Initial Experiment in Using a Powered Parafoil for 

Employment of Intelligence, Surveillance, and 

Reconnaissance (ISR) Unattended Ground 

Sensors (UGS) 

by Michael A. Kolodny 

ARL-TR-3347 October 2004 

Approved for public release; distribution unlimited. 
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Army Research Laboratory 

Adelphi, MD 20783-1197 

ARL-TR-3347 October 2004 

Initial Experiment in Using a Powered Parafoil for 

Employment of Intelligence, Surveillance, and 

Reconnaissance (ISR) Unattended Ground 

Sensors (UGS) 

Michael A. Kolodny 

Sensors and Electron Devices Directorate, ARL 

Approved for public release; distribution unlimited. 
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4. TITLE AND SUBTITLE 

Initial Experiment in Using a Powered Parafoil for Employment of Intelligence, 

Surveillance, and Reconnaissance (ISR) Unattended Ground Sensors (UGS)

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4NOVN5

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6. AUTHOR(S) 

Michael A. Kolodny

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U.S. Army Research Laboratory 

Attn: AMSRD-ARL-SE-S 

2800 Powder Mill Road 

Adelphi, MD 20783-1197

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ARL-TR-3347 

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U.S. Army Research Laboratory 

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Approved for public release, distribution unlimited. 

14. ABSTRACT 

Experiments were run by the U.S. Army Research Laboratory at Yuma Proving Ground, AZ, on 10 and 12 June 2004 to obtain an initial 

assessment of the viability of using a powered parafoil as an unmanned air vehicle for employment of Future Combat System intelligence, 

surveillance, and reconnaissance unattended ground sensors (UGS). These experiments were conducted as an adjunct to the testing of the 

parafoil for the Special Operations Command Wind-Supported Air Delivery System program. Three flights were flown which dispensed UGS 

mass mock-ups. Two of the flights used manually released UGS while the third flight was operated autonomously. The experiments were 

designed to give an initial quick look assessment of the dispersions that might be expected in UGS parafoil employment. 

The initial assessment indicates that the powered parafoil is a viable air delivery platform. Control of the UGS release is good and dispersions 

in landing areas are minimal. Maximum dispersion for a drop of three nodes was about 7 m from the centroid of the landing locations. 

Dispersions were typically less than 3 m.

15. SUBJECT TERMS

unattended ground sensors, powered parafoil, sensor employment

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19a. NAME OF RESPONSIBLE PERSON

Michael A. Kolodny

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Unclassified 

b. ABSTRACT 

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iii

Contents 

List of Figures iv

List of Tables iv

Acknowledgments v

Disclaimer v

Executive Summary 1

1. Background 3

2. UGS Employment Concepts 4

3. Experiment Design 7

4. Test Data and Results 9

5. Summary and Conclusions 13

Distribution List 15 
iv

List of Figures 

Figure 1. Launch of powered parafoil.............................................................................................5 

Figure 2. Airborne powered parafoil. .............................................................................................5 

Figure 3. In-flight opening of payload dispensers. .........................................................................6 

Figure 4. Powered parafoil landing.................................................................................................6 

Figure 5. UGS mass mock-ups. ......................................................................................................8 

Figure 6. Typical drop dispersion. ................................................................................................11 

Figure 7. Autonomous flight relative coordinates. .......................................................................12 

List of Tables 

Table 1. UGS dispensing summary. ...............................................................................................9 

Table 2. YPG UGS drop data. ......................................................................................................10 
v

Acknowledgments 

ARL would like to acknowledge the outstanding support given by the following individuals: 

• Becky Brocato and Rick Slaughter: Yuma Proving Ground 

• MAJ Robert A. Herres: Special Operations Command 

• Robert Adam: MMIST (Mist Mobility Integrated Systems Technology, Inc.) 

ARL greatly appreciates the last-minute effort of these people in making arrangements, altering 

test plans, doing recovery, post-testing calculations, and making an enormous effort to allow 

ARL to participate in the SOCOM testing program and add the UGS employment tests. 

