Chapter 1. INTRODUCTION - TB-9-1377-2000006
Table I. Physiological Limitations for Personnel Ejection
Chapter 2. DESCRIPTION OF PROPELLANT ACTUATED DEVICES
Figure 1. Mechanically operated initiator.
Stroking Devices - TB-9-1377-2000010
Figure 3. Operation of a conventional catapult.
Figure 4. Typical remover.
Table VI. Comparative Data for Removers
Figure 5. Oil damped thruster.
Table VII. Comparative Data for Ejectors
Releases.
Figure 10. Electric ignition element.
Figure 11. F-104B Escape System, schematic diagram.
Capsule escape systems.
Figure 12. Nose capsule.
Figure 13. Nose capsule escape system, schematic diagram.
Figure 14. "Off the runway" ejection sequence.
Figure 15. T4 gas generator.
Energy Transmission in Systems.
CHAPTER 3. BASIC DESIGN
Figure 18. Pressure-time curve for system of figure 17
Weight and Size (Envelope)
Heat Loss
Chapter 4. DESIGN TECHNIQUES
Figure 20. Curves for estimating performance.
Peak Pressure
Figure 21. Curve for approximating propellant charge for catapults and removers.
Section III. DESIGN STRENGTH CALCULATIONS
Safety Factors
Figure 23. Biaxial and triaxial strength curves (sheet 1 of 2).
Figure 23. Biaxial and triaxial strength curves (sheet 2 of 2).
Section IV. DESIGN PROCEDURES
Stroking Devices - TB-9-1377-2000038
Section V. COMPONENT DESIGN
Table VIII. Sizes of Existing Cartridge Cases
Figure 28. Percussion primer.
Body and Chamber
Firing Mechanism
Table XI. Firing Pin Protrusions and Diameters
Table XII. Firing Pins and Shear Pins Used in Propellant Actuated Devices
Figure 35. Mechanically operated firing mechanism.
Figure 36. Thruster looking mechanism.
Section VI. SPECIAL PROBLEMS
Figure 39. Floating piston and thermal expansion chamber.
Protective Coatings
Dissimilar Metals.
Chapter 5. BALLISTIC DESIGN AND ANALYSIS
Propellant Parameters
Refinements to First Order Approximations
Figure 43. Desired pressure vs time curve.
Use of "Ideal" acceleration vs. time curves to estimate stroke length.
Use of "Ideal" acceleration vs. time curves to estimate stroke length. (Cont)
Figure 46. "Ideal" pressure, acceleration, velocity, and travel vs time curves for a three-tube catapult.
Use of Estimated Acceleration vs Time Curve to Determine Approximate Propellant Web.
Estimation of Propellant Charge Weight.
Thrusters.
Development of Propellant Charge Design
Use of Experimental Pressure vs Time Curve to Refine Propellant Charge Design
Rate of pressure rise.
Section II. MATHEMATICAL ANALYSIS OF INTERIOR BALLISTICS
Figure 48. Pressure and quantity of propellant gas vs volume on logarithmic scales.
Equations of motion.
Table XlV. Coefficients for Form Function (Sewn-Perforated Propellant)
Equation of state.
Table XV. Values of Energy Balance Terms Upon Completion of Stroke
Damping Requirement
Bypass Requirements.
Figure 51. Experimental and calculated bypass pressure for MSA1 Thruster.
Initiators
Chapter 6. DESIGN EXAMPLES
Stroke Time.
Component Layout - TB-9-1377-2000077
Figure 54. Expansion ratio with annular volume.
Tubes
Figure 57. Inside tube for catapult.
Figure 58. Telescoping tube for catapult.
Trunnion.
Trunnion. (cont)
Block.
Firing Mechanism .
Locking Mechanism
Minor Parts
Section III. M3A1 THRUSTER
Component Layout - TB-9-1377-2000089
Cartridge
End Cap
Figure 69. End cap of thruster.
End Sleeve and Locking Mechanism
Figure 7. Breech for thruster.
Figure 74. Thruster firing pin.
