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INFORMATION U S OvpartI t of Cvm tome Spwingfied -PT ROPULSION LABORATORY LABORATORIES AIR FORCESYSTEMS CALIFORNIA Government specifications, or other data a definitely Government procurerAent operation, the Government no responsibility, gation whatsoever, and the fact that the Government nM-ay have formulated, or in'any way spe6ifications, regarded by implication or otherwise, as licensing holder or any other person or corporation, any rights or permission to manufacture, use, or sell that may in any way be related i ICle kff MU~lIi" lit il IA. uli/v L -co lK - AfL f/r 4 UNCLASSIFIED Classification (Security classilication of title, body of Abstract and indexin annotation inu&t be entered when the overall report is classilied) I. ORIGINA rING ACTIVITY (Cwporate author) Za. REPORT SECURITY CLASSIFICATION LUNCLASSIFIED Rocket Propulsion Laboratory California 3. REPORT TITLE Propulsion -Project Outgrowth 4. OESCRIPTIVE NOTES (7ype ofoeport and inclusive (1 January 1970 through 31 December 19701 5- AUTHOR(S) name. middle Jr.. Editor 9Q. CONTRACT Va. ORIGINATOR'S b, PROJECT (Any other that may be this report) 10. OISTR1IUTION document has been approved for public release and :-ale; its d.stribution unlimited. It SUPPLEMENTARY 12. SPONSORING MILITARY Force Rocket Propulsion Laboratory Systems Command. 13. AB*ZRACT Astudy was conducted by an ad hoc group within the Air Force Rocket Propulsion Laboratory the calendar year of 1970 in an attempt to the major propulsion developments that may occur in the next 30 to 40 yearE, This report evaluates the future of conventional chemical rocketry based on thermodynamic principles and revolutionary conceptual approaches to system applications. Advanced concepts falling under the general headings of Thermal, Propulsion potential. report does not define a long list of very technology program subjects, designed to encourage and motivate and interested scientists and engineers again strive for IFropulsion Concepts.' ll ll ll II- UNCLASSIFIED Security Cla.tficati. UNCLSSTIED ciassification Propulsion IASSIIF-DD AFRPL-TR-7Z-31 ADVANCED PROPULSION CONCEPTS bee approved for public its distribution unlimidted. PROPULSION LABORATORY LABORATORIES SYSTEMS COMMAND UNITED STATES CALIFORNIA "All nen rea; bu noteqully.Thos wh notn equally possible." E. LAWR.ENCE "The Seven of XWisdom' considerable individuals. Propulsion Laboratory. individuals contributions Lt. Stanley L. Silver- Glassmeyer B. Mead, Jr. Mr. Donald This report includes a series of advanced propulsion ated during the -alendar year of 1970 under an in-house "Project Outgrowth." Commander, -c Propulsion Laboratory --tudy was within the Propulsion- Laboratory predict the major propulsion developments mz.y occur in the next This report conventional etry based on thermodynamic principles revolutionary conceptual approaches applications. Propulsion, Propulsion and Photon are evaluated degree necessary define their potential. not define a long list technology but is designed and motivate and interested scientists and engineers for "Advanced Propulsion TABLE OF CONTENTS "ITRODUCTION CHEMICAL PROPULSION CHAPTER 1-1. INHERENT LIMITATIONS OF CHEMICAL CHAPTER 1-2. ROCKET PROPELLANT- IDEAS.... Liquid Ozone. .. Nitrogen to Support Combustion .. .................1-22 Tripropellants. Solid Hydrogen Propellant System. .......................1-34 CHAPTER 1-3. ROCKET SYSTEM Infinitely Nozzleless Solid Rocket -~Sustained Detonation Propulsion (Solid or Liquid) 1-4. SUMMARY Part IReferences. PART 11 --NONCHEMICAL PROPULSION Electrothermal Thermonuclear Propulsion (Fusion) Laser Propulsion PROPULSION. Electrostatic Thrusters. Propulsion. -Electrostatic Satellite-Dra~g Electromfagnetic-Spacecraft Propulsion Superconducting Accelerator Antigravity Propulsion PROPULSION Antimatter for Propulsion Air-Scooping SUPERFICIALLY ILLUSTRATIONS Effect of Pressure Ratio on Specific 1-2 Air-Augmented Rocket 1-3 Sea Le ,el Performance and Density of Systems 1-4 Altitude Performance Payload Advantage 1-6 Infinite Staging Performance 1-7 Irfinite Stagi'ig Performan. Increase ..... 1-8 Nozzleless Design Variations .... .......... ...1-48 1-9 initial Performance Model (End-Burner) .... ....... cof Reacting Possible Application End-Burner). 1-12 Maximumn Values For Water-Launched Rocket .. Water-Launched Decomposition Resistojet 11-2 Evacuated Concentric Tubes Resistojet Concept 11-3 Core-flow Pattern in a Constricted Theoretical Specific Impulse Versus Temperature for Candidate Propellants Cross Sections for D-T, D-D (Total) & D-He Power Balance 11-9 Experimental OF ILLUSTRATIONS General Fusion Propulsion Problem .. ................11-33I Il-I I Magnetically Confined System-s .. ....................11-34j efomneFetrsfo .,oplinSystems 1116 Ramjet Required Temperature Ratio. Required Laser Power JI-18 Performance Laser Propulsion Diameter of Spot Versus Tracking Lens Diameter. . U-2 i Diameter of Spot Versus Tracking Lens Diameter. 