TOMMUNE TULUM MATTIKULT THE US009994335B1

(12) United States Patent (10) Patent No.: US 9 ,994,335 B1

Been (45) Date of Patent: Jun . 12, 2018
(54 ) RAPID UNMANNED AERIAL VEHICLE (56 ) References Cited
LAUNCHER (UAV ) SYSTEM U .S . PATENT DOCUMENTS
(71) Applicant: The United States of America , as 1,846,157 A * 2/1932 Stevens ....... B64F 1/06
represented by the Secretary of the 124 /25
Navy , Washington , DC (US ) 2,696,957 A * 12 / 1954 Brown ................ . B64F 1 /02
244 / 110 A
(72 ) Inventor: Robert Joseph Been , Sacramento , CA
@ 3,905, 350 A * 9/1975 Becker ............... A63H 12427 // 1417
(US) 3, 968,947 A * 7/1976 Schlegel B64F 1/ 06
244 /63
(73 ) Assignee : The United States of America , as (Continued )

???? represented by the Secretary of the

Navy , Washington , DC (US )
( * ) Notice: Subject to any disclaimer, the term of this
patent is extended or adjusted under 35
U .S .C . 154 (b ) by 261 days .
OTHER PUBLICATIONS
Novakovic et al., “ Increasing Launch Capability of a UAV Bungee
Catapult ,” Scientific Technical Review 64 (4 ) ( 2014 ).
(Continued )
(21) Appl. No.: 15 / 131, 733 Primary Examiner — Richard R Green
Assistant Examiner — Brady W Frazier
(22) Filed: Apr. 18, 2016 ( 74 ) Attorney, Agent, or Firm — Naval Postgraduate
School; James B . Potts; Lisa A . Norris
(57 ) ABSTRACT
Related U .S . Application Data The disclosure provides a rapid UAV launcher comprising
(60 ) Provisional application No. 62/ 170 ,879 , filed on Jun . an upper shuttle assembly and typically a plurality of rail
systems. Each rail system comprises a lower shuttle assem
4 , 2015 , provisional application No. 62 /275 ,864, filed bly extending into a rail channel and translating over a rail
on Jan . 7 , 2016 . surface . The rail channels of each rail system e generally
(51) Int . CI. parallel. The lower shuttle assembly of each rail system is
coupled to a winch strap at a first end and an intermediary
B64F 1/04 ( 2006 .01) rope toward the intended direction of launch . The interme
B64C 39 /02 ( 2006 .01) diary rope extends through the rail channel, through a brake
(52) U . S . CI. disposed in the rail channel, around a pulley , and couples to
CPC ............. 364F 1 /04 ( 2013 .01); B64C 39/024 a forward bungee connector coupled to an elastic unit.
(2013 .01 ); B64C 2201/084 (2013.01) During a launch sequence , a rear mounted winch reels the
(58 ) Field of Classification Search winch strap to pull the lower shuttle assembly toward the
CPC ... B64C 39/024 ; B64C 2201/084 ; B64F 1/04 ; winch , elongating the elastic unit , and providing individual
B64F 1/ 06 tension forces to the lower shuttle assembly of each rail
system .
USPC ............ .................................... 244/63
See application file for complete search history. 16 Claims, 5 Drawing Sheets

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 US 9 , 994, 335 B1
Page 2
(56 ) References Cited
U . S . PATENT DOCUMENTS
4 ,060 ,930 A * 12/ 1977 Hirtle ..................... A63H 27/ 14
446 /65
4,238,093 A * 12 / 1980 Siegel B64F 1/06
244 /63
4,678 , 143 A * 7/ 19871 Griffin
Griffin ....... ....... B64F 1 /06
244/63
4 ,909 ,458 A * 3/ 1990 Martin . . . B64F 1 / 06
244 /63
5 ,671,722 A * 9 / 1997 Moody ................. . . . . F41B 7 / 00
124 / 17
5 ,695 ,153 A 12 / 1997 Britton et al.
6 ,457,673 B1 * 10 / 2002 Miller ............... B64F 1 /06
244 /63
6 ,851,647 B1 * 2 /2005 Rosenbaum .............. 364F 1/06
244 /63
8 ,584 ,985 B2 11/ 2013 Wooley et al.
2003/0116677 A1 * 6 / 2003 Young ... ................. A63H 27 /14
244 /63
2006/0186266 A1* 8/2006 Kennedy ............... A63H 27 / 14
244 /63
2007/0252034 A1 * 11 /2007 McGeer B64C 39 /024
244 /63
2013/0277497 A1* 10 /2013 Jones ... B64F 1/ 06
244 /63
2015/0060600 A1 * 3/2015 Tully .................. B64F2441//63
08

OTHER PUBLICATIONS
Novakovic et al.,“ Analysis of a UAV Bungee Cord Launching
Device ,” Scientific Technical Review 63 (3 ) (2013 ).
* cited by examiner
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 US 9 ,994,335 B1
RAPID UNMANNED AERIAL VEHICLE equal partitioning of the resultant force across all rail
LAUNCHER (UAV ) SYSTEM systems in a direction generally parallel to the axes of the
rail channels mitigates any misalignment tendencies during
RELATION TO OTHER APPLICATIONS launch which might otherwise occur in a multiple rail launch
5 system where the overall resultant force is applied at a single
This patent application claims priority from provisional location on the shuttle assembly . The UAV launcher dis
patent application 62 / 170,879 filed Jun . 4 , 2015 and provi closed herein provides for the rapid launch ofmultiple UAVs
sional patent application 62 /275 ,864 filed Jan . 7 , 2016 , both safely, effectively , and in quick succession , and provides a
of which are hereby incorporated by reference . compact design enhancing portability and allowing for rela
10 tively independent operation .
