Systems Engineering and Management"

Transcription

1 Seminar 10! Project Management System Design! Spacecraft Guidance! Robert Stengel! FRS 112, From the Earth to the Moon! Princeton University, 2015! Project Management Spacecraft Design!" "Fundamentals of Space Systems, Ch 1" Sec " "GOES N Series Data Book! Ch 1, 2, 8, 9, 11, 12, 13" " Spacecraft Guidance:" Understanding Space! Sec 12.3" Copyright 2015 by Robert Stengel. All rights reserved. For educational use only.! " 1! Systems Engineering and Management"!# Introduction"!# Fundamentals of System Engineering"!# Concepts in Systems Engineering"!# Project Development Process"!# Management of the Development of Space Systems"!# Organization" Pisacane, V., Fundamentals of Space System Design, Ch. 1" 2!

2 Systems Engineering" Pisacane, V., Fundamentals of Space System Design, Ch. 1" 3! Product Development" Pisacane, V., Fundamentals of Space System Design, Ch. 1" 4!

3 Spacecraft Mission Objectives and Requirements" Fortescue" 5! Requirements Definition" What must the system accomplish?" Why must it be done?" How do we achieve the design goal?" What are the alternatives?" What sub-systems perform specified functions?" Are all functions technically feasible?" How can the system be tested to show that it satisfies requirements?" Wertz and Larson" 6!

4 Spacecraft Subsystems" Numbers refer to mission functions in Fortesque et al, Spacecraft Systems Engineering" 7! Power and Propulsion" #Solar cells" # Kick motor/ payload assist module" #Attitude-control/ orbit-adjustment/ station-keeping thrusters" #Batteries, fuel cells" #Pressurizing bottles" #De-orbit/ graveyard systems" Satellite Systems " Structure" #Skin, frames, ribs, stringers, bulkheads" #Propellant tanks" #Heat/solar/ micrometeoroid shields, insulation" #Articulation/ deployment mechanisms" #Gravity-gradient tether" #Re-entry system (e.g., sample return)" Electronics" #Payload" #Control computers" #Control sensors and actuators" #Control flywheels" #Radio transmitters and receivers" #Radar transponders" #Antennas" 8!

5 Functional Requirements of Spacecraft Subsystems" 1.# Payload must be pointed in the right direction" 2.# Payload must be operable" 3.# Data must be communicated to the ground" 4.# Desired orbit for the mission must be maintained" 5.# Payload must be held together and mounted on the spacecraft structure" 6.# Payload must operate reliably over some specified period" 7.# Adequate power must be provided" 9! LADEE" Typical Satellite Mass Breakdown" Satellite without on-orbit/de-orbit propulsion" Kick motor/ PAM can add significant mass" 10!

6 Communications Satellite Mass Breakdown " 11! Recommended Mass Growth Margins " Pisacane, V., Fundamentals of Space System Design, Ch. 1" 12!

7 LADEE Bus Modules" Satellite Buses" Standardization of common components for a variety of missions" Modular Common Spacecraft Bus" Lander Congiguration" 13! Hine et al" 14!

8 Geostationary Operational Environmental Satellite (GOES-NOP)" 15! GOES Expanded View" 16!

9 GOES Weather Watch System" 17! GOES Communication Sub-System" 18!

10 GOES Telemetry and Command Sub-System" 19! GOES Electric Power Sub-System" 20!

11 GOES Attitude Control Sub-System" 21! GOES Propulsion Sub-System" 22!

12 GOES Thermal Control Sub-System" 23! Guidance, Navigation, and Control! 24!

13 Guidance, Navigation, and Control " Navigation: Where are we?" Guidance: How do we get to our destination?" Control: What do we tell our vehicle to do?" 25! First Apollo Program Contract! MIT Instrumentation Laboratory! August 9, 1961" Charles Stark Draper" ( )" BUT Lunar landing technique was not decided until July, 1962" 26!

14 Components of Apollo CSM Primary Navigation Guidance and Control System ( PNGCS )" Mindell, D., Digital Apollo, Ch. 5" 27! Landmark Tracking for Apollo Guidance" Mindell, D., Digital Apollo, Ch. 5" 28!

