Natural disasters such as tornados, hurricanes, and wildfires have a devastating impact on communities where these events occur. Lives are lost, citizens are injured, and infrastructure and property are destroyed. In the aftermath resources are limited, while the response and recovery is hampered by reduced communications and infrastructure damage. Based on this scenario use these high-level base requirements
to propose a series of derived/low-level requirements for the design of a UAS down to the element level (e.g., air vehicle element, command & control [C2], payload, data-link [communications], and support equipment) to support response and recovery efforts.Ensure you include applicable test requirements to verify the system will work as proposed and an associated schedule to perform the required phases of development (e.g., system development, ground testing, and in-flight testing). In addition, develop an overview to identify associated design considerations and decisions for your derived requirements. You are encouraged to locate and examine commercially-off-the-shelf (COTS) components to determine capability associated with the UAS elements for the derived requirements and testing strategy.
Request for Proposal
Natural
disasters have a massive impact on the areas in which the disaster occurs.
During natural disasters, lives are lost, people are hurt, and homes,
buildings, and infrastructure are damaged or destroyed. In the aftermath of
these disasters, response and recovery can be slowed by the limited number of
resources available to aid those in need. This request for proposal shall
review the major base requirements of transportability, air vehicle elements,
and payload for a UAV that is designed for search and rescue operations. During
natural disasters, people can easily get lost in all the chaos; in the
aftermath, search and rescue teams will come to the aid of these people. By
allowing search and rescue teams to utilize unmanned aircraft, search and
rescue efforts will become more efficient and areas that cannot be easily
reached by ground search and rescue teams can be further explored for missing
people. The UAV being developed for this proposal will allow search and rescue
personnel to deliver lifesaving materials to the lost people if needed. The UAV
will be a quadrotor design that will allow the UAV to takeoff and landing
vertically. This function will also allow the operator to thoroughly search an
area hit by a natural disaster. The time frame for this UAV will be 2 years in
development.
Transportability:
1.1 The
entire system (including all elements of the UAV) shall be transportable in a
hard, protective case that will weigh less than 50 lbs enabling one person to
carry the UAV.
1.2 The
hardened case shall have various compartments dedicated for all components for
the UAV.
1.3 The
hardened case shall be one single case which will enable the entire UAV/control
system to be carried at once.
1.4 The
hardened case shall be designed to be picked up and carried by a single person
or rolled on the ground via a handle with wheels on the case.
1.5 The
hardened case shall be designed to withstand a fall from a height of 5 feet
with minimal damage to the case.
1.6 The
hardened case shall be designed to protect the UAV by absorbing the shock from
a fall of 5 feet.
Air Vehicle Elements
1.1 Shall
be capable of flight up to 500 feet in altitude above ground level.
1.1.1
The UAV shall climb at a rate of 2 meters per
second.
1.1.2
The UAV shall be capable of descending at a rate
of 1.5 meters per second.
1.1.3
The UAV shall be capable of operating in
temperatures ranging from 0° to 40° C
1.1.4
The UAV shall be capable of flight in sustained
winds up to 25 mph.
1.1.5
The UAV shall utilize satellite GPS for precise
movements.
1.2 Shall
be capable of sustained flight (at loiter speed) in excess of one hour.
1.2.1
Battery life for the UAV shall exceed two hours
of flight time due to a hydrogen fuel cell.
1.2.2
After sustained flight at loiter speeds, the UAV
shall return to the operator.
1.3 Shall
be capable of covering an operational radius of one mile.
1.3.1
The UAV shall have the ability to operate at
distances up to 3 miles.
1.3.2
The UAV shall calculate the distance and fuel
required to return to the operator.
1.4 Shall
be deployable and on station (i.e., in air over mission area) in less than 15
minutes.
1.4.1 The
UAV shall have each component that can easily snap into place.
1.4.2 UAV
components shall easily be taken out of the hardened case due to ergonomic
fittings for the components.
1.4.3 Shall
have a maximum cruising speed of 44 mph depending on wind conditions.
1.5 Shall
be capable of manual and autonomous operation.
1.5.1
The operator shall control the UAV when
necessary.
1.5.2
The operator shall use the autonomous functions
when necessary.
1.5.3
Autonomous operation shall be programed into the
control station when manual operations are not being utilized.