FIELD OF THE INVENTION These and other objects, aspects, and advantages of the
present disclosure will become better understood with ref
One or more embodiments relates to an apparatus and erence to the accompanying description and claims.
method of use for a catapult UAV launcher comprising
typically a plurality of rail systems and utilizing a plurality 15 SUMMARY
of elastic units such as bungees for motive force . The
catapult system partitions an overall force generated by The UAV launcher disclosed comprises an upper shuttle
elongation of the elastic units using a winch into substan - assembly and one or more rail systems. Each rail system
tially equivalent forces applied within each rail system to comprises a lower shuttle assembly coupled to the upper
provide alignment and uniform acceleration during launch . 20 shuttle assembly . In an individual rail system , the lower
shuttle assembly extends into a rail channel and may trans
BACKGROUND late through the rail channel over a rail surface . The lower
shuttle assembly is coupled to a winch strap at one end and
Utilization of unmanned aerial vehicles (UAVs) is rapidly coupled to an intermediary rope at an end toward the
increasing in private , commercial, and military applications. 25 intended . direction of launch . The intermediary rope extends
These aircraft are powered aerial vehicles capable of flight through the rail channel and around a pulley at the launching
either under human control or autonomously, and may be end of the UAV launcher, and subsequently couples to a
designed to function as traditional rotary wing, multi- rotor, forward bungee connector. An elastic unit is coupled to the
or fixed -wing platforms. UAVs are frequently deployed in forward bungee connector and additionally coupled to an aft
efforts related to search and rescue, meteorological assess - 30 bungee connector. During a launch sequence , a rearmounted
ments, traffic surveillance , agricultural crop monitoring, and winch reels the winch strap to pull the lower shuttle assem
others , and are capable of performing highly diverse and bly (and upper shuttle assembly ) toward the winch , resulting
increasingly complicated missions . Mechanisms for safe and in the intermediary rope displacing the forward bungee
effective launching is a significant area of current interest connector and elongating the elastic unit. This occurs simul
and a variety of means have been employed , including 35 taneously in all the rail systems comprising the UAV
horizontal take - off and landing (HTOL ) when a prepared launcher, so that the total energy stored within the elongating
surface is available, catapulted or zero -length rocket-pow - elastic units is portioned evenly for distribution to each
ered launches when runways are precluded , and vertical respective rail system . At a particular point, the winch is
take-off and landing (VTOL ). In generally limited cases released and the retracting bungees act to pull equally on
hand-launching may be employed if the UAV is sufficiently 40 each lower shuttle assembly , rapidly translating the shuttle
light and has a sufficiently low stall speed . assembly toward the pulley. This translation continues until
A developing mission area that is of particular interest to the lower shuttle assembly in each rail system encounters a
many entities in the defense and commercial sectors is that rubber pad brake disposed within the rail channel of each rail
of UAV swarming , which requires multiple UAVs to be system . Generally simultaneously, the winch strap is at the
launched in a relatively short period of time. Under these 45 bitter end of travel and acts to stop the lower shuttle
scenarios , the launcher must provide sufficient force for assembly as the lower shuttle assembly encounters the
launch in a relatively fast cycle in order to maximize the brake. The brake arrests shuttle assembly motion and a
usability of the entire swarm once airborne . Further, if such loaded UAV ejects. In certain embodiments, the brake is
a launch is intended from relatively remote areas, the positioned such that when contact with the lower shuttle
launcher needs to provide this with relatively compact, 50 assembly occurs , the elastic unit of each rail systems arrests
transportable design and with a relative minimum of force - in a partially elongated state , so that the elastic unit provides
bearing components to enhance reliability . Additionally and generally linear characteristics and acceleration over the
ideally , the launcher should additionally require a minimum launch cycle .
of consumables such as compressed air canisters or other When the UAV launcher comprises a plurality of rails
motive means, in order to enhance its overall portability and 55 systems, the rail channels of each rail system are generally
operational independence . parallel, and the elastic units within each rail systems
Provided here is a UAV launcher operating a catapulted provide substantially equivalent force on the lower shuttle
shuttle where one or more rail systems, typically at least two, assembly of the rail system , in order to mitigate any mis
provide motive force to the shuttle assembly through the use alignment which might occur as the upper shuttle assembly
of tensioned elastic members . When a plurality of rail 60 translates during a launch cycle . Generally , the winch strap
systems is present, the elastic members are independently of each rail systems is coupled to and reeled by a single ,
tensioned within each rail system in order to equally parti- common winch shaft to assist in establishing essentially
tion the overall resulting force acting on the shuttle assembly equivalent elongation of each of the elastic units. Similarly ,
during launch , in order to maximize possible cycling of the each elastic unit possesses a substantially equivalent spring
system manner which avoids excessive hysteresis and inef- 65 constant, so that forces generated as a result of the generally
ficiency introduced through use of larger components typi- equivalent elongation are similarly equivalent. This genera
cally found in single rail launching systems. Additionally, tion of largely equal forces within each rail system provides
 US 9 ,994 ,335 B1
for equal forces and acceleration of the lower shuttle assem shuttle assembly 103 extends into rail channel 115 and is in
bly within the rail system during launch . Additionally , the contact with rail surface 104 such that during operation of
use of the intermediary rope over a pulley within each rail launcher 100 , upper shuttle assembly 102 and lower shuttle
system to transmit the tension force of the relaxing elastic assembly 103 may translate along or over some length of rail
members to the lower shuttle assembly allows use of a 5 surface 104 . Rail channel 115 extends substantially over the
redirecting pulley having minimum mass , friction , and iner - length of rail surface 104 to allow corresponding translation
of "upper shuttle assembly 102 when lower shuttle assembly
tia , and avoids reversing the direction of the elastic members 01
to mitigate losses which might otherwise occur if the elastic 103 translates . As indicated , rail surface 104 is fixably
member extended over the pulley . The disclosure further attached to a foundation 105 . In a particular embodiment,
provides a method for launching a UAV using the disclosed 10 lower shuttle assembly 103 comprises a slider assembly in
UAV launcher. contact with rail surface 104, and the slider assembly slides
The novel apparatus and principles of operation are on rail surface 104 during translation of lower shuttle
further discussed in the following description . assembly 103. In another embodiment, a shuttle assembly
stop 146 is coupled to UAV launcher 100 to arrest translation
BRIEF DESCRIPTION OF THE DRAWINGS 15 of lower shuttle assembly 103 toward the winch , as will be
discussed . in some embodiments , upper shuttle assembly
FIG . 1 illustrates an embodiment of the rapid unmanned 102 comprises a UAV support member 161 to motivate a
aerial vehicle launcher. loaded UAV during a launch sequence and a UAV hook 162
FIG . 2 illustrates a second view of the rapid unmanned to prevent a loaded UAV from becoming airborne before the
aerial vehicle launcher. 20 launch sequence completes .
FIG . 3 illustrates another embodiment of the rapid As illustrated at FIG . 1, a winch strap 106 is connected
unmanned aerial vehicle launcher. from lower shuttle assembly 103 , proceeds through a portion
FIG . 4 illustrates a second view of the embodiment of of rail channel 115 , and extends to a winch 107 . Winch 107
FIG . 3 . is coupled to launcher foundation 105 , typically fixably
FIG . 5 illustrates a specific embodiment of a plurality of 25 attached . An intermediary rope 108 extends from an oppo
bungees. site side of lower shuttle assembly 103 , proceeds through
FIG . 6 illustrates a specific embodiment of a bungee another portion of rail channel 115 , extends through a brake
connector for a plurality of bungees . 109 , and around a pulley 110 . Brake 109 is disposed at least
FIG . 7 illustrates a second view of the bungee connector partially within rail channel 115 such that brake 109 acts to
of FIG . 6 . 30 arrest translation of at least lower shuttle assembly 103.
