TELcDYNS RYAN AERONAUTICAL

201 Pages·2008·8.66 MB·English

https://ntrs.nasa.gov/search.jsp?R=19730015330 2019-04-12T04:52:49+00:00Z
NASA CR-112323
N 7 3 2 4 0 57
FEASIBILITY STUDY OF
MODIFICATIONS TO BQM-34K DRONE
FOR NASA RESEARCH APPLICATIONS
ASTM 72-40 27 DECEMBER 1972
PREPARED UNDER CONTRACT NO. NAS1-11758
for
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
^>TELcDYNS RYAN AERONAUTICAL
2701 HARBOR DRIVE, SAN DIEGO. CALIFORNIA 92112 AREA CODE 714/291-7311
Prepared by
H. A. James
Design Specialist
Approved by
p. E. DiBartola
Manager
Preliminary Design
Advanced Systems
Approved by
if. G.v Timmons
Director
Advanced Systems
ii.
FOREWORD
Contributions for this report on various subjects v/ere made by the
following personnel for Advanced Systems: D. C. Harper and II. M.
Allen, design; D. .O. Nevingcr, \veights; R. W. Thompson, parametric,
wing sizing; II. A. James, Project Leader, aerodynamics and perform-
ance; F. L. Miller, systems;-!. Wilcox, reliability; and N. M. Bowers,
structures and materials.
in
SUMMARY
The feasibility of modifying an existing supersonic drone, BQM-34E,
into a NASA free-flight research vehicle is examined in this study. This
remotely controlled vehicle would be capable of free-flight validation
testing of wing configurations representative of a wide range of research
applications for advanced transports and fighters as well as RPVs. This
study is addressed to three main topics per Contract No. NAS 1-11758,
i.e.: aerodynamics and performance, design and structures, and
command and control system.
Appropriate structural and control system modifications, reliability and
operational considerations, and ROM costs indicate that the BQM-34E
drone is indeed suitable as a NASA research vehicle.
During the initial portipn of the study, wing sizing to specified aerody-
namic and performance criteria was accomplished. This resulted in
the definition of six point designs matched to the modified BQM-34E with
its basic propulsion system. From these results, NASA selected a
representative research configuration for more in-depth structural
design and control system studies.
The structural design studies identified several alternative engineering
solutions for the testing of high and low-wing configurations. These were
evaluated in terms of cost, complexity, and model similarity. Repre-
sentative control and high-lift devices were configured for transonic
flutter mode suppression research testing. Practical methods of
achieving variations of wing bending and torsional rigidity were identified.
The results of a comprehensive anal3'sis of command and control systems
required for various types of research programs are summarized. The
basic control and AFSC system is amenable .to modifications with existing
hardware to accommodate steady-state as well as dynamic loads, flutter,
and variable-stability research programs.