1.5.4
Specific flight patterns shall be integrated
into the systems on the UAV for thorough coverage of an area.
1.6 Shall
provide capture of telemetry, including altitude, magnetic heading,
latitude/longitude
position, and orientation (i.e., pitch, roll, and yaw).
1.6.1
UAV data shall be sent back to the operator for
review of the flight.
1.6.2
UAV shall utilize GPS to transmit information
about the flight back to the operator.
1.7 Shall
provide power to payload, telemetry sensors, and data- link
1.7.1
The UAV shall utilize the electrical systems on
board to power the payload, telemetry, and data link sensors.
1.7.2
The UAV shall have built in redundancies in the
event that a function on the UAV ceases to operate properly.
1.8 Shall
provide capability to orbit (i.e., fly in circular pattern around) or hover
over an object of interest.
1.8.1
The UAV shall utilize GPS to hold a specific
position based on latitude/longitude coordinates.
1.8.2
The UAV shall be capable of holding any altitude
up to 500 feet set by the operator.
1.8.3
The UAV shall utilize GPS to fly specific search
grids that will allow the operator to search an area carefully.
1.8.4
The operator shall have the ability to choose
where to have the UAV orbit based on a specific position in the air.
Support Equipment:
1.1 Design
shall identify any support equipment required to support operation
1.1.1 To
support the operation, SAR personnel shall require rope to attach to the UAV in
the event that a person is found and in need of medicine, water, or food.
1.1.2 SAR
personnel shall require a lightweight basket to carry important supplies if a
person is found and ground teams cannot reach the person immediately.
1.1.3 SAR
personnel shall require a thermal imaging camera for operations at night.
1.1.4 SAR
personnel shall require multiple hydrogen fuel cells for the safe operation of
the UAV on long flights.
Testing Requirements:
Tests will be completed to
determine if the functions described above are testable or verifiable. Commercial
off the shelf (COTS) components shall be used in the development of this UAV.
In order to reduce potential development costs, simulation software will be
used to test the abilities of the UAV first. After simulation data indicates
the UAV will operate based on the design requirements, the UAV will be tested
in person. Each requirement will be rigorously tested to determine if the UAV
will be able to aid search and rescue personnel during SAR operations.
1. Transportability
Testing
1.1 Storage of UAV components.
1.1.1
The UAV components will be placed into the
hardened case cut outs to determine if the UAV will fit snugly into the case.
1.1.2
The case will be closed to determine if the case
will close properly without damaging any of the components of the UAV.
1.1.3
The ground control unit will also be placed into
the hardened case to determine if spacing is an issue.
1.2 Durability
of hardened case.
1.2.1
The hardened case will be dropped from heights
varying from 1 foot to 5 feet.
1.2.2
Once the case has been dropped from these
heights, the case will be opened to determine if the components of the UAV have
not been damaged.
1.2.3
The outside of the case will be looked at
carefully to determine how much damage has occurred at each height.
1.2.4
All the components of the UAV will be placed
inside the case to determine if the case is less than 50 pounds.
1.2.5
Determine if the case can easily be carried
based on its shape and determine if the wheels on the case roll smoothly when
applicable.
Air Vehicle Element
2.1 Flight Characteristics
2.1.1
The UAV shall be flown at varying
altitudes up to 500 feet to ensure the UAV is airworthy.
2.1.2
The UAV will be flown at the minimum
and maximum operating temperatures to ensure the UAV will not fail at
temperatures near these extremes.
2.1.3 The max cruising, ascent, and descent speeds
will be tested in normal flight conditions. The UAV will also be tested on days
that are windy. The maximum operation in wind speeds of 25 mph shall be tested.
2.1.4
The hydrogen power cell will be tested
to ensure the UAV can fly for one hour loitering and up to one more hour of
standard flight.
2.1.5
The UAV will be flown out to 3 miles to
determine if the UAV will warn the operator of the maximum distance being
achieved.
2.1.6
The communications between the UAV and
the ground control unit will be tested during the long range flight.
2.1.7
Multiple tests will be ran to determine
that the UAV can be deployed and in the air within 15 minutes. If the UAV
cannot be assembled in less than 15 minutes, a different design based on a
collapsible UAV will need to be researched.
