Flight Demonstration Results of a Two-way Robust 

Acquisition of Data (2-RAD) System 

by Marshal A. Childers 

ARL-TR-3103 January 2004 

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Army Research Laboratory 

Aberdeen Proving Ground, MD 21005-5069 

ARL-TR-3103 January 2004 

Flight Demonstration Results of a Two-way Robust 

Acquisition of Data (2-RAD) System 

Marshal A. Childers 

Weapons and Materials Research Directorate, ARL 

Approved for public release; distribution is unlimited.
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 Flight Demonstration Results of a Two-way Robust Acquisition of Data (2-RAD) 

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14. ABSTRACT 

This report describes a joint effort between the U.S. Army Research Laboratory (ARL), the John Hopkins Applied Physics 

Laboratory (APL), and Yuma Proving Ground (YPG), which was funded by the Central Test and Evaluation Investment 

Program to extend the wireless local area network approach to munition testing. The objective of this two-way robust 

acquisition of data (2-RAD) system program was to design, produce, and demonstrate in flight an instrumented 2.75-inch 

diameter rocket warhead system that integrates commercial off-the-shelf network hardware to demonstrate the feasibility 

of wireless two-way communication on board a munition. Five instrumented warheads were produced, and two of these 

were flight demonstrated at Rocket Alley, YPG. The results of this experiment mark the first successful wireless two-way 

network communication on a munition.

15. SUBJECT TERMS

 HYDRA-70; IEEE 802.11b; network; rocket; two-way communication; 2-RAD 

16. SECURITY CLASSIFICATION OF: 

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 Marshal A. Childers 

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iii 

Contents 

List of Figures iv

List of Tables iv

Acknowledgments v

1. Introduction 1

2. 2-RAD Telemetry System 1

2.1 Components Description .................................................................................................2 

3. Mechanical Design and Structural Analysis 3

3.1 Power Budget ..................................................................................................................3 

3.2 Mechanical Packaging.....................................................................................................4 

4. Flight Demonstration Description and Results 10

5. Conclusion 12

6. References 13

Appendix A. Electrical Wiring Diagram 14

Appendix B. Mechanical Drawing 17

Appendix C. Projectile Trajectory Prediction Graph 37

Distribution List 39 
iv 

List of Figures 

Figure 1. Housing assembly model.................................................................................................5 

Figure 2. Fully assembled warhead attached to an inert MK66 rocket motor...............................5 

Figure 3. System components assembly. ........................................................................................7

Figure 4. Computer assembly. ........................................................................................................7 

Figure 5. Slot in warhead for camera..............................................................................................8 

Figure 6. Camera mount. ................................................................................................................8 

Figure 7. Fully assembled 2-RAD warhead mounted on shock test system. .................................9 

Figure 8. 2-RAD projectile in pre-flight evaluation configuration at Rocket Alley.....................11 

Figure 9. Launch of the 2-RAD projectile....................................................................................12

List of Tables 

Table 1. Manufacturer power specifications for 2-RAD prototype system components. ..............3 

Table 2. Mass and inertial properties of 2-RAD instrumented warhead CAD model..................10 
v 

Acknowledgments 

The author thanks Robert Bamberger, Cash Costello, George Barrett, and Dr. William D’Amico 

of the Johns Hopkins University Applied Physics Laboratory, and Mark Lauss of Yuma Proving 

Ground (YPG), Arizona, for their contributions in component selection, software programming, 

and support of the flight demonstration. Charles Ramsdell of YPG contributed to the success of 

this effort by his support during the flight demonstration. Gordon Brown of the U.S. Army 

Research Laboratory (ARL) is thanked for his expertise and support during the planning, 

“ruggedization,” assembly, and flight demonstration phases of this project. Mike Nair of ARL is 

greatly appreciated for his work in troubleshooting the system, supporting the assembly and 

flight demonstration of the rocket prototypes, and his careful technical review of this report. The 

efforts of Jaime King and John McLaughlin of Dynamic Sciences, Inc. (DSI) were essential to 

the success of the system component integration. Robert Wert of the Oak Ridge Institute for 