CONTENTS
SECTION PAGE
1.0 INTRODUCTION 1
/
.2.0 TECHNICAL APPROACH 3
3.0 RESULTS ' . 5
3.1 Preliminary Studies 5
3.2 Point Designs 21
3.3 Research Configuration 64
3.4 Support Studies - 169
4.0 ' CONCLUSIONS . 183
5.0 RECOMMENDATIONS ... . 185
6.0 NOTATIONS AND SYMBOLS 187
7.0 REFERENCES 191
C
vil
LIST OF FJG U'R ES
FIGURE PAGE
3-1 AVSYN Results 6
3-2 AVSYN Results, Sea Level Launch / 7
3-3 AVSYN Wing Parameter Study /: ' 8
3-4 NASA Wing Study, Preliminary Estimate of the
Thrust Required and Available for the No. 1 Wing-
Design 9
3-5 NASA Wing Study, Sizing Study for Wing No. 1 10
3-6 NASA Wing Study, Preliminary Estimate of the
Thrust Required and Available for the No. 2 Wing-
Design _ _ 11
3-7 NASA Wing Study, Sizing Study for Wing No. 2 12
3-8 NASA Wing Study, Preliminary Estimate of Thrust
Required and Available for the No. 3 Wing Design 13
3-9 NASA Wing-Study, Sizing Study for Wing No. 3 14
3-10 NASA Wing Study, Preliminary Estimate of Thrust
Required and Available for the No, 4 Wing Design 15
3-11 NASA Wing Study, Sizing Study 'for Wing No. 4 16
(._ 3-12 NASA Wing Study, Preliminary Estimate of Thrust
Required and Available for No. 5 Wing Design 17
3-13 NASA Wing Study, Sizing Study for Wing No. 5 18
3-14 NASA Wing Study, Preliminary Estimate of Thrust
Required and Available for the No. 6 Wing Design 19
3-15 NASA Wing Study, Sizing Study for Wing No. 6 20
3-16 No. 1-30 Mach Number vs. Altitude 25
3-17 . 'No. 2-30 Mach Numbei vs. Altitude 26
3-18 No. 3-24 Mach Number vs. Altitude 27
3-19 No. 4-40 Mach Number vs. Altitude 28
" 3-20 No. 5-60 Mach Number vs. Altitude 29
3-21 No. 6-35 Mach Number vs. Altitude . 30
3-22 No. 1-30 Specific Endurance 31
3-23 No. 2-30 Specific Endurance 32
. 3-24 No. 3-24 Specific Endurance 33
3-25 No. 4-40 Specific Endurance 34
3-26 No. 5-60 Specific Endurance 35
3-27 No. 6-35 Specific Endurance 36
3-28 No. 1-30 CD vs. Mach Number . 47
O
IX
LIST OF FIGURES (Continued)
FIGURE ' PAGE
3-29 No. 1-30 Induced Drag Coefficient vs. Mach Number 43
3-30 No. 1-30 Longitudinal Characteristics 49
3-31 No. 2-30 CD vs. Mach Number 50
O
3-32 No. 2-30 Induced Drag Coefficient vs. Mach Number 51
3-33 No. 2-30 Longitudinal Characteristics 52
3-34 No. 3-24 CD vs- Mach Number ' 53
O
3-35 No. 3-24 Induced Drag Coefficient vs. Mach Number 54
3-36 No. 3-24 Longitudinal Characteristics 55
3-37 No. 4-40 CD vs- Mach Number 56
O
3-38 No. 4-40 Induced Drag Coefficient vs. Mach Number 57
3-39 No. 4-40 Longitudinal Characteristics 58
3-40 No. 5-GO CD vs- Mach Number 59
O
3-41 No. 5-60 Induced Drag Coefficient vs. Mach Number 60
3-42 No. 5-60 Longitudinal Characteristics Gl
3-43' No. 6-35 CD vs- Mach Number 62
O
3-44 No. 6-35 Longitudinal Characteristics 63
3-45 General Arrangement, 1-30-2 67
3-46 Design Alternatives .68
3-47 Wing/Fuselage Configuration Tradeoff 69
3-48 Wing Installation and Fuselage Modification 1-30-2 71
3-49 ' Wing Installation and Fuselage Modification 1-30-1 72
3-50 Inboard Profile, Configurations 1-30-1 and 1-30-2 75
3-51 Area Rule Modifications 77
3-52 Area Distribution for the Basic BQM-34E 78
3-53 Area Distribution, Configuration 1-30-2 NASA
Research Wing, Model 166 79
3-54 Wing Plan Form Structural Arrangement 80
3-55 Wing Structural Cross Sections .. 81
