1. AIM 98-4149
SPACE MANEUVER VEHICLE DEVELOPMENT BY
THE MINI-SPACEPLANE TECHNOLOGY PROGRAM
Harry Kcrasopoulos Richard T. CervisI
John Anttonen John T. Fuller
Air Force Research Laboratory The Boeing Company
AIAA Atmospheric Flight Mechanics
Conference and Exhibit
August 10-12, 1998 / Boston, Massachusetts
For permission to copy or republish, contact the American Institute of Aeronautics and Astronautics
1801 Alexander Bell Drive, Suite 500, Reston, Virginia 20191 -4344

2. AIAA-98-4149
SPACE MANEUVER VEHICLE DEVELOPMENT BY THE
MINI-SPACEPLANE TECHNOLOGY PROGRAM
Harry Karasopoulos*
A i r F o r c e Research Laboratory, A i r Vehicles D i r e c t o r a t e
Richard T. Cervisi^
The Boeing Company
John Anttonen*
A i r F o r c e Research Laboratory, Space Vehicles D i r e c t o r a t e
John T. Fuller^
The Boeing Company
Abstract
Under the Mini-Spaceplane Technology Program, the United States Air Force is currently examining
a small, reusahle, upper stage vehicle concept designed hy Boeing. This Space Maneuver Vehicle
(SMV) is a reusahle satellite hus capahle of heing launched from several candidate hooster platforms,
recovered on a conventional runway, and quickly refurhished and re-launched. It is a key
component of the Space Operation Vehicle system architecture currently heing studied hy the Air
Force. The Space Maneuver Vehicle has the capahility to support military missions in space such as
space-hased surveillance, reconnaissance, and space control, with great flexihility and a large on-
orhit A V. The Mini-Spaceplane Technology Program is a 24 month, $6.4M contract with Boeing to
study SMV design requirements, perform conceptual design trades, and undertake two advanced
technology demonstrations. In 1997 Boeing designed a wing hox and center fuselage section
structural test article under this effort, and fahricated it under a related contract. This component
was tested to failure hy Air Force Research Lahoratory in Septemher 1997. The second advanced
technology demonstration under the Mini-Spaceplane Technology Program is the design, fahrication,
and testing of an unpowered, 90% scale, flight test vehicle. Ground and captive-carry testing of the
SMV flight test vehicle is currently underway at Holloman Air Force Base, New Mexico; autonomous
approach and landing flight tests are scheduled for summer 1998. This paper presents an overview
of the Mini-Spaceplane Technology Program, emphasizing the two advanced technology
demonstrations.
Nomenclature Introduction
A F R L = A i r F o r c e R e s e a r c h L a b o r a t o r y
G P S = G l o b a l P o s i t i o n i n g S y s t e m
G E O = G e o s y n c h r o n o u s E a r t h O r b i t
I N S = I n e r t i a l N a v i g a t i o n S y s t e m
L E O = L o w E a r t h O r b i t
M = M a c h n u m b e r
S M V = Space M a n e u v e r V e h i c l e
S O V = Space O p e r a t i o n s V e h i c l e
A V = C h a n g e i n v e l o c i t y , ft/sec
R e u s a b l e m i l i t a r y spaceplane a n d t r a n s a t m o s p h e r i c
v e h i c l e concepts h a v e l o n g been o f interest t o t h e
U n i t e d States A i r F o r c e . E a r l y h y p e r s o n i c research a n d
l i f t i n g r e e n t r y v e h i c l e p r o g r a m s such as t h e X - 1 5 , X - 2 3 ,
a n d X - 2 4 p r o g r a m s o f t h e 1950s a n d 1 9 6 0 s f e d a
n u m b e r o f A i r F o r c e m i l i t a r y spaceplane studies o f that
era such as t h e D y n a - S o a r X - 2 0 a n d t h e
A e r o s p a c e p l a n e p r o g r a m s . A l t h o u g h n u m e r o u s
t r a n s a t m o s p h e r i c v e h i c l e c o n c e p t u a l studies f o l l o w e d
o v e r t h e years, a n o p e r a t i o n a l s y s t e m w a s n e v e r built.
I n t h e 1980s t h e A i r F o r c e r e v i s i t e d these systems.
