INSECTITHOPTER

• Document Type: FOIA
• Collection: FOIA Collection
• Document Number (FOIA) /ESDN (CREST): 06094694
• Release Decision: RIPPUB
• Original Classification: U
• Document Page Count: 8
• Document Creation Date: March 8, 2023
• Document Release Date: December 16, 2019
• Case Number: F-2013-02278
• Publication Date: September 1, 1972

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Insectithopter
RN NO
Advanced TealliffOgy Center.
$105c:Y76
MONTH TO LET
September 1972
UB-CATEGORY/ELEMENT .
]ollection Systems/Emplacement Systems
PROJECT
'3
Long Range/Concept Analysis
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DESCRIPTION: This is a follow-on program to demonstrate control and communi-
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cation feasibility of the insectithopter. Under this program, free-
flight tests and payload/endurance capabilities will be conducted, and
communication navigatiOm� and propulsion technologies developed.
'
BACKGROUND: The insectithopter has been tested in free-flight and wind
tunnel tests. Concepts for using the "ROME" laser system for command
control and data link look promising but no specific experiments
'have been conducted. It is proposed that this system be interfaced
with the vehicle and flight tested to at least 300 feet to establish
total system feasibility. The "ROME" laser system uses a very small
retro-modulator as one mirror of a long laser cavity.
COORDINATION:
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TYPE OF WORK: Advanced Development
FIELD OF WORK: Electronics � r -
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PROP. SOLICITED PROP. IN H
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ISSUE DATE
9/7/72
PAN NO.
DIVI
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Reier Charles N. Adkins
TITLE
ORN NO. CONTRACTOR
COST
$105,376(
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Insectithopter /(-13
Advanced
Tech.Cen.
(b)(3)
(b)(3)
(b)(3)
b)(3)
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4 April 1974
PROJECT HISTORY
Title: Insectithopter
Contractor: Advanced Technology Center
Amount: $105,376
ORN :
1. Intelligence Objective: To provide a clandestine insect-
like (dragonfly) vehicle capable of being directed to a
specific target at least 100 meters distant for the pur-
pose of emplacing an audio surveillance device (optical
microphone). At the outset of this program, both the
aerodynamic and propulsive feasibility had been demon-
strated by flight tests during a phase zero effort of
$40,000. In addition, the proposed method of providing
tracking and guidance (the "ROME Laser" system) was a
proven operational concept. On the other hand, the
optical microphone had been demonstrated only in bread-
board form and further development would be required to
meet size and weight requirements.
2. Original Project Goal: Demonstrate system feasibility
by:
a. Building a ROME laser system to track the
.vehicle and provide at least one channel of control
signals to the vehicle.
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b. Designing and implementing at least a one-axis
control system (yaw) which will steer the vehicle
upon command.
c. Building a vehicle with sufficient performance
to carry the on-board control system and a 0.1-gram
payload.
d. Demonstrating system performance by conducting
flight tests.
3. Modifications of Project Goal: None.
4. Accomplishments of This Effort Relative to Project
Goal and Contribution Toward Intelligence Objective:
Even though the project goals were accomplished, addi-
tional work must be done to meet the intelligence
objective. These include:
a. Provide an additional channel (pitch) of
control in both the laser and on-board guidance system.
b. Demonstrate two-channel controlled powered
flight outdoors in varying wind conditions to determine
emplacement accuracy.
c. Develop further the optical microphone payload
to meet weight and size requirements.
The feasibility of a controlled insectithopter vehicle
with limited operational capability has been investigated
and all program goals to this point have been achieved,
either by operational demonstration or through analysis
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:ligr
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of experimental results. Basic vehicle technology has
been developed to provide a vehicle capable of flying
at 0.8 g gross weight With flapping wing propulsion alone
and at 1.0 g with jet propulsion and cosmetic wing flapping.
The actual empty weight is nominally 0.4 g compared to a
target weight of 0.6 g. Performance measurements indicate
range and endurance capabilities of 200 meters and 60 seconds
with jet propulsion and cosmetic flapping for 1.0 g launch
weight.