FIG . 8 illustrates an embodiment of an aft bungee con - Pulley 110 is coupled to UAV launcher 100 so that, from
nector. pulley 110 . intermediary rope 108 extends through a bungee
FIG . 9 illustrates a process flow diagram of a method for enclosure 116 to connect to a forward bungee connector 111 .
launching a UAV in accordance with one embodiment of the Forward bungee connector is connected to an elastic unit
invention. 35 generally indicated at 147 and represented as a first plurality
Embodiments in accordance with the invention are further of bungees comprising bungee 112 and bungee 113 . Elastic
described herein with reference to the drawings. unit 147 comprising bungees 112 and 113 is connected to an
aft bungee connector 114 which is attached to launcher
DETAILED DESCRIPTION foundation 105 , Typically each bungee in the first plurality
40 of bungees are individually attached to forward bungee
The following description is provided to enable any connector 111 and aft bungee connector 114 , and each
person skilled in the art to use the invention and sets forth bungee extends from forward bungee connector 111 to aft
the best mode contemplated by the inventor for carrying out bungee connector 114 through bungee enclosure 116 . Addi
the invention . Various modifications, however, will remain tionally and regarding FIG . 1, each of winch strap 106 ,
readily apparent to those skilled in the art, since the prin - 45 lower shuttle assembly 103 , rail channel 115 , Rail surface
ciples of the present invention are defined herein specifically 104 , intermediary rope 108 , brake 109 , pulley 110 , forward
to provide a UAV launcher and method of use for a catapult bungee connector 111 , the first plurality of bungees, and aft
UAV launcher employing motive force generated through bungee connector 114 have at least one counterpart not
the elongation of elastic members . Embodiments in accor- visible at FIG . 1 , as will be discussed.
dance with the invention rapidly launch multiple small 50 Selected components discussed above and illustrated at
Unmanned Aerial Vehicles (UAVs). Embodiments in accor - FIG . 1 comprise a rail system , where the rail system com
dance with the invention have application in areas utilizing prises rail channel 115 , rail surface 104 , lower shuttle
multiple UAVs, such as in research , development, and assembly 103 , winch strap 106 , brake 109, elastic unit 147 ,
utilization of swarm UAV technology in military and Human forward bungee connector 111 , aft bungee connector 114 ,
Assistance and Disaster Relief (HADR ) projects . The dis - 55 intermediary rope 108 , and pulley 110 . Within the first rail
closed launcher is generally designed for performance , reli- system , lower shuttle assembly 103 contacts rail surface 104
ability , operator safety , robustness , speed of launch repeti and is coupled to the upper shuttle assembly, winch strap
tion , constructability , and maintainability , and with minimal 106 extends through a portion of rail channel 115 and
setup time. couples to lower shuttle assembly 103 and winch 107 , brake
Launcher 100 is generally illustrated at FIGS. 1 and 2 , 60 109 is positioned within rail channel 115 to arrest movement
where FIGS . 1 and 2 are oriented as indicated by the of lower shuttle assembly 103 along rail surface 104 , inter
respective axes shown. At FIG . 1 , Launcher 100 comprises mediary rope 108 extends from lower shuttle assembly 103 ,
a shuttle generally indicated as 101 and comprising an upper over pulley 110 , and couples to forward bungee connector
shuttle assembly 102 and a lower shuttle assembly 103, with 111 , and elastic unit 147 extends between forward bungee
lower shuttle assembly 103 coupled to upper shuttle assem - 65 connector 111 and aft bungee connector 114 . In certain
bly 102 . In a particular embodiment, lower shuttle assembly embodiments, rail surface 104 is substantially parallel to a
103 is fixably attached to upper shuttle assembly 102. Lower longitudinal axis extending through rail channel 115 , and a
 US 9, 994 ,335 B1
5
translation distance X is parallel to the longitudinal axis and sion generates an increasing spring force as shuttle assembly
extends generally from shuttle assembly stop 146 to brake 101 proceeds toward winch 107 .
109 of the rail system . The translation distance X represents When shuttle assembly 101 has been drawn over a
the translation available to lower shuttle assembly 103 while translation distance X to a particular position on rail surface
lower shuttle assembly 103 contacts rail surface 115 and 5 104 , winch 107 is released . On release , the first plurality of
moves through rail channel 115 . bungees (i.e. bungees 212 , 213 , 217 , and 218 ) and the
Typically UAV launcher 100 employs a plurality of rail second plurality of bungees (i. e. bungees 212a , 213a , 217a ,
systems such that UAV launcher 100 comprises at least a and 218a ) return to a relaxed position , acting to pull shuttle
first rail system and a second rail system . This is illustrated assembly 201 toward pulleys 210 and 210a . Correspond
at FIG , 2 , where launcher 100 is shown as launcher 200 and 10 ingly, lower shuttle assembly 203 and 203a slidably translate
viewed in accordance with the axes shown. As illustrated and /or roll along rail surfaces 204 and 204a toward pulleys
and regarding the first rail system , rail channel 115 is 210 and 210a , until the progress of shuttle assembly 201 is
indicated as first rail channel 215 extending in the direction impeded by the brake 109 . The winch straps lengths are
of the x -axis shown . Upper shuttle assembly 202 is coupled typically sized such that straps act as primary brakes and
to first lower shuttle assembly 203 , which extends into first 15 brake 109 acts to simultaneously stop shuttle assembly 101.
rail channel 215 and contacts first rail surface 204 . Brake Upon encountering the brake , movement of shuttle assembly
109 of FIG . 1 is omitted at FIG . 2 for clarity . First inter - 201 substantially ceases and the UAV positioned on shuttle
mediary rope 208 extends from first lower shuttle assembly assembly 201 launches from the forward momentum
203 and extends through first rail channel 215 , around first imparted to the UAV during the launch process . As dis
pulley 210 , through first bungee enclosure 216 , and connects 20 cussed , in some embodiments , launcher 100 further com
to first forward bungee connector 211 . Bungee 212 and prises a shuttle assembly stop 146 which arrests movement
bungee 213 are visible behind first forward bungee connec - of at least one lower shuttle assembly such as 103 and /or the
tor 211 and coupled to first forward bungee connector 211. upper shuttle assembly 102 when lower shuttle assembly
Also illustrated are bungees 217 and 218 , similarly coupled 103 translates toward winch 107 along rail surface 104 .