Studies such as t h e A d v a n c e d M i l i t a r y S p a c e f l i g h t
* S M V P r o g r a m M a n a g e r , M e m b e r A I A A
' B o e i n g S M V C h i e f E n g i n e e r , M e m b e r A I A A
* S O V P r o g r a m O f f i c e , M e m b e r A I A A
^ B o e i n g S M V P r o g r a m M a n a g e r , M e m b e r A I A A
This paper is declared a w o r k o f the U . S . Government and is
not subject to copyright protection i n the United States.

3. AIAA-98-4149
C a p a b i l i t y , M i l i t a r y A e r o s p a c e V e h i c l e , a n d
T r a n s a t m o s p h e r i c V e h i c l e p o i n t e d t o the considerable
m i l i t a r y p o t e n t i a l f o r this class o f vehicles. T h e A i r
F o r c e i n v e s t e d h e a v i l y i n m i l i t a r y spaceplane
t e c h n o l o g y d e v e l o p m e n t i n t h e N a t i o n a l A e r o s p a c e
P l a n e ( N A S P ) p r o g r a m f r o m the m i d - 1 9 8 0 s t o the e a r l y
1990s, p a r t i c u l a r l y i n h y p e r s o n i c a i r b r e a t h i n g e n g i n e
technologies. S i n c e that t i m e , e m p h a s i s has s e e m i n g l y
shifted f r o m a i r b r e a t h i n g e n g i n e t o r o c k e t p o w e r e d
spaceplane systems, a n d f r o m c o n v e n t i o n a l r o c k e t
l a u n c h operations t o m o r e a i r c r a f t - l i k e l a u n c h
operations. T h i s e m p h a s i s i s reflected b y this decade's
D C - X and D C - X A p r o g r a m s , and b y the c u r r e n t Space
O p e r a t i o n s V e h i c l e S y s t e m p r o g r a m .
T h e A i r F o r c e i s c u r r e n t l y v e r y interested i n m i l i t a r y
spaceplanes a n d t r a n s a t m o s p h e r i c vehicles. A s o u r
c o u n t r y ' s e c o n o m i c a n d m i l i t a r y resources i n space
c o n t i n u e t o r a p i d l y e x p a n d , r e q u i r e m e n t s f o r r o u t i n e ,
fast response, a i r c r a f t - l i k e o p e r a t i o n s t o , i n , a n d f r o m
space b e c o m e i n c r e a s i n g l y i m p o r t a n t . R e q u i r e m e n t s
for g l o b a l reconnaissance, spacelift, a n d space c o n t r o l
are d r i v i n g a n o v e r a l l Space O p e r a t i o n s V e h i c l e s y s t e m
architecture i n w h i c h t h e Space M a n e u v e r V e h i c l e
plays an i m p o r t a n t r o l e .
The Space Maneuver Vehicle
T h e Space M a n e u v e r V e h i c l e c o n c e p t c u r r e n t l y b e i n g
studied b y the U n i t e d States A i r F o r c e i s a d e r i v a t i v e o f
B o e i n g ' s R E F L Y T M concept.' T h i s S M V ( F i g u r e 1 ) i s
a s m a l l , reusable, u p p e r stage w i t h a w i n g - b o d y
c o n f i g u r a t i o n . I t h a s a w i n g span o f a b o u t 1 4 ft, a n
o v e r a l l l e n g t h o f about 2 5 ft, and a w i n g reference area
o f 6 4 sft. T h e Space M a n e u v e r V e h i c l e e m p l o y s
r u d d e r v a t o r a n d f l a p e r o n c o n t r o l surfaces, and i n e r t i a l /
differential G P S guidance. T h e S M V h a s a gross
w e i g h t o f a b o u t 1 1 , 0 0 0 l b , a p a y l o a d w e i g h t o f 1 2 0 0 lb,
a d r y w e i g h t o f a b o u t 2 5 0 0 l b , a n d a p r o p e l l a n t w e i g h t
o f about 6 9 0 0 1 b .
T h e Space M a n e u v e r V e h i c l e i s designed f o r aircraft-
l i k e o p e r a b i l i t y and r e l i a b i l i t y , as w e l l as e x t e n d e d o n -
o r b i t o p e r a t i o n s w i t h d w e l l t i m e s o f u p t o o n e year.