Science and Education went beyond the call of duty to apply his radio frequency expertise in 

support of the system troubleshooting. The author thanks Fred Brandon of DSI for providing the 

projectile trajectory simulation results. Melvin Ridgely of ARL provided logistic support during 

the assembly and shipping of the projectiles. The consultation of Ed Bukowski of DSI about 

battery power and recharging is greatly appreciated. John Condon of ARL is thanked for his 

consultation on the mechanical design of the 2-RAD warhead. 
vi 

INTENTIONALLY LEFT BLANK. 
1 

1. Introduction 

Two-way robust acquisition of data (2-RAD) is an attempt to establish a two-way wireless 

communication system on a munition. Future combat systems will apply a networked structure 

for platforms and munitions (nodes) so that multiple assets will simultaneously communicate 

among each other. Traditional telemetry requires a portion of the radio frequency (RF) spectrum 

to be reserved for long periods of time. In an operational scenario with numerous assets, there is 

not sufficient spectrum to support telemetry that requires multiple extended reservations of RF 

spectrum. To solve this problem, the concept of using an Institute of Electrical and Electronics 

Engineers (IEEE) 802.11b wireless local area network (WLAN) is posed so that all nodes in the 

infrastructure can send, receive, and relay data by making relatively short reservations. The 

WLAN approach is also beneficial in that the use of wireless repeater stations (ground nodes) 

and access points (connected to wired networks) can extend the range of wireless communication 

for munitions. 

This report describes a joint effort between the U.S. Army Research Laboratory (ARL), the John 

Hopkins Applied Physics Laboratory (APL), and Yuma Proving Ground (YPG), which was 

funded by the Central Test and Evaluation Investment Program to extend the WLAN approach to 

munition testing. The objective of this work was to design, produce, and test in flight an 

inexpensive instrumented 2.75-inch diameter rocket warhead to assess the feasibility of two-way 

wireless network communications on board a munition. APL was responsible for selecting and 

functionally evaluating the warhead system components, supporting the flight experiment, and 

reducing the data. ARL was responsible for designing and manufacturing the warhead 

mechanical hardware, integrating the system components, “ruggedizing” the munition, 

assembling the prototype, supporting the pre-flight system troubleshooting, and assisting during 

the flight experiment. YPG was responsible for supporting the flight experiment. 

2. 2-RAD Telemetry System 

The 2-RAD telemetry system applies wireless communication technology that is available from 

commercial off-the-shelf (COTS) products. This technology is based on the IEEE 802.11b 

standard in which a wireless radio generates a 2.4-gigahertz (GHz) carrier wave (2.4 to 

2.483 GHz) that is modulated to achieve a data transfer rate of 1, 2, 5.5, or 11 megabits per 

second (Mbps). The system of wireless transceivers can be operated in an independent 

configuration or in an infrastructure configuration. In the independent configuration, known as 

the ad hoc configuration, the system nodes communicate directly to each other, and no fixed 

transceivers are required. In the infrastructure configuration, the nodes communicate to fixed 
2 

access points (APs) that typically distribute data through a wired connection. For more 

information about IEEE 802.11b, consult the standard (1). 

Component selection for the 2-RAD system was driven by the vehicle geometry (2.75-inch 

diameter rocket), the desired data medium (video), and the need to use COTS components. The 

usable payload space of the rocket warhead and the interface requirements for an IEEE 802.11b 

wireless radio card, a computer, and a universal serial bus (USB)-compatible camera limited the 

number of acceptable components for selection. The mechanical packaging of the selected 

components is detailed in the next section of this report. The rocket payload consists of a single 

board computer, an IEEE 802.11b wireless card, a 0.5-watt amplifier, a USB-compatible camera, 

and a 2.4-GHz antenna. Except for the antenna and two voltage converters, all the 2-RAD 

system components were COTS products. 

2.1 Components Description 

The selected camera used to obtain data for verification of two-way communication is a Logitech 

QuickCam1

 for Notebooks Pro with a maximum 640x480 resolution and maximum frame rate of 

30 frames per second. A USB port is used to send data, provide power, and control the zoom 

feature. 