Satisfactory stability and control characteristics
were analytically determined and experimentally demon-
strated in wind tunnel and free flight tests. Heading
error with controls fixed for both straight and turning
unpowered flight was repeatably less than 4. 50 mils.
A tracking, guidance, and control system was developed
and demonstrated for single-channel directional control
of the vehicle. The system includes a ROME laser and
telescope assembly which has been demonstrated at ranges
in excess of 140 meters�with a 1 mm target. Transmitted
power has been measured in excess of 1.2 watts with a
field of view of 80 mils. Tracking was demonstrated up
to 140 meter range with a moving target on both indoor
and outdoor ranges in various sunlight and wind conditions.
Designs for more sophisticated multi-channel systems have
been developed and analyzed.
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A thermo-pneumatic, ROME-powered rudder actuator was
developed and demonstrated at vehicle scale and weight
in wind tunnel and flight tests, meeting the Control
power and response time requirements for directional
control of the vehicle.
Wind tunnel and flight test experiments have demon-
strated the feasibility of the complete integrated system.
Controlled flight was repeatedly demonstrated with a
gliding vehicle and the ROME laser on an indoor flight
range. Limited powered flight tests were conducted out-
doors with fixed controls in winds up to 10 mph with a
heading error less than 4. 100 mils.
The ultimate demonstration of controlled powered
,flight has not yet been achieved. Considering the exten-
sive burden placed on the laser operator in the tracking
procedure and the additional directional perturbation
effects experienced with powered flights, it was con-
cluded that insufficient time remained in the contract
period to satisfactorily develop techniques for meaningful
powered controlled flights.
5. Evaluation of Project and Contractor: Technically, the
project must be evaluated as excellent. However, there
appears to be a decreasing lack of support from potential
users, and the additional research funds required to
meet the final intelligence objective is larger than
expected.
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The contractor's performance in solving the most
difficult and unique problems associated with this
'unusual program can only receive the highest acclaim.
. Discussion:
a. Origin of Project. An expressed need for a
remote audio emplacement system.
b. Technical Approach. To use an indigenous
insect-like vehicle.
c. Personnel and Funding Considerations. Key
personnel (research scientists) at ATC had conducted
tests on live insects, and the ROME laser technology
is proprietary to LTV, which owns 80 percent of ATC.
Initially, $40,000 was placed at ATC to demonstrate
aerodynamic and propulsive feasibility. The effort
described here was for $105,376.
d. Problems Encountered and Solutions. The entire
program was a composite of unique problem-solving. In
the area of aerodynamics, increased wing stiffness and
pexformance was required to carry the additional payload
and control system weight. This was accomplished by
incorporating boron fiber elements in the wing. Addi-
tional performance was obtained by venting the exhaust
aft to provide jet thrust. A larger engine was required
to provide increased power to the wings. With�the larger
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engine intake porting, lithium nitrate crystals (the
propellant) were being ingested into the engine. This
problem was solved- by incorporating a thin-walled con-
tainer for the lithium nitrate inside the fuel tank.
Structural and weight problems regarding the airframe
and on-board control systems were continually being
solved throughout the program.
e. Reasons for Failure or Success. The ability
of the contractor to try new materials, build an in-
expensive wind tunnel, and conduct many flight tests in
a fly it-fix it iterative approach to problem-solving
contributed in large measure to the technical success
of the program.
f. Recommendations for Further R&D and Disposition
of Final Product. Though further development is required
to provide for pitch control, emplacement accuracy, and
the flight weight optical microphone, the concept feasi-
bility is established. It is recommended that this addi-
tional work be done if and when a specific user/mission
can be defined so that user and mission specifications
can be addressed. To date, there is no final product
except general feasibility of being able to achieve the
intelligence objectives.
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7. Coordination: Various briefings have been given,
including OTS who would be responsible for user selec-
tion. As of this time, no user and/or mission has been
found. The final report has been given to OTS.
Charles N. Adkins
Project Officer
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