to first forward bungee connector 211 . Bungees 212 , 213 , 25 Shuttle assembly stop may be any device or mechanical
217 , and 218 are further coupled at respective opposite ends arrangement configured to arrest at least one shuttle assem
to an first aft bungee connector (not shown ). Additionally , a bly and /or the upper shuttle assembly.
first winch strap (not shown ) extends from first lower shuttle In a particular embodiment comprising a first and second
assembly 203 to a winch (not shown ). rail system , the rail surface of the first rail system is parallel
Regarding the second rail system of FIG . 2 , a second rail 30 to a first longitudinal axis extending through the first rail
channel 215a and second rail surface 204a similarly extend channel, and the rail surface of the second rail system is
in the direction of the x -axis shown . A second lower shuttle parallel to a second longitudinal axis extending through the
assembly 203a is coupled to upper shuttle assembly 202 and second rail channel, and the first longitudinal axis is sub
extends into second rail channel 215a as illustrated . A stantially parallel to the second longitudinal axis . Here ,
second intermediary rope 208a extends from second lower 35 " parallel " or " substantially parallel” mean that a first direc
shuttle assembly 203a , extends through second rail channel tion vector is parallel to a first line and a second direction
215a , around second pulley 210a, through second bungee vector is parallel to a second line , and the angle between the
enclosure 216a , and couples to second forward bungee first direction vector and the second direction vector is less
connector 211a . Bungees 212a , 213 , 217a , and 218a com - than 5 degrees, preferably less than 2 degrees, and more
prise a second plurality of bungees , and are individually 40 preferably less than 1 degree . Similarly, when a surface is
connected to second forward bungee connector 211a and a substantially parallel to the first line, this means that a 3rd
second aft bungee connector (not shown ) at respective direction vector is parallel to the surface and co -planer with
opposite ends . Additionally, a second winch strap (not the first line, and the angle between the first direction vector
shown) extends from second lower shuttle assembly 203a to and the third direction vector is less than 5 degrees , prefer
the winch (not shown ). The winch typically comprises a 45 ably less than 2 degrees , and more preferably less than 1
common shaft to which both winch straps are connected , degree . in another embodiment, the rail surface of the first
such that rotation of the common shaft generates substan - rail system and the rail surface of the second rail system are
tially equal tension in both the first winch strap and second substantially co - planer. Here , “ co -planer ” or “ substantially
winch strap . co - planer ” mean thatover a translation distance X - available
In a typical operation , a UAV is positioned on upper 50 to a lower shuttle assembly while the lower shuttle assembly
shuttle assembly 201 , and winch 107 is employed to place contacts a rail surface , the rail surface of the first rail system
both first and second winch straps in tension , drawing shuttle and the rail surface of the second rail system are in -plane
assembly 101 ( 201) comprising upper shuttle assembly 102 with a given geometric plane to within 0 .01 X , preferably
(202 ), first lower shuttle assembly 203 , and second lower to within 0 .005 X7, and more preferably to within 0 .002 X ,
shuttle assembly 203a toward winch 107 . As shuttle assem - 55 The elastic units within each rail system of launcher 100
bly 101 (201 ) proceeds toward winch 107 , first intermediary are generally intended to experience substantially equivalent
rope 208 and second intermediary rope 208a are placed in elongation as the shuttle assembly is pulled toward the
tension around first pulley 210 and second pulley 210a winch , and generally intended to possess substantially
respectively, and first forward bungee connector 211 and equivalent spring constants over the elongation , so that the
second forward bungee connector 211a are pulled toward 60 elastic units provide substantially equal force to each rail
first pulley 210 and second pulley 210a . As first forward system he winch releases and the shuttle assembly is pulled
bungee connector 211 and second forward bungee connector toward the respective pulleys for subsequent UAV launch .
211a are pulled toward the corresponding pulleys, both the For example , at FIG . 2 , the first plurality of bungees and the
first plurality of bungees (i .e . bungees 212, 213 , 217 , and second plurality of bungees each relax in a manner which
218 ) and the second plurality of bungees (i.e . bungees 212a , 65 provides substantially equal force on lower shuttle assembly
213a , 217a , and 218a ) extend as a group , due to the 203 and 203a . The substantially equal force is intended to
anchoring of both pluralities at foundation 105 . This exten evenly partition overall force to mitigate loading on indi
 US 9 ,994,335 B1
vidual rail systems, as yell as act to maintain the alignment tudinal axis L? and second direction vector uz parallel to
of lower shuttle assembly 203 and 203a within the respec second longitudinal axis L2, and the angle between u , and uz
tive rail channels as shuttle assembly 201 travels toward less than 5 degrees , preferably less than 2 degrees, and more
pulleys 210 and 210a . In an embodiment, a first force F? is preferably less than 1 degree , as earlier discussed . Similarly ,
needed to extend the elastic unit of a first rail system over a 5 a third direction vector uz is parallel to rail surface 404 and
distance Xx and a second force F2 is needed to extend the co -planer with first longitudinal axis L , and a fourth direc
elastic unit of a second rail system over the distance Xx , and tion vector u , is parallel to rail surface 404a and co - planer
0 .95F / F , s1. 1, preferably 0 . 95sF , /F , s1.05, more prefer - with second longitudinal axis L2, and the respective angles
ably 0 . 99 SF /F , s1.01. Similarly in an embodiment, the between u , and uz and u , and u , are less than 5 degrees ,
elastic unit of the first rail system has a spring constant K 10 preferably less than 2 degrees, and more preferably less than
equal to F , /Xx and the elastic unit of the second rail system 1 degree .