The IEEE 802.11b wireless radio is a Linksys2

 instant wireless network access point (WAP11) 

card that has two connectors for external antennas. This card can be configured as an access 

point or as a client (node), supports 11 Mbps data transfer, has 63 milliwatts (mW) transmit 

power, and -84 decibels referred to 1 milliwatt (dBm) receiver sensitivity. 

The single board computer is a CompuLab 586CORE3 with a 133-MHz AMD Elan4 SC520 X-86 

compatible processor, 64-megabyte (MB) flash memory, a 100/10BaseT ethernet port, and a 

USB host port. The operating system for the computer is Red Hat Linux 7.05. To connect the 

single board computer to the camera and the wireless radio card, APL designed and produced 

two mezzanine boards. These printed circuit boards physically connect to the 90-pin connectors 

on the single board computer and provide power connections to the computer and camera, enable 

USB communications with the camera, and enable ethernet communications to the Linksys 

WAP11 card. 

The selected amplifier is a Teletronics6

 SmartAmp 2.4-GHz series 500-mW amplifier. This 

device has an operating range of 2.4 to 2.5 GHz, 200 mW of maximum transmit input power, as 

much as 24 dB transmit gain, and 14 dB typical receive gain. 

 1

Logitech and QuickCam are registered trademarks of Logitech, Inc., 6505 Kaiser Drive, Freemont CA 94555. 2

Linksys is a registered trademark of Linksys, 17401 Armstrong Ave., Irvine CA 92614. 

3CompuLab and 586CORE are trademarks of CompuLab Ltd., Malat Bldg., Technion, Haifa Israel. 

4

 Elan is a trademark of Advanced Micro Devices, One AMD Place, Sunnyvale CA 94088. 5

Red Hat, 1801 Varsity Drive, Raleigh NC 27606. 

6

Teletronics is a registered trademark of Teletronics International, Inc., 1803 Research Blvd. Suite 204, Rockville MD 20850. 
3 

The antenna is a 2.4-GHz, 4.9-dBi (decibels referenced to an isotropic radiator) gain, circular 

patch antenna that was provided by the Naval Air Warfare Center Weapons Division. 

3. Mechanical Design and Structural Analysis 

3.1 Power Budget 

The prototype system was designed for flight experimentation on a 2.75-inch rocket with a flight 

time of approximately 25 seconds. Considering the additional time required for pre-flight turnon and function checks, the power system was designed to produce 30 minutes of continuous 

operation. The power specifications for each system component are listed in table 1. 

Table 1. Manufacturer power specifications for 2-RAD prototype system components. 

Device Power 

(W) 

Voltage 

(V) 

Maximum 

Current (mA) 

Compulab 586CORE Single Board 

Computer 

4.3 3.3 1303 

Linksys WAP11 Access Point Card 12.5 5 2500 

Teletronics 500 mW SmartAmp 4.9 7.5 653 

Logitech Quickcam Camera 0.5 5 100 

Lithium ion batteries with a nominal voltage of 3.7 volts and 640 milliampere (mA) hours 

standard capacity, which are typically used as replacements for Canon7 digital camera batteries, 

were selected to provide power to the system. These batteries have previously shown good 

discharge characteristics and can endure the launch and flight of a 2.75-inch rocket (2). Table 1 

shows that the system requires three different voltages. The manufacturer specifications for the 

Linksys WAP11 card indicate a 2.5-ampere current requirement, but bench testing at APL 

revealed that the card intermittently draws approximately 2 amperes. Power regulation to the 

Linksys WAP11 card was accomplished with a DC-to-DC voltage-converting printed circuit 

board (PCB) designed by ARL, which supplied 5 volts at a maximum of 3 amperes. The 

3.3 volts supplied to the computer were regulated by a LMS1585AIT-3.3-volt National 

Semiconductor8 low dropout fast response regulator. The 5 volts to the camera were achieved by 

a single DC-to-DC voltage-converting PCB that was designed by ARL and similar to the one 

used in a previous ARL flight demonstration (2) to provide 5 volts to a mezzanine card that 

forwards power to the camera by the USB cable. Power to the three regulator boards was 

supplied by six batteries in a 2-series, 3-parallel configuration to provide a nominal 7.4 volts 

with approximately 1,900 mA hours capacity. According to the manufacturer of the amplifier, 

 7

Canon U.S.A., Inc., One Canon Plaza, Lake Success NY 11042. 