T h e 7 f t l o n g b y 4 f t d i a m e t e r p a y l o a d bay i s designed
w i t h standard interfaces t o a l l o w interchangeable
payloads f o r m i s s i o n f l e x i b i l i t y . O f f - b o a r d p a y l o a d
processing w i l l b e e m p l o y e d t o h e l p d r i v e t u r n a r o u n d
t i m e s t o 7 2 h o u r s o r less. T h e S M V i s a reusable
satellite bus that i s e f f e c t i v e l y a transatmospheric U A V
( U n i n h a b i t e d A i r V e h i c l e ) as i t i s designed t o operate
a u t o n o m o u s l y t h r o u g h o u t b o t h a t m o s p h e r i c a n d
e x o a t m o s p h e r i c e n v i r o n m e n t s . A f t e r r e e n t r y , the S M V
w i l l l a n d o n c o n v e n t i o n a l r u n w a y s .
T h e Space M a n e u v e r V e h i c l e c o n c e p t i s p o w e r e d b y a
r o c k e t engine i n t h e 4 0 0 0 t o 5 0 0 0 l b thrust range
u t i l i z i n g space storable p r o p e l l a n t s . A v a r i e t y o f r o c k e t
engine o p t i o n s a r e c u r r e n t l y b e i n g studied; o n e i s a n
engine based o n t h e X L R - 1 3 2 u s i n g h y p e r g o l i c
propellants ( n i t r o g e n t e t r o x i d e a n d h y d r a z i n e ) t o
p r o v i d e a A V o f m o r e t h a n 1 0 , 5 0 0 ft/s. W i t h such a
large A V capability, t h e S M V w i l l p e r f o r m as a
reusable satellite b u s t o l o w - a n d m i d - e a r t h orbits. I t
w i l l also b e able t o c o n d u c t G E O f l y b y s w h e n inserted
d i r e c t l y i n t o L E O b y a l a u n c h v e h i c l e . T h i s latter
o p t i o n w o u l d a l l o w t h e Space M a n e u v e r V e h i c l e t o
u t i l i z e i t s f u l l A V p o t e n t i a l f o r e x t e n s i v e o r b i t
m a n e u v e r s . A reusable a e r o d y n a m i c a l l y - c o n f i g u r e d
Space M a n e u v e r V e h i c l e offers m u c h greater m i s s i o n
f l e x i b i l i t y o v e r c o n v e n t i o n a l l a u n c h v e h i c l e u p p e r
stages, i n c l u d i n g t h e a b i l i t y t o p e r f o r m aeroassisted
o r b i t a l m a n e u v e r s f o r unpredictable, o n - d e m a n d o r b i t
transfers, a n d t o p r o v i d e increased d o w n r a n g e a n d
crossrange r e c o v e r y o p t i o n s .
T h e S M V i s a c r i t i c a l c o m p o n e n t o f the o v e r a l l Space
O p e r a t i o n V e h i c l e ( S O V ) s y s t e m architecture under
d e v e l o p m e n t b y t h e A i r E o r c e R e s e a r c h L a b o r a t o r y ' s
S p a c e V e h i c l e s D i r e c t o r a t e a t K i r t l a n d A i r F o r c e Base,
N e w M e x i c o . I n this r o l e the S M V w i l l b e l o f t e d b y
either a s u b - o r b i t a l (near t e r m ) o r a f u l l y o r b i t capable
(far t e r m ) reusable S O V . A L E O capable S O V c o u l d
d e p l o y a Space M a n e u v e r V e h i c l e b y direct o r b i t
i n s e r t i o n i n L E O , o r d e p l o y m u l t i p l e S M V s v i a a
s u b o r b i t a l p o p - u p m a n e u v e r . S u c h a s y s t e m w o u l d b e
e n t i r e l y reusable a n d p r o v i d e s i g n i f i c a n t m i s s i o n
c a p a b i l i t y a n d f l e x i b i l i t y . E x p e n d a b l e l a u n c h vehicles
c o u l d also b e u t i l i z e d u n d e r s o m e circumstances t o
b o o s t Space M a n e u v e r V e h i c l e s t o L E O a n d b e y o n d .
Mini-Spaceplane Technology Program
T h e M i n i - S p a c e p l a n e T e c h n o l o g y P r o g r a m i s a 2 4
m o n t h , $ 6 . 4 M contract w i t h B o e i n g t o study S M V
applications a n d design r e q u i r e m e n t s , p e r f o r m
conceptual design trades, a n d t o u n d e r t a k e t w o
advanced t e c h n o l o g y d e m o n s t r a t i o n s . T h i s p r o g r a m i s
f u n d e d b y t h e Space O p e r a t i o n s V e h i c l e S y s t e m
P r o g r a m O f f i c e a n d is j o i n t l y m a n a g e d b y A F R L ' s A i r
V e h i c l e a n d Space V e h i c l e D i r e c t o r a t e s .