has a spring constant K , equal to F2/Xx, and 0. 95K , /K 51.1, In certain embodiments , brake 409 and 409a are placed
preferably 0. 955K ,/K251.05 , more preferably 0 .995K , within rail channels 404 and 404a respectively in order to
K2s1 .01. arrest the motion of lower shuttle assemblies 403 and 403a
Additionally, in order to provide the substantially equiva - 15 while the respective elastic units of the rail systems remain
lent forces the respective elongation of the first elastic unit in a tensioned position with elongation of the elastic unit
and the second elastic unit are typically intended to be generally greater than 10 % , preferably 15 % , more prefer
generally equivalent during a launching operation . Toward ably 20 % . Similarly , when the lower shuttle assemblies are
this end and in a particular embodiment, when the lower withdrawn from the brake to a position corresponding to the
shuttle assembly of a first rail system is in contact with the 20 translation distance X , the respective elastic units of the rail
brake of the first rail system , a distance between the aft systems remain in a tensioned position with elongations
bungee connector of the first rail system and the forward generally less than 90 % , preferably less than 85 % , more
bungee connector of the first rail system is equal to XB1, and preferably less than 80 % . The elongation range of from
when the lower shuttle assembly of the second rail system is about 20 % to about 80 % generally allows the elastic unit to
in contact with the brake of the second rail system , a distance 25 operate in the elongation range where the force versus
between the aft bungee connector of the second rail system displacement characteristics of the elastic unit are generally
and the forward bungee connector of the second rail system linear. Further, by maintaining the elastic unit at an elonga
is equal to XB2, and 0 . 90sXB1/XB251. 10 , preferably tion generally less than 80 % at launch , jerk of the shuttle
0 .955Xp1 / X 1 .05, and more preferably 0 . 99sX assembly may be mitigated as the lower shuttle assemblies
XB251.01, such that the first and second elastic units have 30 proceed toward the respective pulleys. Further, ceasing
generally equivalent lengths when the respective elastic relaxation of the elastic units through the action of the brake
units are in a minimum tension during a launch operation . while the elastic units remain under tension prevents the
Similarly , in an embodiment, when the shuttle assembly is excessive vibration of and accompanying wear to the elastic
pulled by a winch strap in a direction toward the winch while units associated with sudden and complete relaxation ,
a lower shuttle assembly contacts the rail surface , the 35 in other embodiments , the winch comprises a winch shaft
forward bungee connector of a first rail system displaces a having an axis of rotation perpendicular to the first longi
distance Xpz and the forward bungee connector of a second tudinal axis and the winch strap of each rail system in the
rail system displaces a distance XB4, and 0 . 90 < X83 plurality is coupled to the winch shaft . This is additionally
XB451. 10 , preferably 0 .955X23 /XB451. 05 , and more pref - illustrated at FIG . 4 , where in the first rail system , rope 408
erably 0 . 99sX73 /XB431. 01, such that the first and second 40 extends over pulley 410 and couples to lower shuttle assem
elastic units experience generally equivalent elongation as bly 403 within rail channel 415 , and winch strap 406 couples
the shuttle assembly translates toward a launch position to lower shuttle assembly 403 within rail channel 415 before
In some embodiments where a first rail system has a first attaching to winch shaft 460 . Similarly in the second rail
longitudinal axis extending through its rail channel, each railsystem , rope 408a extends over pulley 410a and couples to
system in the plurality of rails systems has a longitudinal 45 lower shuttle assembly 403a within rail channel 415a, and
axis extending through its respective first rail channel, and winch strap 406a couples to lower shuttle assembly 403a
every longitudinal axis in the plurality is substantially par- within rail channel 415a before additionally attaching to
allel to the first longitudinal axis. As an example, FIG . 3 winch shaft 460. Winch shaft 460 comprises winch 407. At
illustrates a view of launcher 100 comprising shuttle assem - FIG . 4 , an axis of rotation R , of winch shaft 460 is
bly 302 and lower shuttle assemblies 303 and 303a within 50 perpendicular to first longitudinal axis L , and winch straps
rail channels 315 and 315a and slidably contacting rail 406 and 406a are each coupled to winch shaft 460. With
surfaces 304 and 304a respectively. Lower shuttle assem - second longitudinal axis L , substantially parallel to first
blies 303 and 303a are individually coupled to intermediary longitudinal axis L , as occurs at FIG . 4 , this arrangement
ropes 308 and 308a , which respectively extend over pulleys allows each rotation of the single winch shaft 460 to reel
310 and 310a before coupling to forward bungee connectors 55 substantially equal portions ofwinch straps 406 and 406a. In
311 and 311a . FIG . 4 presents a cross -section view of FIG . a particular embodiment where a first winch strap and a
3 rotated 90 degrees and sectioned in accordance with the second winch strap are connected to a winch shaft, a single
cutting plane illustrated. Brake 109 of FIG . 1 is not shown rotation of the winch shaft reels a length of the first winch
at FIG . 3 for clarity but is included at FIG . 4 , as brake 409 . strap equal to X , and reels a length of the second winch
At FIG . 4 , first longitudinal axis L , extends through rail 60 strap equal to XL2, and 0 . 90sXz1 /X _251 . 10 , preferably
channel 415 and second longitudinal axis L , extends through 0 .955XL /X _ 251 .05, and more preferably 0 .99sX !
rail channel 415a . In the embodiment illustrated , first lon - X , 31.01. Reeling substantially equivalent lengths with a
gitudinal axis L , is substantially parallel to rail surface 404 common shaft assists in providing for the elastic members of
and second longitudinal axis L , is substantially parallel to the first and second rail systems to be extended in a
rail surface 404a . Additionally , first longitudinal axis L? is 65 substantially equivalent manner during the process, so that
substantially parallel to second longitudinal axis L2. This is the resulting tension forces acting on each lower shuttle
indicated by first direction vector u , parallel to first longi- assembly through the intermediary rope and shown as Fri
 US 9 ,994 ,335 B1
10
and FR2 are generally equivalent. These balanced forces parallel to a longitudinal axis perpendicular to axis LB1, for
assist in maintaining the alignment ofsubstantially conform example, a longitudinal axis of bungee enclosure 516 . In a
ing lower shuttle assembly 403 within rail channel 415 and particular embodiment, a first plurality of bungees is
lower shuttle assembly 403a within rail channel 415a when attached to a forward bungee connector with reflection
the winch is released and shuttle assembly 401 rapidly 5 symmetry around an axis LB and the first plurality is
accelerates toward pulleys 410 and 410a under the tension attached to an aft bungee connector with reflection symme
forces FR, and F . This balancing is additionally assisted in try around an axis Lry andL and L are substantially
embodiments earlier discussed , where a first force F , parallel. In another embodiment , an extension axis is per
extends the elastic unit of a first rail system and a second pendicular to both axis LR , and axis LR and the extension
force F , extend the elastic unit of a second rail system both 10 axis intersects the forward bungee connector 111 and the aft
over a distance Xx, and 0 . 95F / F , s1. 1 , preferably 0 . 955F / bungee connector 114 of FIG . 1 . In a further embodiment,
F251.05, more preferably 0 . 995F /F251.01. Additionally in each bungee in the first plurality is substantially parallel to
some embodiments , the length of the winch straps is estab - the extension axis when the forward bungee connector of the
lished to that the winch straps become taut as the lower first rail system displaces the distance XB3, and in a still
shuttle assemblies approach the brake, so that tension in the 15 further embodiment, a section of the intermediary rope
winch straps assists the brake in arresting the lower shuttle coupled to the forward bungee connector is substantially
assemblies. parallel to the extension axis, such that the first plurality
As indicated , in some embodiments , the elastic unit of a bungees
given rail system comprises a plurality of bungees , with each
and the section of the intermediary rope are gen
erally aligned .
