-1 and hydrazine-water mixtures can be used with catalytic decomposition chambers. All of the above mentioned fuels can be used in a thermal type cham

34、ber.Storability, energy content, material compatibility, and safety become the parameters used in selecting a fuel for a particular application. The Monopropellant blends which contain either hydrazine nitrate or hydrazine azide exhibit high energy levels and good reactivity, however, they have limi

35、ted storage capability at elevated temperatures, as determined by measuring pressure rise in a sealed propellant tank. Pressure rise rates of the nitrate and azide blends are high compared to monomethylhydrazine blends such as MHF-3 or water-hydrazine blends. MHF-5 is a high nitrate content blend an

36、d MGGP-1 and 70/20/10 are moderate nitrate content blends.As a general guideline for this document, “long-term storage“ is measured in years. Typical monopropellant and pressurization system tankage storage requirement for aircraft emergency power units is three years. Reference to “short-term stora

37、ge“ generally relates to months. Short-term storage capability is adequate for many launch and space vehicle applications where propellant loading is done just before launch and tank storage time requirements during the mission are short.Most of the published data of propellant capability for long-t

38、erm storage are in the 100 to 165 F (38 to 74 C) range. Decomposition of mixed hydrazine fuels is temperature dependent. The higher the temperature, the higher the rate of fuel decomposition. Also, it has been shown that the mixed hydrazine fuels do not attain a constant slope for pressure rise rate

39、 until approximately 60 days.SAE AIR1343B Page 10 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-FIGURE 2 - Freezing Point Versus Percent H2O in N2H4/H2O BlendSAE AIR1343B Page 11 of 52_ Copy

40、right SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 2 - Constituents of Hydrazine Blends With Depressed Freezing PointsSAE AIR1343B Page 12 of 52_ Copyright SAE International Provided by IHS under lice

41、nse with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE 3 - Physical and Chemical Properties of Hydrazine MonopropellantsSAE AIR1343B Page 13 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or network

42、ing permitted without license from IHS-,-,-4.1 (Continued):Reports have been published (2.1 and 2.2) on storage tests of mixed hydrazine fuels at temperatures of 100 to 160 F (38 to 74 C) in laboratory and field experiments while in contact with various tankage materials. MHF-3 was shown to be stora

43、ble for three years or more in 1100, 2024, and 6061 aluminum, 304 stainless and Ti-6Al-4V alloys, although analysis of the fuel blends, prior to and after storage, ascertained that some fuel decomposition occurred in all storage containers.Figure 3 shows elevated temperature long-term storage data f

44、or MHF-3 and 70-20-10. Five year storage appears practical with either of these fuels. Storage data on MHF-5 and MGGP-1 are also shown.FIGURE 3 - Storage Data on Hydrazine BlendsSAE AIR1343B Page 14 of 52_ Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4.2 Bipropellants:A bipropellant system uses a fuel and an oxidizer, which when mixed, undergo an exothermic reaction (combustion), releasing energy in the form of hot gases. Ig