I n t h e first advanced t e c h n o l o g y d e m o n s t r a t i o n ,
B o e i n g designed a w i n g b o x a n d center fuselage
structural test article u s i n g a d v a n c e d c o m p o s i t e s . T h i s
test article w a s t h e n fabricated u n d e r a sister contract
a n d tested t o f a i l u r e b y t h e A i r F o r c e R e s e a r c h
L a b o r a t o r y i n S e p t e m b e r 1 9 9 7 . T h e s e c o n d advanced
t e c h n o l o g y d e m o n s t r a t i o n i s t h e design, f a b r i c a t i o n ,
a n d testing o f a n u n p o w e r e d , 9 0 % scale, f l i g h t test
v e h i c l e . G r o u n d a n d c a p t i v e - c a r r y testing o f this S M V
f l i g h t test v e h i c l e i s c u r r e n t l y u n d e r w a y a t H o l l o m a n
A i r F o r c e Base, N e w M e x i c o ; a u t o n o m o u s approach
a n d l a n d i n g f l i g h t tests are scheduled f o r the s u m m e r o f
1 9 9 8 . T h e s e d e m o n s t r a t i o n s a r e discussed i n m o r e
detail b e l o w .
2

4. AIAA-98-4149
Composite Structure Advanced
Technology Demonstration
T h e o b j e c t i v e o f t h e c o m p o s i t e structure advanced
t e c h n o l o g y d e m o n s t r a t i o n w a s t o demonstrate a l o w
cost, l o w w e i g h t c o m p o s i t e structure f o r t h e Space
M a n e u v e r V e h i c l e , as w e l l as validate design m e t h o d s
and load paths. A w e i g h t goal o f 1.0 lb per sft w e t t e d
area w a s selected a l o n g w i t h a cost goal o f $ 3 0 0 0 per lb
o f structure. T h e structural test article design used
B o e i n g ' s REFLY™ 109-1 c o n f i g u r a t i o n as t h e
structural baseline ( F i g u r e 2 ) . T h i s c o n f i g u r a t i o n i s
p r i m a r i l y m a d e o f high-temperature-cure graphite
e p o x y composites. A m a j o r p o r t i o n o f t h e S M V
structure w a s selected f o r design, f a b r i c a t i o n , a n d
testing. T h i s w i n g b o x a n d center fuselage section
( F i g u r e 3 ) extends f r o m t h e f o r w a r d l o a d e x t e n s i o n
structure, f o r w a r d o f t h e w i n g , t h r o u g h t h e m i d -
fuselage a n d w i n g b o x , t o the aft l o a d e x t e n s i o n j u s t
f o r w a r d o f the ruddervators. F i g u r e 4 presents design
highlights o f the test article. T h e actual test structure
appears i n F i g u r e s 5 a n d 6.
A l t h o u g h the structural test article w a s designed under
the M i n i - S p a c e p l a n e T e c h n o l o g y P r o g r a m , i t w a s
constructed b y B o e i n g under the M i n i C e n t e r Fuselage
& W i n g b o x D e m o n s t r a t i o n task o f the A F R L S t r u c t u r a l
T e s t A r t i c l e P r o g r a m . A f t e r about a 6 M o n t h , $ 6 0 0 K
loads analysis, f a b r i c a t i o n , a n d i n s t r u m e n t a t i o n effort,
B o e i n g d e l i v e r e d the structural test article t o the A i r
F o r c e i n A u g u s t 1 9 9 7 . I n S e p t e m b e r it entered A F R L ,
A i r V e h i c l e D i r e c t o r a t e ' s in-house S t r u c t u r a l T e s t
F a c i l i t y at W r i g h t - P a t t e r s o n A i r F o r c e Base. S t r u c t u r a l
testing t o f a i l u r e o f the w i n g b o x a n d center fuselage
section w a s c o m p l e t e d i n September.^ T w o l o a d i n g
c o n d i t i o n s w e r e selected that corresponded t o w o r s t
case loadings r e s u l t i n g f r o m a n S M V l a u n c h f r o m a n
air-dropped expendable l a u n c h vehicle. A s y m m e t r i c
l o a d i n g c o n d i t i o n w a s statically tested t o 8 0 % o f the
design u l t i m a t e l o a d . A n u n s y m m e t r i c l o a d i n g
c o n d i t i o n w a s t h e n statically tested t o failure, w h i c h
occurred at about 1 6 0 % o f the design u l t i m a t e l o a d .