8

National Semiconductor Corporation, 2900 Semiconductor Dr., Santa Clara, CA 95052-8090. 
4 

this device is self-regulating, the nominal 7.5 volts are the minimum required voltage, and a 

supply of 9 to 12 volts is recommended. Therefore, two batteries in series were used to supply 

an unregulated nominal 11.1 volts at approximately 640 mA hours to the amplifier. Battery 

power was introduced to the system components through a manual turn-on switch. An electrical 

wiring diagram of the 2-RAD system is shown in appendix A of this report. 

3.2 Mechanical Packaging 

ARL was tasked to design a warhead to house the 2-RAD prototype system components. The 

design intent was to 1) incorporate required COTS components into a 2.75-inch diameter 

HYDRA9

-70 rocket warhead that is compatible with the M261 lightweight launcher, 2) provide a 

modular or accessible payload, 3) place the antenna forward of the rocket launcher, 4) provide 

for warhead attachment to a standard MK66 rocket motor, and 5) ensure component and system 

integrity during expected operational conditions. Five warhead assemblies were manufactured. 

To provide access to system components for the purpose of pre-flight troubleshooting, the 

warhead assembly consisted of a mounting plate that inserted into a housing tube. The hardware 

for the 2-RAD system was modeled with SolidWorks10 computer-aided design (CAD) software 

to facilitate the design layout and provide mass and inertial properties approximations. Figure 1 

is a CAD–generated diagram of the housing and component assembly. Mechanical drawings of 

the warhead hardware are shown in appendix B of this report. 

The warhead housing was designed to accommodate the selected COTS components for the 

2-RAD system. The housing was machined from 6061-T6 aluminum stock of 3.5-inch outside 

diameter and 1.5-inch inside diameter. Given that the width of the Linksys WAP11 card 

exceeded 2.8 inches, the warhead section that housed this component required a 2.9-inch inside 

diameter. In order for the warhead to fit into the rocket launcher, the Linksys WAP11 card was 

situated in the front of the warhead so that the front section of the warhead protruded from the 

launcher when the rocket assembly was placed in launch position. The outside diameter of the 

front section was 3.25 inches (see figure 1). The middle section was designed with a 2.5-inch 

inside diameter and 2.75-inch outside diameter. The rear section of the housing tube was 

machined to a 2.75-inch outside diameter, and the stock 1.5-inch inside diameter of this section 

was unchanged. The warhead total length was 39.75 inches. Figure 2 shows a fully assembled 

warhead attached to an inert MK66 rocket motor. Stress approximations were made for the front 

section wall and middle section wall, assuming a 100-g acceleration on a warhead weighing 

12.2 pounds. The calculated compressive stresses predicted that the walls could survive the 

expected launch event. To provide for attaching the warhead to the rocket motor, Acme threads 

(for thread details, see drawing in appendix B) were machined at the rear-most portion of the 

housing tube. 

 9

Not an acronym 

10SolidWorks Corporation, 300 Baker Avenue, Concord MA 01742. 
5 

Figure 1. Housing assembly model. 

Figure 2. Fully assembled warhead attached 

to an inert MK66 rocket motor. 

The mounting plate was machined from 7075-T6 aluminum plate stock to 0.22 inch thickness. 

The plate was supported in the housing tube by bulkheads at each end and by set screws. 