15 IMU Alignment and State Update" Mindell, D., Digital Apollo, Ch. 5" 29! Apollo Guidance Computer" Parallel processor" 16-bit word length (hexadecimal)" Memory" # 36,864 words (fixed)" # 2,048 words (variable)" 1 st operational solid-state computer" Identical computers in CSM and LM" # Different software (with many identical subroutines)" 30!

16 Apollo Guidance Computer (AGC) vs. iphone 5S"!# 16-bit Processor"!# Storage: 36,864 words (fixed)"!# 2,048 words (variable)"!# Clock speed: 1 million ticks per sec"!# Weight: 70 lb"!# 1 st operational solid-state computer"!# Separate Inertial Measurement Unit"!# 64-bit Processor"!# Storage: Gbytes"!# 1 Gbyte RAM"!# Clock speed: 1,300 million ticks per sec"!# Weight: 1/4 lb"!# Plus accelerometers angular rate gyros,." 31! Apollo Guidance Computer Magnetic Core Memory Ropes" 1 core = 1 bit " 1 Kiloword Memory Bank"!# No built-in redundancy"!# No redundant computers"!# No failures"!# Mean time between failures = $" 32!

17 Apollo Lunar Module Radars" Landing radar" # 3-beam Doppler radar altimeter" # LM descent stage " Rendezvous radar" # continuous-wave tracking radar" # LM ascent stage! 33! Apollo Guidance Computer Commands" Display/Keyboard (DSKY)" Sentence" # Subject and predicate" # Subject is implied" Astronaut, or" GNC system" # Sentence describes action to be taken employing or involving an object" Predicate" # Verb = Action" # Noun = Variable or Program (i.e., the object)" See And for simulation" 34!

18 Numerical Codes for Verbs and Nouns in Apollo Guidance Computer Programs" Verb Code!Description!!Remarks! 01!Display 1st component of!octal display of data!!!!on REGISTER 1! 02!Display 2nd component of!octal display of data!!!!on REGISTER 1! 03!Display 3rd component of!octal display of data!!!!on REGISTER 1! Noun Code!Description!!Scale/Units! 01!!Specify machine address!xxxxx! 02!!Specify machine address!xxxxx! 03!!(Spare)! 04!!(Spare)! 05!!Angular error!!xxx.xx degrees! 06!!Pitch angle!!xxx.xx degrees!!!heads up-down!!+/ ! 07!!Change of program or major mode! 11!!Engine ON enable! 35! Verbs and Nouns in Apollo Guidance Computer Programs" Verbs (Actions)" # Display" # Enter" # Monitor" # Write" # Terminate" # Start" # Change" # Align" # Lock" # Set" # Return" # Test" # Calculate" # Update" Selected Nouns (Variables)" # Checklist" # Self-test ON/OFF" # Star number" # Failure register code" # Event time" # Inertial velocity" # Altitude" # Latitude" # Miss distance" # Delta time of burn" # Velocity to be gained" Selected Programs (CM)" # AGC Idling" # Gyro Compassing" # LET Abort" # Landmark Tracking" # Ground Track Determination" # Return to Earth" # SPS Minimum Impulse" # CSM/IMU Align" # Final Phase" # First Abort Burn" 36!

19 A Little AGC Digital Autopilot Code" 37! Apollo GNC Software Testing and Verification" Major areas of testing" # Computational accuracy" # Proper logical sequences" Testing program" # Comprehensive test plans" # Specific initial conditions and operating sequences" # Performance of tests" # Comparison with prior simulations, evaluation, and re-testing" Levels of testing" # 1: Specifications coded in higher-order language for non-flight hardware (e.g., mainframe then, PCs now)" # 2: Digital simulation of flight code" # 3: Verification of complete programs or routines on laboratory flight hardware" # 4: Verification of program compatibility in mission scenarios" # 5: Repeat 3 and 4 with flight hardware to be used for actual mission" # 6: Prediction of mission performance using non-flight computers and laboratory flight hardware" 38!