2.1.8
The UAV operator shall test the manual
operation capabilities of the UAV. The operator will also put the UAV into an
autonomous flight mode to test the flight grip capabilities of the UAV. The
proper pitch, roll, and yaw controls will be tested during this time.
2.1.9 Determine if the UAV can send flight data,
images, and video back to the operator.
2.1.10
The UAV will be placed into an orbit
around a specific point. At this time, the UAV will be tested to determine if
the UAV can hold a position based on latitude and longitude. The ability of the
UAV to hold altitude will be tested, and flight grid patterns will also be
tested again during this time.
2.1.11
The hydrogen fuel cells will be checked
carefully for proper operation.
3. Support Equipment
3.1 Required Support Equipment
3.1.1
For intended search and rescue
operations, a rope shall be attached to the UAV. At this time, the payload
characteristics will be determined. The UAV will be designed to carry small
payloads in the event that a missing person is found but ground search and
rescue personnel cannot reach the person.
3.1.2
A lightweight metal basket will be
attached to the UAV. The UAV will be flown at varying speeds and altitudes to
ensure the UAV can carry the required payloads.
3.1.3
Materials such as food, water,
medicine, clothes, or even lifejackets will be placed inside the basket of the
UAV. The UAV will be flown at various speeds and altitudes to ensure the UAV
can fly with light payloads.
3.1.4
The camera on the UAV will be tested to
ensure clear videos and pictures can be taken during flight and at loiter
speeds.
3.1.5 The thermal imaging camera shall be tested
at night to ensure proper operation.
The Development Process
The 10-Phase
Waterfall Method will be utilized as a starting point for the development of
this UAV. This development process would be the most efficient process because
during phases 5, 6, and 7, the testing of the UAV could be completed as these
phases concern testing and development of the UAV. This would allow a smooth
transition to the last phases of the waterfall method which are certification,
production, and support.
To ensure an acceptable level of
safety in the operation of any airborne system, including UAV systems, the airworthiness of the system and its safe
usage of the airspace in which it operates
must be addressed at an early stage in the design, and pursued in the development and operational trial phases
(Austin, 2010, pg. 223).
By using the
waterfall method, the UAV should be completed in a reasonable amount of time (1
year) and ready for use in search and rescue operations. The specimen test,
prototype build and test, and the development of the UAV (modifications) will
take the longest amount of time to complete as the developer wants to ensure
that each function of the UAV is testable and verifiable. Phases 1-4 will be
completed in 4 months, phases 5-8 will be completed in 5 months, and phases
8-10 will be completed in 3 months.
The UAV being created for search and
rescue missions has been designed to carry light payloads of water, food,
clothes, or medical supplies in the event that ground SAR personnel cannot
reach a person directly affected by a natural disaster. The UAV has also been
designed for search and rescue missions when a person is lost or missing. The
standard camera will be utilized during the day for SAR operations and the
optional thermal camera can be used at night during missions. The UAV being
designed must be created to carry small payloads for SAR missions. This is why
basic derived requirements for support equipment must be tested. If the UAV
cannot carry small payloads, SAR personnel will not get full usage out of the
UAV. A hydrogen fuel cell has been selected for use instead of batteries of gas
because of the flight times that are achievable. A hydrogen fuel cell may be
more efficient than gas or batteries, and it could be lighter than having to
carry gas. Unlike a battery that has a short flight time, the hydrogen fuel
cell intended for use of this UAV should allow the UAV to remain in the air for
2 hours. This would prevent the operator from having to fly the UAV back for
gas or a battery replacement. The requirements for this UAV will ensure that
the UAV is more than capable for usage during search and rescue operations for
missing people or for delivering small loads of supplies to a person who cannot
immediately be reached by ground personnel. The GPS grid patterns will allow
the operator to manually or autonomously follow sweeping patterns that will
allow the operator to thoroughly search and area. The UAV will also be
developed to warn the operator of altitude limitations, distance limitations,
and when the hydrogen fuel cell is running low. The computer systems within the
UAV should allow the UAV to return to the operator autonomously based on
latitude and longitude. All the design considerations, testing, modifications,
certification, and production of the UAV shall be completed in a steady manner
to ensure that each step is completed correctly.
References
Austin, R. (2010).
Unmanned aircraft systems: UAVS design, development, and deployment. Chichester, U.K: John Wiley & Sons Ltd.
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