Photographs of an assembled mounting plate with the system components attached are shown in 

figure 3. The front bulkhead served a dual purpose as an antenna mount. The antenna was 
6 

mounted to the bulkhead with 1-72 unified coarse thread series (UNC) screws. A semi-rigid 

coaxial cable was used to connect the antenna to the amplifier. Machined 7075-T6 aluminum 

“standoffs” and 4-40 UNC screws were used to attach the amplifier to the mounting plate (for 

stand-off drawings, see appendix B). The Linksys WAP11 card was mounted to the plate by 

4-40 mounting screws and Nylon standoffs. A flexible coaxial cable connected the amplifier to 

the Linksys WAP11 card. An ethernet crossover cable was used to connect the Linksys WAP11 

card to the single board computer with wires on one end that were soldered to the card and an 

RJ45 connector on the other end that was soldered to the mating connector of a mezzanine board. 

The two mezzanine boards and the single board computer were mounted to the plate with a 

frame machined from 0.23-inch-thick polycarbonate sheet stock. A photograph of the computer 

assembly is shown in figure 4. The following assembly steps were applied to ensure alignment 

of the 51-pin connectors on the mezzanine boards with those on the single board computer. 

First, the mezzanine boards were loosely fastened to the polycarbonate frame by 4-40 UNC 

screws and nuts. Next, the connectors on the single board computer were pressed onto the 

mezzanine board connectors and the screws were tightened. Finally, a 2.5-inch by 4-inch section 

of 0.060-inch-thick elastic material was cut from stock E•A•R11 Specialty Composites C-1002-

06PSA and placed under the computer board, and the assembly was fastened to the mounting 

plate by 4-40 UNC screws. 

Two packaging requirements drove the mounting design for the camera. First, the camera field 

of view must be maximized. Second, to maintain a modular approach, the mounted camera must 

permit removal of the system components after assembly. Both requirements were met by 

placement of the lens in the warhead wall and placement of the camera in a side-look orientation. 

The camera lens was placed within 0.020 inch of the outer surface of the warhead wall by a slot 

machined in the warhead front section (see figure 5). This slot permitted removal of the 

mounting plate with the camera attached. A 7075-T6 aluminum block was used to mount the 

camera to the plate. Mounting screws (0-80 UNF) and a combination of aluminum and Nylon 

spacers held the camera to the block, and 4-40 UNC screws were used to attach the block to the 

mounting plate (figure 6). 

The two battery configurations were each packaged in cases that were machined from 7075-T6 

aluminum. Each battery case had 0.100-inch wall thickness and was secured to the mounting 

plate by 4-40 UNC screws. To secure the batteries within the battery cases and provide electrical 

insulation, a thin layer of Mylar12 material was formed around the battery packs before they were 

inserted into the cases. 

 11energy-absorbing resins; E-A-R



is a registered trademark of Specialty Composites, 7911 Zionsville Road, Indianapolis, IN 46268. 12Mylar® is a registered trademark of E. I. DuPont de Nemours & Co., Inc. 
7 

a. camera side 

b. wireless card side 

Figure 3. System components assembly. 

Figure 4. Computer assembly. 
8 

Figure 5. Slot in warhead for camera. 

Figure 6. Camera mount. 

To assess the rocket launch survivability of the system, selected components and full 2-RAD 

warhead assemblies were tested with an MTS13 shock test system. The shock test system was 

used to apply a simulated launch maximum acceleration of 100 g to the camera and computer 

and 85 g to the assemblies. Each test item was secured to the shock table with mounts that were 

machined from 7075-T6 aluminum. Figure 7 shows the fully assembled 2-RAD warhead 

mounted on the shock test system. Further detail about using this shock test system to assess 

munition component survivability is given in a previous report (3). As a result of the shock 

testing of the camera and computer, no degradation of performance or structural integrity was 

detected in these components. Shock survivability testing was also performed on two fully 