bungee in the plurality coupled to the forward bungee 20 An embodiment of a particular forward bungee connector
connector of the given rail system at a first end and coupled is illustrated at FIGS . 6 and 7 as forward bungee connector
to the aft bungee connector of the given rail system at a 611 and 711 respectively , illustrated as components within a
second end . Each plurality of bungees comprises at least section of launcher 101. FIG . 6 illustrates bungees 548 and
two, preferably at least four , more preferably at least six 547 as 648 and 647 and surrounded by bungee enclosure
separate bungees and typically each bungee in a given 25 616 , and indicates the respective bungees coupled to for
plurality of bungees exhibits substantially equivalent elas - ward bungee connector 611 through quick link devices 651
ticity . In an embodiment, each bungee in a plurality of and 652 . FIG . 7 illustrates the forward bungee connector in
bungees has a spring constant k ; over a distance Xx, and the a view rotated 90 degrees, and indicates bungees 548, 549,
spring constant k , for each bungee is within 10 % of a mean and 550 as 748 , 749 , and 750 within bungee enclosure 716 ,
km, where k ,, is a mean among all k , in the plurality, such that 30 with the respective bungees coupled to forward bungee
for any ki, 0. 9sk ,/km - 1. 1, preferably 0. 95sk ,/km, < 1.05 , and connector 711 through quick link devices 751, 752 , and 753 .
more preferably 0 .99sk ,/km31.01. Among other advantages , In the embodiment illustrated at FIGS. 6 and 7 , the forward
these arrangements in a given plurality of bungees may act bungee connector utilizes two plates 654 and 655 rigidly
to mitigate the impact of fatigue experienced by a given connected by bolting members such as 656 in order to
bungee in a plurality as a result ofmany cycles of launcher 35 establish bungee connections which exhibit the reflection
operation . Additionally, the use of an intermediary rope symmetry of FIG . 5 . This is also reflected at FIG . 7,
coupled to a forward bungee connector and extending over illustrating plate 754 and bolting member 756 . Forward
a pulley as discussed allows the intermediary rope to pull the bungee connector couples to an intermediary rope at FIG . 6
lower shuttle assembly , rather than employing the elastic via quick link 655 , shown as 755 at FIG . 7 . In a particular
units directly . This allows the use multiple bungees in a 40 embodiment, an aft bungee connector is configured similarly
plurality to be utilized as the elastic unit without requiring a and an analogous quick link to 655 couples to foundation
corresponding increase in the width and size of the pulley to 105 of FIG . 1 . As an example , FIG . 8 illustrates aft bungee
accommodate additional bungees , and thereby mitigates or connectors in a first and second rail system , with bungees
eliminates the increased mass, friction , and additional inertia 750, 749, and 748 ofFIG . 7 represented as 850, 849 , and 848
such a necessary increase in the pulley would introduce into 45 within bungee enclosure 816 . Bungees 850 , 849, and 848 are
the system . individually coupled to aft bungee connector 814 through
In a particular embodiment, a plurality of bungees is quick links such as quick link 851, and aft bungee connector
attached to a forward bungee connector such as 111 and an 814 is coupled to launcher foundation 805 via quick link
aft bungee connector such as 114 in a manner such that the 858 . A corresponding aft bungee connector for a second
collection of connections of individual bungees display 50 plurality of bungees comprising a second rail system in the
reflection symmetry around some axis . For example , FIG . 5 plurality of rail systems is additionally shown, with bungees
illustrates a first plurality of bungees generally indicated by 850a , 849a , and 848a within bungee enclosure 816a and
520 and comprising bungee 547, 548 , 549 , and 550, among individually coupled to aft bungee connector 814a through
others illustrated . The first plurality comprises the six sepa quick links such as quick link 851a , and aft bungee con
rate bungees surrounded by a bungee enclosure 516 and 55 nector 814a coupled to launcher foundation 805 via quick
viewed along the x -axes of FIGS. 1 -4 as indicated . At FIG . link 858a.
5 , individual bungees are illustrated as circles with connec - In a particular embodiment, winch 107 is a powered
tion points to a forward or aft bungee connector generally winch , such as a battery powered winch . In one embodi
indicated at the approximate center of each circle . As ment, the battery powered winch is a customized recre
illustrated , the first plurality 520 is arranged such that the 60 ational boat commercial off- the - shelf (COTS ) winch . In one
collection of connections points exhibit a reflection symme- embodiment, a 12 - volt battery is connected to winch 107 to
try around axis Lg Such an arrangement may tend to supply power to winch 107 ; a fully charged battery is
mitigate variabilities in the individual spring constants ki calculated to provide over 500 launches on a single charge ,
which may be present in a given plurality of bungees , and in another embodiment, launcher 100 further includes a
assists in symmetrically distributing generally equal tension 65 control system 136 . In one embodiment control system 136
forces in order to produce an overall resultant force on the is used to control the retraction and release of the winch
forward or aft bungee connector which is substantially straps. In one embodiment, control system 136 includes a
 US 9 ,994 ,335 B1
12
control switch having three positions corresponding to : (1 ) a plurality of rail systems where each rail system com
neutral, (2 ) pull shuttle back by rotating the winch in the prises :
reel- in direction of rotation , and ( 3 ) release winch from a rail channel comprising a rail surface , where the rail
locked position to release shuttle by rotating the winch in the surface of a first rail system of the plurality of rail
reel-out direction of rotation . systems is substantially parallel to a first longitudinal
In one embodiment, launcher 100 further includes mis axis and where the rail surface of a second rail
cellaneous hardware, such as fittings, pulleys and other system of the plurality of rail systems is substantially
components as shown in the drawings. parallel to a second longitudinal axis , and where the
FIG . 9 illustrates a process flow diagram of a method 940 first longitudinal axis is substantially parallel to the
for launching a UAV using launcher 100 in accordance with 10 second longitudinal axis ;
one embodiment of the invention . In operation 941 an a lower shuttle assembly contacting the rail surface and
operator loads a UAV , such as a thirty (30 ) pound UAV , on the lower shuttle assembly coupled to the upper
the shuttle at the forward end of the rails while the pluralities shuttle assembly ;
of bungees are not under tension . For example, when the a winch strap extending through some portion of the
control switch of the control system is set to position 1 , the 15 rail channel, where a first end of the winch strap is
operator places the UAV on the top plate of the shuttle and coupled to the lower shuttle assembly and a second
for example engages the UAV hook with a UAV hook end of the winch strap is coupled to the winch ;
engagement on the upper shuttle assembly . In operation 942 , a brake disposed within the rail channel and positioned
the operator then engages the winch to pull the shuttle back within the rail channel such that the lower shuttle
to the cocked position in approximately 10 seconds. For 20 assembly is between the brake and the winch strap ,
example , when the control switch of the control system is set where the brake is disposed within the rail channel to
to position 2 for the winch reel- in rotation . As the winch arrest movement of the lower shuttle assembly over
straps are retracted toward the back of launcher 100 , the the rail surface ;
shuttle is pulled back along the rails and the bungee cords an elastic unit where the elastic unit is coupled to a
attached to the shuttle are extended toward the pulleys. 25 forward bungee connector and an aft bungee con
When the shuttle reaches a preferred stop point along the nector, where the aft bungee connector is coupled to