T h e s e tests successfully v a l i d a t e d the pre-test design
and l o a d path analyses. T h e cost g o a l o f less t h a n
$ 3 0 0 0 / l b w a s also met. T h e final o b j e c t i v e o f this
advanced t e c h n o l o g y d e m o n s t r a t i o n , a structural w e i g h t
o f 1.0 Ib/sft o f w e t t e d area, w a s e f f e c t i v e l y i f n o t
e x p l i c i t l y met. A l t h o u g h the as-built structural w e i g h t
came t o 1.08 Ib/sft, s o m e o n - h a n d , heavier t h a n
required m a t e r i a l w a s e m p l o y e d i n a n o n - c r i t i c a l area
o f the structure t o save m o n e y . A n a l y s e s s h o w that
using the lighter, m o r e e x p e n s i v e m a t e r i a l w o u l d h a v e
resulted i n 0 . 9 6 Ib/sft. •
Autonomous Approach & Landing
Advanced Technology Demonstration
T h e objectives o f this advanced t e c h n o l o g y
d e m o n s t r a t i o n are to validate S M V l o w speed h a n d l i n g
qualities, a v i o n i c s , a n d d e m o n s t r a t e a u t o n o m o u s
approach and l a n d i n g guidance a n d c o n t r o l . U n d e r the
M i n i - S p a c e p l a n e T e c h n o l o g y P r o g r a m , B o e i n g
designed a n d b u i l t a 9 0 % - s c a l e " S M V flight test
v e h i c l e ( F i g u r e 7 ) based o n their R E F L Y T M 3 0 9 - 6
c o n f i g u r a t i o n . T h i s flight test v e h i c l e has a graphite-
e p o x y a n d a l u m i n u m h o n e y c o m b structure a n d w e i g h s
2 6 0 0 lb. F o r captive-carry and free-flight tests, t h e
S M V flight test v e h i c l e i s attached t o a stronghack
apparatus ( F i g u r e 8 ) . T h e stronghack is r i g g e d to carry
the flight test v e h i c l e a t a n angle o f attack a t about - 2
deg. T h e flight test v e h i c l e i s attached t o a 7 f t
d i a m e t e r parachute o n a 3 0 f t l i n e f o r s t a b i l i z a t i o n i n
the t o w c o n f i g u r a t i o n . T h e f l i g h t test v e h i c l e r i g i s
lifted v e r t i c a l l y a n d t o w e d o n a 7 0 f t tether b y a
S i k o r s k y H H - 6 0 B l a c k H a w k helicopter ( F i g u r e 9.)
T h i s flight test p r o g r a m i s c u r r e n t l y u n d e r w a y a t
H o l l o m a n A i r F o r c e B a s e ( F i g u r e s 1 0 - 1 2 ) . E x t e n s i v e
static a n d d y n a m i c g r o u n d tests a n d captive-carry flight
tests h a v e been c o m p l e t e d as o f the date this paper w a s
w r i t t e n . ' • T h e s e tests i n i t i a l l y v e r i f i e d the o p e r a t i o n o f
the separation, e m e r g e n c y r e c o v e r y , l a n d i n g , a n d
c o m m u n i c a t i o n subsystems. A total o f eight captive-
carry tests a c c o m p l i s h e d n u m e r o u s objectives. T h e s e
i n c l u d e d d e m o n s t r a t i n g stable t o w o f b o t h t h e
stronghack alone and stronghack / f l i g h t test v e h i c l e
c o m b i n a t i o n b y t h e H H - 6 0 helicopter. I n - f l i g h t
p e r f o r m a n c e w a s characterized f o r the radar altimeter,
G P S / I N S , actuation, i n s t r u m e n t a t i o n , a n d a i r data
subsystems. F l i g h t test v e h i c l e base pressure w a s
collected t o c o n f i r m drag p r e d i c t i o n . P e r f o r m a n c e o f
the range t r a c k i n g s y s t e m w a s also characterized.