3-56 Mach Number vs. Altitude - 83
3-57 V-n Diagrams - Symmetrical Maneuvers, Model
BQM-34E . 84
3-58 V-n Diagrams - Unsymmetrical Maneuvers, Model
BQM-34E . .85
3-59 Model AQM-34R Drone 124
3-60 Analysis Approach and Cycle 125
3-61 Structural Analysis Procedure 127
3-62 Concept 1, .Variable Wing Stiffness 131
3-63 Concept 2, Variable Wing Stiffness 132
. 3-64 Concept 3, Variable Wing Stiffness 133
LIST OF FIGURES (Continued)
FIGURE ° PAGE
•
3-05 Concept 4, Variable Wing .stiffness 134
3-GG Concept 5, Variable Win;; Stiffness 135
., . 3-67 Concept G, Variable Win;.; Stiffness / .136
3-68 Concept 7, Variable Wing Stiffness ' 137
3-G9 Wing Stiffness Variation, Model 147TF Composite
Skins . 1 39
3-70 Deleted
3-71 Estimated Static Stability and CG Range 143
3-72 Model BQM-3-1E With Supercritical Wing 1-30,
Elevator Angle Required for Trim 145
.' 3-73 Model BQM-34E With Supercritical Wing 1-30,
Estimated Maneuver Capability 146
3-74 ' Model BQM-.'ME Estimated Change in Stability Due
to Added Fuselage Section Forward of Wing 150
3-75 ModelBQM-34E With Supercritical Wing, -
Comparison of Lateral-Directional Stability
Derivatives 151
/"' 3-76 No. 1-30-2 Time History ojt a Typical NASA
Research Mission 153
3-77 No. 1-30 Maximum Rate-of-Climb vs. Altitude 154
3-78 No. 1-30 Specific Range vs. Mach Number, 2000
Pounds 155
3-79 Avionics Functional Bloc!; Diagram 157
3-80 Guidance and Control Concepts 160
3-81 Longitudinal Axis AFCS Channel 164
3-82 Lateral Axis AFCS Channel " 165
3-83 Model BQM-34E Reliability Functional Block
Diagram, Operational Complex 171
3-84 NASA Research Vehicle Recovery Phase Reliability,
Functional Block Diagram " 173
5-1 Recommendations for Phase II "186
LIST OF TABLES
TABLE PAGE
1-1 Wings Planned for Study / 2 ;
3-1 NASA Research Mission Tabulation, Wing
No. 1-30, Mach 0.98 Transport 38
3-2 NASA Research Mission Tabulation, Wing
No. 2-30, Mach 0. DO Transport 38
3-3 NASA Research Mission Tabulation, Wing
No. 3-24, Air-to-Air RPV 39
. 3-4 NASA Research Mission Tabulation, Wing j
No. 4-40, Endurance Turbojet 39 i
3-5 . . NASA Research Mission Tabulation, Wing i
No. 5-60, Endurance Turbofan 40 I
3-G NASA Research Mission Tabulation, Wing |_
\ No. 6-35, SST Configuration - - 40
3-7 Profile Drag Buildup, Model 1-30 41
3-8 Profile Drag Buildup, Model 2-30 42 i
3-9 Profile Drag Buildup,-Model No. 3-24 43 .','
3-10 Profile Drag Buildup, Model No. 4-40 44 j
3-11 Profile Drag Buildup, Model No. 5 45
3-12 Profile Drag Buildup, Model No. 6-35 46
3-13 . NASA Point Design Summary 65
3-14 ' Configuration List 66
3-15 Structural Design Criteria Summary, Parachute
Recovery .- 86
3-16 Structural Design Criteria Summary, MARS
Recovery 91
3-17 • Figures of Merit, Associated Parameters,
Weighting Factors 94
3-18 Comparison Matrix , 95
3-19 Evaluation 99
3-20 Weight and Balance Summary, NASA Wing Study
(Low Wing) 121
3-21 Command Guidance Equipments 162
3-22 Secondary Power 168
3-23 ' NASA BQM-34E and Navy BQM-34E Flight
Phase Reliability Prediction Comparison 176
LIST OF TABLES (Continued)
TABLE PAGE
3-24 NASA BQM-34E and Navy BQM-3-1E Recovery
Phase Reliability Prediction Comparison 177
3-25 Estimate of Tasks 179
3-2G Possible Elements of Flight Assurance/
Determination 181
xiv