rails, the winch is stopped and locked in position by the the launcher foundation , and where the elastic unitof
winch . In operation 943 the operator releases the winch by the first rail system of the plurality of rail systems has
pushing a command button on the control system for the a spring constant K over a distance Xx and the
winch reel- out rotation to launch the UAV . For example , 30 elastic unit of the second rail system of the plurality
when the control switch of the control system is set to of rail systems has a spring constant K2 over the
position 3 , the winch drum is released from the locked distance Xx, and where 0 .955K ,/K251.05 ;
position allowing the winch straps to uncoil from the winch an intermediary rope comprising a first rope portion
mechanism . When the winch is released from the locked disposed within the rail channel, where a first end of
position , the shuttle travels forward and carries theUAV by 35 the intermediary rope is coupled to the lower shuttle
pushing the rear of the UAV and holding the UAV on the assembly and a second end of the intermediary rope
shuttle using the forward hook of the UAV to prevent the is coupled to the forward bungee connector, and
UAVs tendency to want to rise off the shuttle prior to the where the lower shuttle assembly is between the first
shuttle hitting the brake system at the end of the rails. In rope portion and the winch strap ; and
operation 943 , the shuttle is stopped by the winch straps and 40 a pulley in contact with the intermediary rope between
hits the brake system at the end of the rails , simultaneously . the first end of the intermediary rope and the second
In operation 944 the UAV is ejected off the shuttle and into end of the intermediary rope and positioned to estab
the air. In one embodiment, the UAV is ejected from the rails lish the first rope portion disposed within the rail
at approximately 35 miles per hour (mph ). channel.
It is to be understood that the above-described arrange - 45 2. The UAV launcher of claim 1 where the elastic unit is
ments are only illustrative of the application of the principles a plurality of bungees where each bungee in the plurality of
of the present invention and it is not intended to be exhaus - bungees is coupled to the forward bungee connector at a first
tive or limit the invention to the precise form disclosed . end of the each bungee and coupled to the aft bungee
Numerous modifications and alternative arrangements may connector at a second end of the each bungee , and where the
be devised by those skilled in the art in light of the above 50 each bungee in the plurality of bungees has a spring constant
teachings without departing from the spirit and scope of the ki- l over a distance Xk , and where km - 1 is a mean of all ki- 1
present invention . It is intended that the scope of the in the first plurality of bungees , and where for any ki- 1 ,
invention be defined by the claims appended hereto . 0 . 95ski- 1/km - 151 .05.
In addition , the previously described versions of the 3 . The UAV launcher of claim 1 where when the lower
present invention have many advantages , including but not 55 shuttle assembly of the first rail system is in contact with the
limited to those described above . However, the invention brake of the first rail system , a distance between the aft
does not require that all advantages and aspects be incor- bungee connector of the first rail system and the forward
porated into every embodiment of the present invention . bungee connector of the first rail system is equal to XR1, and
All publications and patent documents cited in this appli - where when the lower shuttle assembly of the second rail
cation are incorporated by reference in their entirety for all 60 system is in contact with the brake of the second rail system ,
purposes to the same extent as if each individual publication a distance between the aft bungee connector of the second
or patent document were so individually denoted . rail system and the forward bungee connector of the second
rail system is equal to XB2, and where 0 .95 < XB251.05.
What is claimed is : 4 . The UAV launcher of claim 3 where the elastic unit of
1 . A UAV launcher comprising : 65 the first rail system is a first plurality ofbungees where each
an upper shuttle assembly; bungee in the first plurality of bungees is coupled to the
a winch coupled to a launcher foundation ; and forward bungee connector of the first rail system at a first
 US 9 , 994, 335 B1
13 14
end of the each bungee and coupled to the aft bungee the each rail system coupled to the lower shuttle
connector of the first rail system at a second end of the each assembly of the each rail system and the forward
bungee , and where the elastic unit of the second rail system bungee connector of the each rail system and extending
is a second plurality of bungees where every bungee in the over the pulley of the each rail system ;
second plurality of bungees is coupled to the forward bungee 5 utilizing the tension of the intermediary rope of the each
connector of the second rail system at one end of the every rail system to displace the forward bungee connector of
bungee and coupled to the aft bungee connector of the the each rail system toward the pulley of the each rail
second rail system at another end of the every bungee . system ;
5 . The UAV launcher of claim 4 where the each bungee utilizing the displacement of the forward bungee connec
in the first plurality of bungees has a spring constant ki- 1 10 tor of the each rail system to extend the elastic member
over the distance Xx , and where k , _ , is a mean of all ki of the each rail system coupled to the forward bungee
in the first plurality of bungees , and where for any k - 1, connector of the each rail system and the aft bungee
0 . 95ski- 1/km - 151.05 . connector of the each rail system ;
6 . The UAV launcher of claim 5 where the every bungee continuing the retracting until the lower shuttle assembly
in the second plurality ofbungees has a spring constant k?-2 15 of the each rail system reaches a particular position on
over the distance Xx, and where km -2 is a mean of all k?- 2 the rail surface of the each rail system , thereby achiev
in the second plurality of bungees , and where for any ki- 2 , ing a launch position for the UAV ;
0 .95ski- 2/km - 251.05, and where 0.955km - 1/k _ 251.05. releasing the winch and allowing the elastic member of
7 . The UAV launcher of claim 3 where when the winch the each rail system to pull the lower shuttle assembly
strap of the first rail system pulls the lower shuttle assembly 20 ofthe each rail system toward the pulley of the each rail
of the first rail system in a direction toward the winch while system , thereby displacing the upper shuttle assembly
the lower shuttle assembly of the first rail system is in coupled to the lower shuttle assembly of the each rail
contact with the rail surface of the first rail system , the system toward the pulley of the each rail system and
forward bungee connector of a first rail system displaces a thereby displacing the UAV supportmember compris
distance XR3 and the forward bungee connector of a second 25 ing the upper shuttle assembly toward the pulley of the
rail system displaces a distance XB4 , and 0 .955X83! each rail system ;
XR4S1.05 . utilizing the displacement of the UAV support member to
8 . The UAV launcher of claim where the winch comprises motivate the UAV in contact with the UAV support
a winch shaft, and where the second end of the winch strap member toward the pulley of the each rail system , and
of the first rail system is coupled to the winch shaft and the 30 ejecting the UAV off the upper shuttle assembly by
second end of the winch strap of the second rail system is arresting the displacement of the lower shuttle assem
coupled to the winch shaft, and where the winch shaft has an bly toward the pulley of the each rail system using the
axis of rotation perpendicular to the first longitudinal axis . brake of the each rail system , thereby arresting the
9 . The UAV launcher of claim 8 where a single rotation displacement of the upper shuttle assembly and arrest
of the winch shaft reels a length XLi of the winch strap of 35 ing the displacement of the UAV support member
the first rail system and the single rotation of the winch shaft motivating the UAV , thereby launching the UAV.