Practice runs t h r o u g h t h e release b o x c o n f i r m e d t h e
helicopter p i l o t ' s a b i l i t y t o m e e t altitude, speed,
h o r i z o n t a l p o s i t i o n , a n d l o a d o s c i l l a t i o n r e q u i r e m e n t s
w i t h the flight test v e h i c l e under t o w . T h e s e tests also
served as a t r a i n i n g p e r i o d f o r p e r s o n n e l m a n n i n g the
c o n t r o l v a n .
C a p t i v e - t a x i tests w e r e c o m p l e t e d to v e r i f y safe t o w o f
the flight test v e h i c l e b y the g r o u n d t o w test v e h i c l e a t
speeds u p t o 7 7 m p h . S e v e n t e e n free-taxi tests a t
speeds u p t o 6 2 m p h h a v e characterized the o p e r a t i o n
o f the a u t o n o m o u s n a v i g a t i o n , guidance, steering, and
b r a k i n g subsystems. T h e s e tests p r o v i d e d tire side
force coefficient a n d brake t o r q u e data r e q u i r e d t o
refine guidance and c o n t r o l gains. A 7 7 m p h b r a k i n g
parachute r u n w i l l b e conducted this s u m m e r d u r i n g a
regression test p e r i o d .
A series o f a u t o n o m o u s approach a n d l a n d i n g free-
flight tests are scheduled f o r the s u m m e r o f 1 9 9 8 . F o r
these tests, the S M V flight test v e h i c l e w i l l b e released
f r o m the stronghack a t about 9 , 0 0 0 f t a b o v e g r o u n d
level, about 3 n m i f r o m the t o u c h d o w n p o i n t , and a
speed o f about 9 0 kts. D u a l - g l i d e s l o p e a u t o n o m o u s
approach a n d l a n d i n g guidance l o g i c i s e m p l o y e d b y
the S M V , s i m i l a r t o that used b y the S p a c e S h u t t l e .
A f t e r release, the flight test v e h i c l e w i l l d i v e steeply
' A c t u a l l y , 1 0 0 % scale o f a n earlier design.
'' T h i s paper w a s w r i t t e n i n M a y 1998.
3

5. AIAA-98-4149
and accelerate, m a i n t a i n i n g a constant . 2 5 g n o r m a l
acceleration u n t i l r e a c h i n g a r e l a t i v e speed o f a b o u t
240 kts. A t this p o i n t the S M V flight test v e h i c l e w i l l
have entered the approach p r o f i l e , a n d it w i l l p e r f o r m a
.6g p u l l - u p t o enter a constant - 2 2 d e g steep glide
slope. W h e n a n altitude o f a b o u t 9 0 0 f t i s reached, the
vehicle w i l l p e r f o r m a second, .5g p u l l - u p t o a -1.5 deg
s h a l l o w glide slope. T h e S M V flight test v e h i c l e w i l l
d e p l o y i t s l a n d i n g gear a t a n altitude o f 150 f t , a n d
p e r f o r m a f i n a l l a n d i n g flare a t about 3 0 t o 5 0 f t a b o v e
g r o u n d l e v e l . T o u c h d o w n speed w i l l b e a b o u t 1 6 0 kts.
N o s e w h e e l steering w i l l b e used t o track t h e r u n w a y
centerline a n d closed l o o p a u t o b r a k i n g w i l l b e
e m p l o y e d t o c o n t r o l r o l l - o u t deceleration.
The Future
Future SMV Development
T h e M i n i - S p a c e p l a n e T e c h n o l o g y P r o g r a m described
a b o v e i s a p o r t i o n o f the first phase o f a p l a n n e d ( b u t
currently u n f u n d e d ) m u l t i - p h a s e d A i r F o r c e S M V
d e v e l o p m e n t a n d a c q u i s i t i o n p r o g r a m . T h e Phase I
objectives are t o e x a m i n e s y s t e m r e q u i r e m e n t s , c o n d u c t
e x p e r i m e n t a l v a l i d a t i o n o f k e y s y s t e m c o m p o n e n t s , a n d
to p e r f o r m i t e r a t i v e c o n c e p t u a l design. T h i s phase w a s
initiated i n t h e fall o f 1 9 9 6 w i t h the M i n i - S p a c e p l a n e
T e c h n o l o g y P r o g r a m . A d d i t i o n a l concept design a n d
o p t i o n a l e x p e r i m e n t a l d e m o n s t r a t i o n s a r e necessary t o
c o m p l e t e this phase. I f funds b e c o m e a v a i l a b l e ,
current A i r F o r c e plans a r e t o l e t three c o m p e t i t i v e
contracts later this year t o c o n t i n u e this phase and lead
to a d o w n - s e l e c t t o o n e contractor i n the fall o f 1 9 9 9 .