 13Not an acronym; MTS Systems Corporation, 14000 Technology Dr., Eden Prairie, MN 55344-2290. 
9 

assembled warheads. The first tested unit was evaluated for structural integrity only. This 

warhead was exposed to a shock with a maximum acceleration of 85 g. Visual inspection of 

each component, all mounting hardware, and the warhead structure revealed that no structural 

degradation occurred from the shock. A second warhead assembly was shock tested twice at a 

maximum acceleration of 85 g. During the first shock event, the unit was tested with battery 

power supplied and the Linksys WAP11 card configured as a client. System power was 

monitored with a Cisco14 Aironet 350 personal computer memory card international (PCMCIA) 

client adapter connected to a 2.2-dBi omnidirectional antenna to verify that the Linksys WAP11 

card on the 2-RAD system remained active. No two-way data link was attempted for this shock 

experiment. The power remained on during and after the shock event. The same unit was tested 

a second time with the Linksys card configured as a client and the system powered by the 

batteries. A link was established with a nearby Linksys WAP11 card that was configured as an 

AP and connected to a 2.2-dBi diversity omnidirectional antenna system. The two-way 

communication link was maintained during and after the second shock event, and no structural 

degradation was visually detected in the components, mounting hardware, or warhead structure. 

Figure 7. Fully assembled 2-RAD warhead mounted on 

shock test system. 

 14Cisco Systems, Inc., 170 West Tasman Dr., San Jose CA 95134. 
10 

Flight trajectory prediction for the instrumented warhead was made with interior ballistic and 

trajectory simulation software to quantify the flight stability of the projectile (4). Aeroballistic 

properties of this custom warhead were not matched to any fielded tactical or training warhead. 

The mass and inertial properties used as input to the trajectory code are listed in table 2. The 

center of mass dimensions listed in the table are referenced from the interface of the warhead and 

the rocket motor. 

Results of the flight trajectory prediction are given in appendix C of this report. 

Table 2. Mass and inertial properties of 2-RAD instrumented warhead CAD model. 

Mass 

(pounds) 

Principal 

moment of 

inertia-x 

(poundsinch2

) 

Principal 

moment of 

inertia-y 

(poundsinch2

) 

Principal 

moment of 

inertia-z 

(poundsinch2

) 

Center of 

mass-x 

(inches) 

Center of 

mass-y 

(inches) 

Center of 

mass-z 

(inches) 

12.128 15.230 1294.009 1294.439 14.42393621 0.00001781 0.02580386 

4. Flight Demonstration Description and Results 

The flight experiments were held at the Rocket Alley test area of YPG in which two rockets were 

fired on September 18, 2003. 

The transceivers used to send and receive data with the rocket consisted of Linksys WAP11 cards 

that were configured as clients. This configuration was chosen because pre-flight link attempts 

revealed that the system established a more consistent link when the rocket was configured as an 

AP and the transceivers were configured as clients. Four of the transceivers were placed at various 

sites on Rocket Alley: Site 1 was 75 feet to the left of the rocket launcher and used a diversity 

2.2-dBi omnidirectional antenna system; Site 2 was approximately 900 feet down range (along the 

flight path) from the launcher and used an 11-dBi gain omnidirectional antenna on a 10-foot mast; 

Site 3 was approximately 1,900 feet down range (along the flight path) and used an 11-dBi 

omnidirectional antenna on a 10-foot mast; Site 5 was approximately 6 km down range and 1 km 

to the right of the flight path and used a 23-dBi parabolic antenna on a 50-foot mast. The primary 

data to be transferred over the link between that rocket and the transceivers were camera control 

messages (ground to munition communication) and digitized camera video (munition to ground 

communication). Link and timing information was monitored at three sites by laptop computers 

that were each equipped with a Cisco Aironet 350 PC client card and WildPackets Airopeek15

WLAN analyzer software. These monitoring stations were situated at Site 1 with an 11-dBi 

omnidirectional antenna on a 20-foot mast, at Site 4 (approximately 3 km down range 

 15Airopeek is a trademark of WildPackets, Inc., 1340 Treat Blvd, Suite 500, Walnut Creek CA, 94597. 
11 

and 1 km to the right of the flight path) with an 11-dBi omnidirectional antenna on a 5-foot mast, 

and at Site 5 with an 11-dBi omnidirectional antenna on a 50-foot mast. 