Disclaimer 

The perspectives expressed in this report are those of ARL and may not reflect the positions of 

TRADOC, PMs, or the Army. 
vi

INTENTIONALLY LEFT BLANK
1

Executive Summary 

Experiments were run by the U.S. Army Research Laboratory at Yuma Proving Ground, AZ, on 

10 and 12 June 2004 to obtain an initial assessment of the viability of using a powered parafoil as 

an unmanned air vehicle for employment of Future Combat System intelligence, surveillance, 

and reconnaissance unattended ground sensors (UGS). These experiments were conducted as an 

adjunct to the testing of the parafoil for the Special Operations Command Wind-Supported Air 

Delivery System program. Three flights were flown which dispensed UGS mass mock-ups. 

Two of the flights used manually released UGS while the third flight was operated 

autonomously. The experiments were designed to give an initial quick look assessment of the 

dispersions that might be expected in UGS parafoil employment. 

The initial assessment indicates that the powered parafoil is a viable air delivery platform. 

Control of the UGS release is good and dispersions in landing areas are minimal. Maximum 

dispersion for a drop of three nodes was about 7 m from the centroid of the landing locations. 

Dispersions were typically less than 3 m. 
2

INTENTIONALLY LEFT BLANK
3

1. Background 

The Army’s Future Combat Systems (FCS) and Future Force Warrior (FFW) programs have a 

requirement for intelligence, surveillance, and reconnaissance (ISR) unattended ground sensors 

(UGS). The Air Force, Marines, and Special Operations Command (SOCOM) likewise have 

requirements for ISR UGS. FCS ISR UGS are a core component of the FCS unit of action (UA) 

and are a critical asset to provide situational awareness. The fundamental operational 

requirements are as follow: 

• Employment: UGS must be employed as far as 150 km. This long-range employment 

requirement precludes hand emplacement or ground vehicle emplacement and makes air 

drop employment highly desirable during many conditions. 

• Information and persistence: UGS must provide persistent surveillance and useful ISR 

information about targets (classification, location, and direction of movement) and 

communicate this information 150 km back to the UA. Detailed UGS ISR operational 

requirements document (ORD) requirements are given in annex E of the FCS ORD. 

Currently, no air delivery platform is identified for UGS in FCS. A delivery platform is needed 

which is practical and will be an FCS available asset. The UA Mounted Battle Lab (UAMBL) at 

Ft. Knox, KY, has stated that the class IV-B unmanned air vehicle (UAV) (which includes the 

powered parafoil), high mobility artillery rocket system (HIMARS) (rocket), and the FCS nonline-of-sight (NLOS) cannon are the acceptable air delivery platforms. There are the obvious 

issues with the sensor hardware configuration and hardening for air delivery, development of the 

dispensing mechanism, variances in dispersion patterns of the nodes in the UGS field, etc. These 

issues are just beginning to be examined. 

ARL and others have considered the use of a powered parafoil as an employment platform for 

FCS ISR UGS. The parafoil is not currently a core asset to the UA or unit of employment (UE), 

and is not a complete solution to the long-range employment requirement. Using the parafoil in 

high winds will be a concern. The preference for the powered parafoil is based on several 

considerations as follows: 

• Already developed and commercially available from MMIST, (Mist Mobility Integrated 

Systems Technology, Inc.) 

• Heavy payload of close to 600 lb with round trip range of 50 km, 

• Round trip range of 650 km with 100-lb payload, 
4

• Development of an UGS dispenser system relatively easy and inexpensive, 

• Can give controlled dispensing of UGS nodes, if needed. 

2. UGS Employment Concepts 

The employment concept envisioned is to use the unmanned powered parafoil to employ far ISR 

UGS. Employment of an UGS field may be as far as 150 km—the maximum range of the UA 

area of interest. The mission of the parafoil would be to fly and air drop UGS in predefined area 

and then return to the employing unit (or some other unit). Multiple UGS fields could be 

dispensed on a single flight. MMIST’s powered parafoil has six cargo bins, each capable of 

carrying cargo or fuel tanks. If five of the six bins were used for fuel tanks, leaving a single bin 

with a 100-lb payload, the round trip range would be 650 km, assuming an average headwind 

speed of zero. Head or tail winds add directly to the ground speed as with a powered aircraft. 