First Order Approximations
Figure 76. Initiator component layout.
Figure 79. Cartridge retainer.
Figure 81. Initiator cap.
Figure 82. Firing pin for initiator.
Firing-Pin Housing
Chapter 7. PERFORMANCE EVALUATION
Figure 86. Teat instrumentation.
Figure 88. Piezoelectric amplifier.
Strain Resistance Gages.
Figure 89. Coupling network for use with bridge-type gages.
Travel Measurement.
Figure 92. Schematic diagram of linear electrolytic positioning transducer.
Typical Instrumentation Setup.
Figure 94. Oscillogram obtained with test setup of figure 93.
Figure 95. Vertical test tower.
Figure 96. Test tower showing catapult, transducers, and wiring on test track.
Figure 97. Another type of vertical test tower.
Figure 99. Air cylinder for testing propellant actuated devices.
Figure 101. Teat setup for initiators.
Prototype Evaluation.
Qualification and Analysis Evaluation Program
Table XVII. Qualification and Analysis Evaluation Schedule
Figure 102. Temperature-altitude-humidity test cycle.
Performance Evaluation.
Appendix I. CONVERSION OF DISTORTION ENERGY EQUATION TO MORE USEFUL FORMS FOR PROPELLANT ACTUATED DEVICES
Biaxial Stresses.
Appendix II. TABLE OF WALL RATIOS
TABLE OF WALL RATIOS (cont)
Appendix III. DERIVATION OF EQUATION USED IN DETERMINING LENGTH OF ENGAGEMENT OF THREADS
Appendix IV. DERIVATION OF WEB THICKNESS EQUATION FOR TELESCOPING TUBE DEVICES
Appendix V. DERIVATION OF EQUATION FOR BYPASS TUBE PRESSURE
DERIVATION OF EQUATION FOR BYPASS TUBE PRESSURE (cont)
Appendix VI. REFERENCES
GLOSSARY - TB-9-1377-2000130
GLOSSARY (cont) - TB-9-1377-2000131
TB-9-1377-200 Propellant Actuated Devices Manual
Table I. Physiological Limitations for Personnel Ejection
Chapter 2. DESCRIPTION OF PROPELLANT ACTUATED DEVICES
Figure 1. Mechanically operated initiator.
Stroking Devices - TB-9-1377-2000010
Figure 3. Operation of a conventional catapult.
Figure 4. Typical remover.
Table VI. Comparative Data for Removers
Figure 5. Oil damped thruster.
Table VII. Comparative Data for Ejectors
Releases.
Figure 10. Electric ignition element.
Figure 11. F-104B Escape System, schematic diagram.
Capsule escape systems.
Figure 12. Nose capsule.
Figure 13. Nose capsule escape system, schematic diagram.
Figure 14. "Off the runway" ejection sequence.
Figure 15. T4 gas generator.
Energy Transmission in Systems.
CHAPTER 3. BASIC DESIGN
Figure 18. Pressure-time curve for system of figure 17
Weight and Size (Envelope)
Heat Loss
Chapter 4. DESIGN TECHNIQUES
Figure 20. Curves for estimating performance.
Peak Pressure
Figure 21. Curve for approximating propellant charge for catapults and removers.
Section III. DESIGN STRENGTH CALCULATIONS
Safety Factors
Figure 23. Biaxial and triaxial strength curves (sheet 1 of 2).
Figure 23. Biaxial and triaxial strength curves (sheet 2 of 2).
Section IV. DESIGN PROCEDURES
Stroking Devices - TB-9-1377-2000038
Section V. COMPONENT DESIGN
Table VIII. Sizes of Existing Cartridge Cases
Figure 28. Percussion primer.
Body and Chamber
Firing Mechanism
Table XI. Firing Pin Protrusions and Diameters
Table XII. Firing Pins and Shear Pins Used in Propellant Actuated Devices
Figure 35. Mechanically operated firing mechanism.
Figure 36. Thruster looking mechanism.
Section VI. SPECIAL PROBLEMS
Figure 39. Floating piston and thermal expansion chamber.