The instrumented warheads were attached to MK66 Mod 2 rocket motors and launched from a 

19-tube M261 lightweight launcher with a quadrant elevation equal to 434 mils (24.4 degrees). 

Figure 8 shows the launch site at Rocket Alley with the rocket in a pre-flight evaluation 

configuration, and figure 9 is a still photograph of one of the rockets taken during launch. The 

total flight distances of the rockets were approximately 7.5 km. Before each rocket was 

launched, a two-way data link was established between the rocket AP and the clients at Sites 1 

and 3, but when the warheads were attached to the rocket motors and inserted into the launcher, 

the link with Site 3 failed. During flight, neither of the rockets achieved a link with Sites 2, 3, or 

5. Video data obtained from a two-way link between Site 1 and the second rocket contained 3 

seconds of post-launch data with 0.5 second of discernible video. Link and timing monitoring 

data were obtained by the Cisco Aironet 350 PCMCIA client adapter at Sites 1 and 5 for each 

rocket. At the time of this writing, the video data from the first rocket had not been postprocessed. 

Figure 8. 2-RAD projectile in pre-flight evaluation configuration at Rocket Alley. 
12 

Figure 9. Launch of the 2-RAD projectile. 

5. Conclusion 

In an effort to assess the feasibility of two-way network-based communications on a munition, 

APL, ARL, and YPG produced a prototype 2.75-inch diameter rocket system that applied IEEE 

802.11b standard COTS wireless hardware. The work presented in this report represents the first 

attempt to employ such industrial communication technology on a munition. 

The results of this experiment reflect two major accomplishments. First, in light of the technical 

challenges of integrating the COTS hardware into the munition and establishing a two-way 

communication link, the video data obtained from the rocket firings mark the first successful 

wireless two-way communication on a munition. Second, the experiment results help to identify 

the need to apply technology that can provide a robust two-way link for an extended period 

between munitions and transceivers. When this ability is realized, it will open the door to 

simultaneous multiple munition communication experimentation that can approach those needs 

of future combat systems. 
13 

6. References 

1. LAN/MAN Standards Committee of the IEEE Computer Society. Part 11: Wireless LAN 

Medium Access Control (MAC) and Physical Layer (PHY) Specifications: Higher Speed 

Physical Layer Extension in the 2.4 GHz Band; IOC/IEC 8802.11: 1999(E), Piscataway, NJ, 

16 September 1999. 

2. Davis, B. S.; Condon, J. A.; Brown, T. G. Flight Demonstration Results of an Inertial 

Measurement Unit and Global Positioning System Translator Telemetry System; 

ARL-TR-2630; U.S. Army Research Laboratory: Aberdeen Proving Ground, MD, 

November 2001. 

3. Childers, M.A. Evaluation of the IMPAC66 Shock Test Machine, Serial Number 118; 

ARL-TR-2840; U.S. Army Research Laboratory: Aberdeen Proving Ground, MD, 

October 2002. 

4. Brandon, F. 2-RAD launch event (PRODAS V3.1.25, Arrow Tech Assoc. and PRODAS 

Partners, copyright 1999-2003), U.S. Army Research Laboratory: Aberdeen Proving 

Ground, MD, unpublished data. 
14 

INTENTIONALLY LEFT BLANK
15 

Appendix A. Electrical Wiring Diagram 
16 

INTENTIONALLY LEFT BLANK
17 

Appendix B. Mechanical Drawing 
18 
19 
20 
21 
22 
23 
24 
25 
26 
27 
28 
29 
30 
31 
32 
33 
34 
35 
36 
37 