Flights can be autonomous or controlled via a radio or Iridium satellite communications 

(SATCOM) link. Autonomous operation of the parafoil would require the UGS to be dropped at 

a minimum altitude above ground of approximately 800 to 1000 ft. A dispenser would need to 

be designed that has the capability to dispense one node at a time. MMIST engineers have 

indicated that this would not be difficult. 

The powered parafoil is ground launched from a pickup truck or high mobility multipurpose 

wheeled vehicle (HMMWV) with a 35-mph head wind required for launch. The parafoil flies at 

approximately 50 km/hr air speed. The payload dispenser consists of six bins, each capable of 

carrying a payload of 100 lb with a total payload limit of 573 lb. Any (or all) of the bins may be 

used for fuel tanks, trading payload for range. The maximum range is 942 km with an average 

head wind of 0 mph. With three bins of fuel, the range is about 350 km, still leaving a payload 

of 300 lb. The flight ceiling is 14,500 ft above mean sea level, allowing employment missions to 

be flown over all but the tallest mountains. The minimum launch time is 14 seconds and launch 

and recovery can be accomplished with a three-person crew. 

Figures 1 through 4 show the powered parafoil in operation. 
5

Figure 1. Launch of powered parafoil. 

Figure 2. Airborne powered parafoil. 
6

Figure 3. In-flight opening of payload dispensers. 

Figure 4. Powered parafoil landing. 
7

There are several concepts for deployment of UGS which use the powered parafoil. One is to 

have the UGS nodes dropped and then let them free fall. This would require the nodes to be 

hardened to survive impact, and issues ensuring a controlled vertical landing would have to be 

addressed. An alternate scheme would have either guided or unguided secondary mini-parafoils 

attached to the UGS. The guided mini-parafoil would allow for a more precision emplacement 

of the nodes but at added significant cost per node. Both schemes would allow for a soft landing 

with the potentially undesirable result of having each node’s location flagged with the parafoil. 

Trade-offs of employment dispersions versus the number of nodes required versus the cost of the 

secondary parafoils would have to be assessed. 

3. Experiment Design 

The Snowgoose powered parafoil was developed for SOCOM by MMIST, Ottawa. The tests 

conducted at the Yuma Proving Ground (YPG), AZ, were for the SOCOM WSADS program, 

which uses the parafoil for leaflet delivery and parachute re-supply. The flight scenarios and 

embedded mission software were designed for these SOCOM missions. The dispensers, which 

were designed to have the bottom open and to simply drop everything from the bin, were also 

tailored to the WSADS program. 

SOCOM and MMIST allowed ARL to place mass mock-ups of UGS in the four or five unused 

bins of the Snowgoose. Twelve aluminum mass mock-ups were built to simulate the 

approximate size and weight of an UGS node. The node model was based on the ARL 

affordable ISR UGS concept, a 3.5-inch tall, 4-inch diameter family of scatterable mines 

(FASCAM) cylindrical package with sensors, batteries, and a two-board electronics set for short 

haul communications, long haul SATCOM “reachback,” and sensor processing and signal 

conditioning. This size and shape also closely align with the proposed production-envisioned 

massively deployed UGS (MDUGS). Figure 5 shows the UGS mass mock-ups used for the 

experiment. 
8

Figure 5. UGS mass mock-ups. 

The purpose of the experiment was to get an initial indication for the UGS node dispersions that 

might be expected from a powered parafoil employment. UGS were placed on three mission 

flights. The first two were manually controlled flight with drops from an altitude of 

approximately 300 to 500 ft above ground level. The UGS had a “target” on the ground. A 

single dispensing bin was opened during each pass over this target. The Snowgoose operator 

piloted the parafoil toward a targeted release point displayed on the ground station and pushed 

the release button. On the two manually controlled flights, three bins contained two UGS nodes 

each and two of the bins contained three nodes each for a total of 12 on-board nodes. 