T h e Phase I I objectives a r e t o design a n d b u i l d t w o
S M V flight test vehicles, a n d t o i n c r e m e n t a l l y e x p a n d
their flight e n v e l o p e . A series o f subsonic t h r o u g h
h y p e r s o n i c p o w e r e d flight tests u s i n g e x i s t i n g r o c k e t
engine t e c h n o l o g y are planned. T h i s phase w o u l d also
include h i g h h y p e r s o n i c , s u b o r b i t a l f l i g h t
d e m o n s t r a t i o n s u s i n g e x p e n d a b l e boosters. Successful
c o m p l e t i o n o f these tests w o u l d lead t o o n e o r m o r e
o r b i t a l m i s s i o n tests. F o r this, t h e Space M a n e u v e r
V e h i c l e w o u l d b e inserted i n t o o r b i t w i t h either t h e
Space S h u t t l e o r a n expendable booster. I n Phase I I I ,
the S M V flight test vehicles w o u l d b e l a u n c h e d i n a
pop-up m o d e b y t h e Space O p e r a t i o n s V e h i c l e
suborbital d e m o n s t r a t o r .
SMV as a Technology Testbed
A Space M a n e u v e r V e h i c l e t e c h n o l o g y d e m o n s t r a t o r
can b e flight tested t o h y p e r s o n i c a n d o r b i t a l v e l o c i t i e s
and serve as a n i n e x p e n s i v e test-bed f o r a n u m b e r o f
h y p e r s o n i c a n d spaceplane technologies. D u r i n g b o t h
the ascent a n d r e e n t r y phases o f flight, t h e S M V
traverses m u c h o f the h y p e r s o n i c f l i g h t e n v i r o n m e n t
that can n o t b e s i m u l a t e d i n g r o u n d test facilities. A n
orbital S M V c o u l d b e used t o test h i g h t e m p e r a t u r e
materials, active a n d passive t h e r m a l p r o t e c t i o n
systems, a n d h i g h t e m p e r a t u r e sensor w i n d o w s . I t
c o u l d also p r o v i d e h i g h temperature, reacting g a s
f l o w f i e l d a n d b o u n d a r y layer data c r i t i c a l f o r
c o m p u t a t i o n a l f l u i d d y n a m i c s m e t h o d s v a l i d a t i o n .
S i n c e t h e v e h i c l e w i l l h a v e b o t h a e r o d y n a m i c c o n t r o l
surfaces a n d attitude c o n t r o l thrusters, guidance,
n a v i g a t i o n , c o n t r o l , a v i o n i c s , and a c t u a t i o n subsystems
and s o f t w a r e c o u l d p o t e n t i a l l y b e tested d u r i n g o n - o r b i t
a n d r e e n t r y m a n e u v e r i n g d e m o n s t r a t i o n s . T h e large
A V c a p a b i l i t y w o u l d p r o v i d e a n u n p a r a l l e l e d o n - o r b i t
m a n e u v e r i n g a b i l i t y a n d its m o d e r a t e h y p e r s o n i c lift-to-
drag r a t i o a e r o d y n a m i c shape c o u l d b e used t o
d e m o n s t r a t e single a n d m u l t i - p a s s a e r o b r a k i n g a n d
aeroassisted plane change m a n e u v e r s . S u b o r b i t a l o r
w h o l l y e n d o a t m o s p h e r i c trajectories c o u l d also b e
f l o w n t o test advanced h y p e r s o n i c a i r b r e a t h i n g engine
concepts.
Perhaps t h e greatest v a l u e o f a Space M a n e u v e r
V e h i c l e t e c h n o l o g y d e m o n s t r a t o r , h o w e v e r , w o u l d b e
its u s e as a n operations test-bed a n d t o evaluate
aircraft-like o p e r a b i l i t y a n d r e l i a b i l i t y technologies.