Appendix C. Projectile Trajectory Prediction Graph 
38 

INTENTIONALLY LEFT BLANK. 
39 

NO. OF 

COPIES ORGANIZATION

 * ADMINISTRATOR 

 DEFENSE TECHNICAL INFO CTR 

 ATTN DTIC OCA 

 8725 JOHN J KINGMAN RD STE 0944 

 FT BELVOIR VA 22060-6218 

 *pdf file only 

 1 DIRECTOR 

 US ARMY RSCH LABORATORY 

 ATTN AMSRD ARL CI IS R REC MGMT 

 2800 POWDER MILL RD 

 ADELPHI MD 20783-1197 

 1 DIRECTOR 

 US ARMY RSCH LABORATORY 

 ATTN AMSRD ARL CI OK TECH LIB 

 2800 POWDER MILL RD 

 ADELPHI MD 20783-1197 

 1 DIRECTOR 

 US ARMY RSCH LABORATORY 

 ATTN AMSRD ARL D D SMITH 

 2800 POWDER MILL RD 

 ADELPHI MD 20783-1197 

 4 DIRECTOR 

 US ARMY RSCH LABORATORY 

 ATTN AMSRD ARL SE RL M DUBEY 

 B PIEKARSKI 

 AMSRD ARL SE RM H WALLACE 

 AMSRD ARL SE SS LADAS 

 2800 POWDER MILL RD 

 ADELPHI MD 20783-1197 

 1 CDR US ARMY TACOM ARDEC 

 ATTN AMSTA AR FSP M HOLLIS 

 PICATINNY ARSENAL NJ 07806-5000 

 1 CDR NAVAL SURF WARFARE CTR 

 ATTN G33 D HAGEN 

 17320 DAHLGREN ROAD 

 DAHLGREN VA 22448-5100 

 3 PROGRAM MGR ITTS 

 STRICOM 

 ATTN AMFTI EL D SCHNEIDER 

 12350 RESEARCH PKWY 

 ORLANDO FL 32826-3276 

 1 US ARMY CECOM RDEC 

 ATTN AMSEL RD NV AS UEA 

 G KLAUBER 

 10221 BURBECK ROAD 

 FORT BELVOIR VA 22060-5806 

NO. OF 

COPIES ORGANIZATION

 4 APPLIED PHYSICS LABORATORY 

 ATTN W D’AMICO 

 11100 JOHNS HOPKINS ROAD 

 LAUREL MD 20723-6099 

 ABERDEEN PROVING GROUND

 2 DIRECTOR 

 US ARMY RSCH LABORATORY 

 ATTN AMSRD ARL CI OK (TECH LIB) 

 BLDG 305 APG AA 

 1 CDR USA AMSAA 

 ATTN AMXSY EF S MCKEY 

 BLDG 392 

 1 US ARMY EVALUATION CMD 

 ATTN USA CSTE EAC AZ R MIRABELLE 

 BLDG 4120 

 2 CDR US ARMAMENT RD&E CTR 

 ATTN AMSTA AR FST T J MATTS 

 J WHITESIDE 

 BLDG 120 

 1 CDR USA DTC 

 ATTN CSTE DTC TTM J SCHNELL 

 RYAN BLDG 

 3 DIR USARL 

 ATTN AMSRD ARL WM J SMITH 

 A HORST 

 AMSRD ARL WM SG T ROSENBERGER 

 BLDG 4600 

 2 DIR USARL 

 ATTN AMSRD ARL WM B D LYON 

 W CIEPIELLA 

 BLDG 4600 

 20 DIR USARL 

 ATTN AMSRD ARL WM BA T BROWN (2 CYS) 

 F BRANDON T BROSSEAU 

 B DAVIS T HARKINS 

 D HEPNER G KATULKA 

 R MCGEE P MULLER 

 P PEREGINO A THOMPSON 

 M WILSON M CHILDERS (4 CYS) 

 K HUBBARD 

 BLDG 4600 
40 

NO. OF 

COPIES ORGANIZATION

 5 DIR USARL 

 ATTN AMSRD ARL WM BC P PLOSTINS 

 M BUNDY J GARNER 

 B GUIDOS J NEWILL 

 P PLOSTINS 

 BLDG 390 

 3 DIR USARL 

 ATTN AMSRD ARL WM BF 

 D WILKERSON H EDGE T HAUG 

 BLDG 390 

 2 DIR USARL 

 ATTN AMSRD ARL WM RP J BORNSTEIN 

 C SHOEMAKER 

 BLDG 1121