reels a length X 2 of the winch strap of the second rail 13 . A UAV launcher comprising :
system , and 0 . 955X1/ X , 51. 05. an upper shuttle assembly where the upper shuttle assem
10 . The UAV launcher of claim 8 further comprising a bly comprises a UAV support member and a UAV
shuttle assembly stop which arrests movement of the lower 40 hook ;
shuttle assembly of the first rail system toward the winch a winch coupled to a launcher foundation ;
when the lower shuttle assembly of the first rail system a plurality of rail systems, where each rail system com
contacts the rail surface of the first rail system , and where a prises :
translation distance X , extends from the shuttle assembly a rail channel comprising a rail surface where the rail
stop to the brake of the first rail system , and where when the 45 surface is substantially parallel to a longitudinal axis
lower shuttle assembly of the first rail system translates over extending through the rail channel, and where the
the translation distance X , while contacting the rail surface longitudinal axis is substantially parallel to every other
of the first rail system , the rail channel of the first rail system longitudinal axis in the plurality of rail systems;
constrains the lower shuttle assembly of the first rail system a lower shuttle assembly contacting the rail surface and
from translating in a direction perpendicular to X , by an 50 the lower shuttle assembly coupled to the upper shuttle
amount exceeding 0 .001 X . assembly ;
11 . The UAV launcher of claim 1 where the upper shuttle a winch strap extending through some portion of the rail
assembly comprises a UAV support member and a UAV channel, where a first end of the winch strap is coupled
hook . to the lower shuttle assembly and a second end of the
12 . A method of launching a UAV using the UAV launcher 55 winch strap is coupled to the winch ;
of claim 11 comprising: a brake disposed within the rail channel and positioned
loading a UAV on the upper shuttle assembly by placing within the rail channel such that the lower shuttle
the UAV in contact with the UAV support member of assembly is between the brake and the winch strap ,
the upper shuttle assembly and in contact with the UAV where the brake is disposed within the rail channel to
hook of the upper shuttle assembly ; arrestmovement of the lower shuttle assembly over the
retracting the winch strap of each rail system in the rail surface;
plurality of rail systems using the winch and translating an elastic unit where the elastic unit is coupled to a
the lower shuttle assembly ofthe each rail system along forward bungee connector and an aft bungee connector,
the rail surface of the each rail system toward the where the aft bungee connector is coupled to the
winch , 65 launcher foundation , and where the elastic unit has a
utilizing the displacement of the lower shuttle assembly of spring constant K , over a distance Xx and an elastic
the each rail system to tension the intermediary rope of unit of any other rail system in the plurality of rail
 US 9 ,994 ,335 B1
15 16
systems has a spring constant K , over the distance XX , connector at a second end of the each bungee , and where the
and where 0 . 955K , / K , s1. 05 , and where when the each bungee in the plurality of bungees has a spring constant
lower shuttle assembly is in contact with the brake, a ki- , over the distance Xx, and where km - 1 is a mean of all
distance between the aft bungee connector and the ki- l in the plurality of bungees, and where for any ki- 1, in the
forward bungee connector is equal to XB1, and where 5 plurality of bungees, 0 . 95 sk , k / s1. 05 .
when a lower shuttle assembly of the any other rail 15 . The UAV launcher of claim 14 where when the winch
system is in contact with a brake of the any other rail strap pulls the lower shuttle assembly in a direction toward
system , a distance between an aft bungee connector of
the any other rail system and the forward bungee the winch while the lower shuttle assembly is in contact with
the rail surface, the forward bungee connector displaces a
connector of the any other rail system is equal to XB2, 10 distance
dis XB3 , and where when a winch strap of the any other
and where 0 .955X1/X3251 .05 ; rail system pulls the lower shuttle assembly of the any other
an intermediary rope comprising a first rope portion
disposed within the rail channel, where a first end of the system in the direction toward the winch while the lower
intermediary rope is coupled to the lower shuttle shuttle assembly of the any other system is in contact with
assembly and a second end of the intermediary rope is 15is aa rail surface of the any other system , the forward bungee
coupled to the forward bungee connector, and where connector
and 0 .
of the any other system displaces a distance X B4 ,
955X23 /XB451.05.
the lower shuttle assembly is between the first rope 16 . The UAV launcher of claim 15 where the winch
portion and the winch strap ; and comprises a winch shaft, where the second end of the winch
a pulley coupled to the UAV launcher and in contact with 2. strap
Sira is ofcoupled
the intermediary rope between the first end of the 20 rotation to the winch shaft and where a single
the winch shaft reels a length XLi of the winch
intermediary rope and the second end of the interme strap , and where a second end of the winch strap of the any
diary rope and positioned to establish the first rope
portion disposed within the rail channel . other rail system is coupled to the winch shaft , and where the
single rotation of the winch shaft reels a length X _2 of the
14 . The UAV launcher of claim 13 where the elastic unit s winch
is a plurality of bungees where each bungee in the plurality 25 strap of the any other rail system , and 0 . 955Xz?
of bungees is coupled to the forward bungee connector at a X _ 251.05.
first end of the each bungee and coupled to the aft bungee * * * * *