20 Lunar Module Navigation, Guidance, and Control Configuration" 39! Lunar Descent Guidance! 40!

21 Lunar Module Transfer Ellipse to Powered Descent Initiation" 41! Lunar Module Powered Descent" 42!

22 Lunar Module Descent Events" 43! Lunar Module Descent Targeting Sequence" Braking Phase (P63)" Approach Phase (P64)" 44! Terminal Descent Phase (P66)!

23 Characterize Braking Phase By Five Points" 45! Lunar Module Descent Guidance Logic (Klumpp, Automatica, 1974)" Reference (nominal) trajectory, r r (t), from target position back to starting point (Braking Phase example)" # Calculated before mission" # Three 4 th -degree polynomials in time" # 5 points needed to specify each polynomial " r r (t) = r t + v t t + a t t j t t s t t 4 24! x(t) $ # r(t) = # y(t) "# z(t) % 46!

24 Coefficients of the Polynomials" r r (t) = r t + v t t + a t t j t t s t t 4 24 r = position vector" v = velocity vector " a = acceleration vector" j = jerk vector (time derivative of acceleration)" s = snap vector (time derivative of jerk)!! x$ # r = # y "# z% v = dr dt =! # # " #!x!y!z $! # = # % # "# v x v y v z $ %! a = dv dt = # # # "# a x a y a z $ %! j = da dt = # # # "# j x j y j z $ %! s = dj dt = # # # "# s x s y s z $ % 47! Corresponding Reference Velocity and Acceleration Vectors" v r (t) = v t + a t t + j t t s t t 3 6 a r (t) = a t + j t t + s t t 2 a r (t) is the reference control vector" # Descent engine thrust / mass = total acceleration" # Vector components controlled by orienting yaw and pitch angles of the Lunar Module! 48! 2

25 Guidance Logic Defines Desired Acceleration Vector" If initial conditions, dynamic model, and thrust control were perfect, a r (t) would produce r r (t)! a r (t) = a t + j t t + s t t 2 2! r r (t) = r t + v t t + a t t j t t s t t but they are not" Therefore, feedback control is required to follow the reference trajectory! 49! Guidance Law for the Lunar Module Descent" Linear feedback guidance law (real time! a command (t) = a r (t) + K V [ v measured (t)! v r (t)]+ K R r measured (t)! r r (t) K V :velocity error gain K R :position error gain [ ] Nominal acceleration profile is corrected for measured differences between actual and reference flight paths" Considerable modifications made in actual LM implementation (see Klumpp s original paper on Blackboard)! 50!

26 LM Manual Control Response During Simulated Landing" 51! Simulated LM Manual Control Response To Rate Command" 52!

27 Next Time:! Commercial Space Flight" Augustine s Laws, Ch 1, 8, 26, 36, 37, 40; 1986 (On-Line Copy in Princeton University Library)" " Commercial Space Transportation:! Industry Trends, Government Challenges, and International Competitiveness Issues, GAO T, 2013 " " Telemetry, Communications Tracking" [Understanding Space] Sec 13.1, "15.1 " 53! Supplemental Material! 54!

28 Apollo GNC Software Specification Control" Guidance System Operations Plan (GSOP)" # NASA-approved specifications document for mission software" # Changes must be approved by NASA Software Control Board" Change control procedures" # Program Change Request (NASA) or Notice (MIT)" # Anomaly reports" # Program and operational notes" Software control meetings" # Biweekly internal meetings" # Joint development plan meetings" # First Article Configuration Inspection" # Customer Acceptance Readiness Review" # Flight Software Readiness Review" 55! Apollo GNC Software Documentation and Mission Support" Documentation generation and review" # GSOP: 1: Prelaunch 2: Data links 3: Digital autopilots 4: Operational modes 5: Guidance equations 6: Control data" # Functional description document: H/W-S/W interfaces, flowcharts of procedures" # Computer listing of flight code" # Independently generated program flowchart" # Users Guide to AGC" # NASA program documents: Apollo Operations Handbook, Flight Plans and Mission Rules, various procedural documents" Mission support" # Pre-flight briefings to the crew" # Personnel in Mission Control and at MIT during mission" 56!