The third flight was an autonomous flight with autonomous UGS dispensing. This flight had 

three nodes placed in a single dispensing bin. The parafoil was programmed with a “target” on 

the ground. The Snowgoose autonomously flew to the drop point that it calculated for the 

payload to land on the target. Pinpoint accuracy was not expected on these flights. Since the 

Snowgoose navigation and dispensing software was designed for dispensing parachute payloads 

that would be affected by the local winds, it was not optimal for the node mock-ups which fell 

straight down to the ground. 

For all flights, the coordinates of the UGS landing points were surveyed. In addition, post-flight 

data of the actual release points and altitude above ground were retrieved from the Snowgoose 

flight data. This allowed for a determination of the dispersions and the “error” of the 

autonomous drop. 
9

4. Test Data and Results 

The flights produced the following dispensing of the UGS: 

Table 1. UGS dispensing summary. 

Flight No. Bin No. Quantity UGS Dispensed Drop Mode 

1&2 2 3 Manually controlled drop 

1&2 3 3 Manually controlled drop 

1&2 4 2 Manually controlled drop 

1 5 2 Manually controlled drop 

2 5 0 Bin door stuck 

1&2 6 0 Bin door stuck 

3 2 3 Autonomous drop 

Bins 5 and 6 had been damaged in earlier tests and had problems in the release lever. The bin 5 

door stuck in the second flight and the bin 6 door stuck in the first two flights. These bins had 

two UGS each that were not dispensed. After each flight, the UGS were recovered and the 

landing position of each node was global positioning system (GPS) surveyed. The drop area on 

the ground was very flat for the first two drops and consisted of a mix of sand with many stones 

and large pebbles. The ground was hard with about 0.5 inch of loose sand on top. Of the total of 

21 UGS dropped, 18 landed on their sides. The significance of this, if any, is not clear. The 

drop area for the autonomous drop was rough and uneven. Table 2 tabulates all the data taken 

and calculated, including drop coordinates, landing coordinates, and calculation of the 

dispersions. 

UGS that landed within 3 to 5 ft of each other were treated as the same point, taking into 

consideration of GPS accuracy. We calculated the dispersion by determining the distance that a 

node was from the centriod of the landing positions. The maximum dispersion distance was 

7.2 m, with 2 to 3 m more typical. Contributing to the dispersions is the fact that the UGS were 

lying in the floor of a big bin, which is about 3 ft by 3 ft, and were sliding around during flight. 

When the floor drops open, the UGS fall from different spots within the bin and leave at slightly 

different times. With a dispenser designed for UGS, this would not happen. Figure 6 shows a 

typical landing dispersion. 
10

Table 2. YPG UGS drop data. 

 

Bin 

No. 

UGS 

No. 

Height 

(meters) 

North 

Delta 

Landing 

(degrees) 

East Delta 

Release 

(degrees) 

North 

Delta 

Landing 

(meters) 

East 

Delta 

Release 

(meters) 

Offset 

(meters) 

Drop 

Dispersion 

Distance 

from c.g. 

(meters) 

 

Flight 1 - Manual Drop 

Drop 1 2 1 107 0.000294 -0.000775 32.72 -72.32 79.38 2.69 

Drop 1 2 2 107 0.000322 -0.000803 35.81 -74.91 83.03 1.34 

Drop 1 2 11 107 0.000322 -0.000803 35.81 -74.91 83.03 1.34 

 

Drop 2 3 3 93 0.000155 -0.000224 17.21 -20.91 27.08 0 

Drop 2 3 7 93 0.000155 -0.000224 17.21 -20.91 27.08 0 

Drop 2 3 12 93 0.000155 -0.000224 17.21 -20.91 27.08 0 

Drop 3 4 4 170 -0.000604 -0.000666 -67.13 -62.09 91.45 3.02 

Drop 3 4 8 170 -0.000631 -0.000721 -70.22 -67.27 97.25 3.02 

Drop 4 5 5 81 -0.000624 -0.000977 -69.34 -91.19 114.56 3.02 

Drop 4 5 9 81 -0.000651 -0.001033 -72.43 -96.37 120.56 3.02 

Flight 2 - Manual Drop 

Drop 1 2 1 98 -0.000091 -0.000944 -10.16 -88.06 88.64 3.09 

Drop 1 2 2 98 -0.000036 -0.000944 -3.98 -88.06 88.15 3.09 

Drop 1 2 11 98 -0.000064 -0.000944 -7.07 -88.06 88.34 0 

 