11-22 Diameter of Spot Versus Tracking Lens Diameter 11-23 Isp Versus Power Requiremneit Powe~r Delive red at 1000 psi Ch imber H1-25 Various Pulsed Plasma Accelerators. ................11-72 Propulsion Engine 11-27 Electron Bombardment Engine .. ....................11-81 Colloid Thruster. Alfven Wave Propulsion 11-30 Characteristics of a Gonducto:-- a Magnetic LIST OF ILLUSTRATIONS (Cont'd) a 11-31 MHD Wings of Alfven Wave Device .......... .. 11-99 11-32 Arrangement of Electrostatic Spheres ...... H.-104 11-33 Electrostatic Sphere Cross Section ........ ... 11-105 "11-34 Sandiwich Structure Composed of Quartz 11-108 11- 35 Schematic of Satellite in Earth Orbit...................Il-lZ 11-37 Schematic of Solenoid Coil 11-38 Diagram of Solenoid Coil in Earth Orbit. 11-39 Status of Superconducting Materials ...... ...... 11-122 11-4 1 Shielded and Partially Shielded for a Dipole 11-42 Maneuvering with the Solar Sail ... ....... ... .11-145 of Orbital 11-44 Propulsion GRAVIMETRIC OF FORMATION CONVENTIONAL PERFORMANCE COMvPARISONS CONVERSION EFFICIENCIES PROPERTIES- PERFORMANCE OZONE-OXYGEN (LIQUIDS). PERFORMANCE MONOPROPELLANT COMPARISONS OF STULTENE. 18--8 RELATIVE PERFORMANCE CAPABILITY NfQ_2Z-LELESS OBTAINABLE VELOCITIES...... ROT-HERMAL PROPULSION EM PERFORMANCE PERFORMANCE PERFORMANCE FUSION PROPULSION CONCEPTS., CLASSIFICATION ELECTROMAGNETIC ACCELERATORS ELECTROSTATIC PERFORMANCE PERFORMANCE OF IPARTICLE ACCELERATOR INTRODUCTION in-chem-al propulsion wifllome from evolutinatry ixhprovements ixv propellants, packaging, effikiency, ruggedness and jystem flexibility. These individual rnents may be combined for specific applications to produce significant in range and/or payjload capability. In addition, increases Sisercice life with- ittenda:rt cost -reductions- de expected to-be achieved in-the-next g-neration f inisile -systems. Much o, the -current Air rocket propulsion technology program is: structured to make Spotential improvements a reality within the next five to ten years. The of the stud::::contained i: this:docu: ent, however, and stimulate transitions- to concepts beyond conventional chemical roket propi4sion -Which,_ if pur-sueA, -w uld brinag about substantial step improvemet -in pr6-prdisionprf-r~ie During (thp caendar yeat0-: 4970, an ad-hoc group within the Air Force Rocket-Prbpulsioil-Laborator (-AFRPL) conducted a study of -Advanced Propulsiow-COncept6'in an attempt to predidt the-propulsion developments and breakthroughS- that-ina.-occur in the next 30 to-40 years. Various Government agencies, educational institutions, industries, and- individUals contacted and encouraged to submit inventions or suggestions propulsion and related sciences. Propulsion-was br oadly defined as any technique for transmitting a mass from one point to another in an environment. Contributors were encouraged to apply unrestricted thifiking in approaching the problem of proprusion. The basic idea was to re-establish free thinking .2nd ezeativity existed during late _1950s and early 1960s, an inventiveness which to-a large extent appears to-have been lost during more recent times. The ad hoc com-ittee operated under a self-imposed rule that -restricted its efforts to evolutionary chemical rocket concepts offering at -least a 25 -to 30 percent improvement in propulsion capability. Ideas not meeting this requirement, but offering immediate potential to conventional p ropulsion were promiptly -passed on to Staff and Di-esion Offices within the AFRPL for consideration as routine business. Most of the ideas qualifying for. committee action were sent to various individuals within the AFRPL for study and analysis. Several ideas that were substantially outside the technical charter or province of the AFRPL were sent to supporting research laboratories such as the Air Force Cambridge Research Labora- fory, the Air Force Aerospace Research Laboratories, and the Air Scientific Research, for analysis. Ideas that had a good ity of materially advancing the current state of the art in propulsion were evaluated with a greater degree of thoroughness. To this end, a number involving analysis and experimentation were either made under tract or conducted within the AFRPL. - was taken-bythe One -portion effort was de'voted-to inherent limitations of chemical and its useoin Comparison the theoretical est-alished improvements from ch6calrockets futre. This set a baseline which advanced could be compared. Ideas concerned with chemi- cal rocketry-usually fell into one of two general categories. lants-were to reassure no significant improvements beeno eoverlooked this area. novel ideas rocket sys- were examined-in attempt to one or more of the-inherent limitations of chemical the second portion study consisting pulsion-technique s involving other than categdries. under--what-r-might called "Unknown -fell- the- conet of-psychic -which-psyciuinesis illustrates extent-to*which unrestricted-thinkl g-was applied. This category -of prop-ulion-is-discussed briefly in Appendix I. The second-