29 Ascent (Launch) Guidance! 57! Gravity-Turn Flight Path" Hermann Oberth" Oberth s Synergy Curve " Gravity-turn flight path is function of 3 variables" # Initial pitchover angle (from vertical launch)" # Velocity at pitchover" # Acceleration profile, T(t)/m(t) " Gravity-turn program closely approximated by tangent steering laws " 58!

30 Tangent Steering Laws Approximate Gravity Turn " Neglecting surface curvature " # tan!(t) = tan! o 1" t $ % t BO ' ( Open-loop command, i.e., no feedback of vehicle state " Accounting for effect of Earth surface curvature on burnout flight path angle " * tan!(t) = tan! o 1" t $, " tan# t BO % + t t BO ' - ( ) /. 59! Feedback Guidance Law " Errors due to disturbances and modeling errors corrected by feedback control with damping " Thrust Angle(t) = c! [! c (t) "!(t)]" c q q(t) q = d! dt = pitch rate 60!

31 Phases of" Ascent Guidance" Vertical liftoff" Roll to launch azimuth" Pitch program to atmospheric exit " # Jet stream penetration" # Booster cutoff and staging" Explicit guidance to desired orbit" # Booster separation" # Acceleration limiting" # Orbital insertion " 61! Jet Stream Profiles " Launch vehicle must able to fly through strong wind profiles" Design profiles assume 95 th -99 th -percentile worst winds and wind shear" 62!

32 Thrust Vector Control During Launch " Attitude control" # Attitude and rate feedback" Drift-minimum control" # Attitude and accelerometer feedback" # Increased loads" Load relief control" # Rate and accelerometer feedback" # Increased drift" 63! Explicit Guidance Law " ~Lunar Module Ascent, Space Shuttle Launch " (Brand, Brown, Higgins, and Pu, CSDL, 1972) " Initial conditions" # End of pitch program, outside atmosphere" Final condition" # Insertion in desired orbit" Initial inputs" # Desired radius" # Desired velocity magnitude" # Desired flight path angle" # Desired inclination angle" # Desired longitude of the ascending/ descending node" Continuing outputs" # Unit vector describing desired thrust direction" # Throttle setting" 64!

33 Guidance Program Initialization" Thrust acceleration estimate" Mass/mass flow rate" Acceleration limit (~ 3g)" Effective exhaust velocity" Various coefficients" Unit vector normal to desired orbital plane, i q " " sini d sin! d % $ ' i q = $ sini d cos! d ' # $ cosi d ' i d :desired inclination angle! d :desired longitude of descending node 65! Guidance Program Operation: Position and Velocity " Thrust acceleration estimate, a T, from guidance system" Compute corresponding mass/flow rate and throttle setting, #T" Position"! r$! r $ # # # y = # rsin '1 ( i r i q ) "# z% "# open % Velocity"! r $! v IMU i r $ # # # y = # v IMU i q "# z % "# v IMU i z % v IMU :velocity estimate in IMU frame 66!

34 Guidance Program: Velocity and Time to Go " Effective gravitational acceleration" g eff =! µ r + r " v 2 2 Time to go (to burnout)" r 3 t gonew = t goold! "t!t :guidance interval Velocity to be gained" " $ v go = $ $ # $ (!r d!!r )! g eff t go / 2!!y!z d!!z Time to go prediction (prior to acceleration limiting)" t go = ṁ m 1! e!v go / c ( eff ) % ' ' ' ' c eff :effective exhaust velocity 67! Guidance Program Commands " Guidance law produces required radial and cross-range accelerations" [ ]! g eff [ ] a Tr = a T A + B( t! t o ) ( ) a Ty = a T C + D t! t o a T = net available acceleration, accounting for limit Guidance coefficients, A, B, C, and D are functions of" ( r d,r, r, t go ) ( y, y,t go ) plus c eff,m!m, acceleration limit 68!

35 Guidance Program Commands " Required thrust direction, i T (i.e., vehicle orientation in (i r, i q, i z ) frame"! # a T = # # "# a Tr a Ty what's left over $ ; i T = a T a T % Guidance philosophy" Force spacecraft into desired orbital plane" Climb toward desired 2-D orbit" Achieve orbital velocity" 69!