S M V - u n i q u e m i s s i o n s c o u l d b e f l o w n as w e l l as
s i m u l a t e d S O V m i s s i o n s . L e s s o n s learned f r o m b o t h
g r o u n d a n d o n - o r b i t o p e r a t i o n s c o u l d b e i n v a l u a b l e f o r
future reusable l a u n c h systems.
Summary
T h e Space M a n e u v e r V e h i c l e b e i n g e x a m i n e d under
the M i n i - S p a c e p l a n e T e c h n o l o g y P r o g r a m i s a s m a l l ,
reusable upper stage v e h i c l e concept w i t h a large o n -
o r b i t d w e l l t i m e a n d A V c a p a b i l i t y . I t i s a c r i t i c a l
c o m p o n e n t o f t h e o v e r a l l S p a c e O p e r a t i o n V e h i c l e
s y s t e m architecture under d e v e l o p m e n t b y t h e A i r
F o r c e Research L a b o r a t o r y . T h i s paper h a s presented
an o v e r v i e w o f t h e o n - g o i n g M i n i - S p a c e p l a n e
T e c h n o l o g y P r o g r a m , a s i g n i f i c a n t first step i n
d e v e l o p i n g the Space M a n e u v e r V e h i c l e .
Acknowledgments
C o l . C r a i g M c P h e r s o n a n d M a j . K e n V e r d e r a m e o f the
Space O p e r a t i o n s V e h i c l e P r o g r a m O f f i c e , A F R L . T h e
entire U S A F a n d B o e i n g Space M a n e u v e r V e h i c l e
t e a m , especially U S A F S M V T e s t D i r e c t o r , C a p t Jeff
J a n i c i k o f t h e Space a n d M i s s i l e S y s t e m s Center,
U S A F S M V T e s t C o n d u c t o r , C a p t . M i k e K e l l y o f the
5 8 6 F l i g h t T e s t S q u a d r o n , a n d F l i g h t T e s t P i l o t , L t .
C o l . C h e v a l l i e r o f t h e 4 2 2 T e s t a n d E v a l u a t i o n
S q u a d r o n . A l s o , M s E s t e l l e A n s e l m o a n d M r . C h r i s
C l a y o f the A i r V e h i c l e s D i r e c t o r a t e , A E R L .
References
1. H e r z b e r g , J . , A l v a r a d o , B . , a n d K i l g o r e , T . ,
" R e u s a b l e Space v e h i c l e T e c h n o l o g y and A p p l i c a t i o n s
S t u d y , " W r i g h t L a b o r a t o r y T e c h n i c a l R e p o r t , W L - T R -
9 6 - 3 0 7 0 , D e c e m b e r 1 9 9 5 .
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6. AIAA-98-4149
2. A n s e l m o , E . , D e l M u n d o , P., and C l a y , C , "Space
M a n e u v e r V e h i c l e ( S M V ) C e n t e r F u s e l a g e T e c h -
n o l o g y D e m o n s t r a t o r , " P r e s e n t e d a t the 3'^'' C o n f e r e n c e
o n N e x t G e n e r a t i o n L a u n c h Systems, Space
T e c h n o l o g y a n d A p p l i c a t i o n s I n t e r n a t i o n a l F o r u m ,
A l b u q u e r q u e , N e w M e x i c o , 2 5 - 2 9 January 1998.
5

7. Figure 1 Artist Rendition of a Space Maneuver Vehicle at Touchdown Flare
Figure 2 REFLY SMV Configuration 109-1 as Structural Baseline
6

8. AIAA-98-4149
Figure 3 SMV Wing Box and Center Fuselage Test Article
L
AFT LOAD EXTENSION •
{Steel Angle;
AFT UPPER FUSELAGE
(Graph ite/epoxy-nomex
core sandwich)
FWD UPPER FUSELAGE
(Graph ite/epoxy-nomex
core sandwich)
FWD LOAD EXTENSION
(Alum weldment and angles'"'^
bolted to fuselage)
WING LOAD EXTENSION
(Machined aluminum plate
assembly bolted to fuselage)
LOWER FUSELAGE
(One-piece graphite/epoxy-
nomex core sandwich)
Figure 4 SMV Test Article Design Highlights
7

9. AIAA-98-4149

10. Figure 7 SMV Flight Test Vehicle at Roll-Out, September 1997

11. AIAA-98-4149
Figure 10 SMV Flight Test
10

12. AIAA-98-4149