Drop 2 3 3 89 -0.000923 -0.000052 -102.65 -4.85 102.76 2.69 

Drop 2 3 7 89 -0.000979 0.000031 -108.82 2.92 108.86 7.32 

Drop 2 3 12 89 -0.000923 -0.000080 -102.65 -7.44 102.91 4.78 

Drop 3 4 4 86 -0.000347 -0.000636 -38.59 -59.32 70.77 1.54 

Drop 3 4 8 86 -0.000375 -0.000636 -41.68 -59.32 72.50 1.54 

Flight 3 - Autonomous Drop 

Drop 1 2 1 247 n/a n/a -94.00 -27.00 97.8 0 

Drop 1 2 2 247 n/a n/a -94.00 -27.00 97.8 0 

Drop 1 2 11 247 n/a n/a -94.00 -27.00 97.8 0 

Note: Above ground levels for flights number 2 & 3 were estimated with a nominal ground elevation of 250 m ~ 820 ft 

derived from flight #1.
11

Figure 6. Typical drop dispersion. 

Two-dimensional offsets (north and east) of the landing points from the drop point varied from 

27 to 120 m. The post-drop wind factor is negligible on the UGS mass mock-ups. The offset is 

a result of the initial forward velocity imparted on the nodes by the velocity of the parafoil. The 

greater the drop altitude, the larger the expected offset because of the forward speed of the 

parafoil. However, the ground speed is directly increased or decreased by the headwinds or 

tailwinds. Looking at the data in table 2 and using the offset and height of drop, one can derive 

the head wind or tail wind. It appears that the winds at the drop altitudes were running between 

0 and 20 mph. 

The autonomous drop was most interesting since it is more representative of the operational 

manner in which UGS would be employed. Three UGS were dropped from one bin on the 

autonomous flight. The parafoil was programmed with the coordinates of the ground “target” 

spot and flew to a release point that would allow the measured winds to carry the presumed 

parachuted payload to the target spot as is the case with the SOCOM scenarios programmed. 

Therefore, the UGS were going to predictably land up wind from the desired landing spot. 

Figure 7 shows the relative two-dimensional release, target, and actual landing spots. 
12

Scale: 25 m x 25 m Grids 

Target cone 

 

 

Wind direction 

 

 

 

 

 

 Release pt. Flight direction 

 

 Landing pt

0 m 25 m 50 m 75 m 100 m 125 m 

East 

Figure 7. Autonomous flight relative coordinates. 

As figure 7 indicates, the parafoil flew upwind past the target and then properly released the 

UGS payload upwind from the target in the expectation the wind would carry the payload back 

to the ground target spot. Post-flight calculations using the wind and altitude data from the 

parafoil indicate that the drop was in the correct spot. 
13

5. Summary and Conclusions 

The basic conclusion of these tests is that the powered parafoil appears to be a viable UAV to be 

used for employment of ISR UGS. They are commercially available, they can travel long 

ranges, and they can carry a heavy payload. Designing an appropriate UGS dispenser would be 

much simpler and less expensive than the dispensers needed for HIMARS or the FCS NLOS 

cannon. Drops can be programmed autonomously to dispense UGS one node at time to populate 

a field, along a road, or almost any other desired coverage. The powered parafoil can fly 

multiple passes back and forth, working its way across the field with timed drops along a given 

pass. High altitude drops that create a spray pattern could also be programmed. Dispersions of 

dropped UGS are reasonably small, and control of the emplacements appears good. 

Future drops should be planned with modified software to implement UGS deployment 

scenarios. 
14

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