Protective Coatings
Dissimilar Metals.
Chapter 5. BALLISTIC DESIGN AND ANALYSIS
Propellant Parameters
Refinements to First Order Approximations
Figure 43. Desired pressure vs time curve.
Use of "Ideal" acceleration vs. time curves to estimate stroke length.
Use of "Ideal" acceleration vs. time curves to estimate stroke length. (Cont)
Figure 46. "Ideal" pressure, acceleration, velocity, and travel vs time curves for a three-tube catapult.
Use of Estimated Acceleration vs Time Curve to Determine Approximate Propellant Web.
Estimation of Propellant Charge Weight.
Thrusters.
Development of Propellant Charge Design
Use of Experimental Pressure vs Time Curve to Refine Propellant Charge Design
Rate of pressure rise.
Section II. MATHEMATICAL ANALYSIS OF INTERIOR BALLISTICS
Figure 48. Pressure and quantity of propellant gas vs volume on logarithmic scales.
Equations of motion.
Table XlV. Coefficients for Form Function (Sewn-Perforated Propellant)
Equation of state.
Table XV. Values of Energy Balance Terms Upon Completion of Stroke
Damping Requirement
Bypass Requirements.
Figure 51. Experimental and calculated bypass pressure for MSA1 Thruster.
Initiators
Chapter 6. DESIGN EXAMPLES
Stroke Time.
Component Layout - TB-9-1377-2000077
Figure 54. Expansion ratio with annular volume.
Tubes
Figure 57. Inside tube for catapult.
Figure 58. Telescoping tube for catapult.
Trunnion.
Trunnion. (cont)
Block.
Firing Mechanism .
Locking Mechanism
Minor Parts
Section III. M3A1 THRUSTER
Component Layout - TB-9-1377-2000089
Cartridge
End Cap
Figure 69. End cap of thruster.
End Sleeve and Locking Mechanism
Figure 7. Breech for thruster.
Figure 74. Thruster firing pin.
First Order Approximations
Figure 76. Initiator component layout.
Figure 79. Cartridge retainer.
Figure 81. Initiator cap.
Figure 82. Firing pin for initiator.
Firing-Pin Housing
Chapter 7. PERFORMANCE EVALUATION
Figure 86. Teat instrumentation.
Figure 88. Piezoelectric amplifier.
Strain Resistance Gages.
Figure 89. Coupling network for use with bridge-type gages.
Travel Measurement.
Figure 92. Schematic diagram of linear electrolytic positioning transducer.
Typical Instrumentation Setup.
Figure 94. Oscillogram obtained with test setup of figure 93.
Figure 95. Vertical test tower.
Figure 96. Test tower showing catapult, transducers, and wiring on test track.
Figure 97. Another type of vertical test tower.
Figure 99. Air cylinder for testing propellant actuated devices.
Figure 101. Teat setup for initiators.
Prototype Evaluation.
Qualification and Analysis Evaluation Program
Table XVII. Qualification and Analysis Evaluation Schedule
Figure 102. Temperature-altitude-humidity test cycle.
Performance Evaluation.
Appendix I. CONVERSION OF DISTORTION ENERGY EQUATION TO MORE USEFUL FORMS FOR PROPELLANT ACTUATED DEVICES
Biaxial Stresses.
Appendix II. TABLE OF WALL RATIOS
TABLE OF WALL RATIOS (cont)
Appendix III. DERIVATION OF EQUATION USED IN DETERMINING LENGTH OF ENGAGEMENT OF THREADS
Appendix IV. DERIVATION OF WEB THICKNESS EQUATION FOR TELESCOPING TUBE DEVICES
Appendix V. DERIVATION OF EQUATION FOR BYPASS TUBE PRESSURE
DERIVATION OF EQUATION FOR BYPASS TUBE PRESSURE (cont)
Appendix VI. REFERENCES
GLOSSARY - TB-9-1377-2000130
GLOSSARY (cont) - TB-9-1377-2000131
TB-9-1377-200 Propellant Actuated Devices Manual
