Every year in the United States and other countries of the word, natural disasters leave millions of dollars in destruction and loss of human lives. The need for property and effective information is highly necessary for the companies and agencies responsible to provide recovery and help. The objective of this work is to present the proposal for the design of UAS system that will provide surveillance in the event of natural disasters with the intention for recollection of information, prompt response and recovery.
The system should satisfy the following design requirements, configurations and limitations.
UAS System Proposal:
1. Transportability
1.1 Transportation shall have DJI Phantom 4 Case professional.
1.1.2 Shall the Interior dimensions 20’’ x 14’’ x 14’’ (Case, 2015)
1.1.2 Shall Exterior dimension 21.2’’ x 16’’ x 15.6’’
1.1.3 Shall the case be water resistant and impact resistant?
1.1.4 Shall Weight 14.6 lbs.
2. Air vehicle element
The project vehicle name is the UAV Scout XY
2.1 The Scout shall have vertical take-off and landing VTOL.
2.2 The vehicle shall be a quadcopter requiring not launch equipment
2.2.1 Shall have Height 30 cm (1 ft.)
2.2.3 Shall be loaded weight 5.0 lb.)
2.2.4 Shall have power plant of 4 x electric motor
2.2.4.1 Shall be powered with Intelligent LiPo batteries each one.
2.2.5. Shall have Propeller diameter: 12 inch
2.2.5.1 Shall have max. Speed 31 miles/hr.
2.3. Shall have capability to flight up to 1000 feet altitude above ground level (AGL)
2.3.1 Shall be able to flight for 1 hour and 30 minutes.
2.3.2 Shall be able to operated covering and operational radios of 3.0 miles from the user
2.3.3 Shall by flight directly by the operator or with preprogrammed using GPS.
2.3.3.1 Shall be able to monitors external conditions as wind speed, internal functions, as battery level.
2.3.3.2 Shall be able to take autonomous automated decisions as return to the starting point, land in emergency, hover and maintain steady flight.
2.3.3.4 Shall be able thru GPS to flight following all necessary navigation.
2.3.4 Shall be deployable in less than 15 minutes.
2.3.5 Shall be able to capture telemetry with payloads that include gimbal-mounted digital still video cameras.
2.3.6 Shall have close camera for remote sensing and night-vision camera with a stabilized zoom camera.
2.3.7 The power to payload is provided with battery Intelligent LiPo battery that power, telemetry sensors, and data-link.
3 Command and Control (C2)
3.1 Shall have Manual and autonomous operation of the system with hover in fixed positions?
3.2 Shall be capable of manual and autonomous operation for altitudes up to 500 feet AGL.
3.3 Shall have redundant flight control to prevent flyaway.
3.3.1 Shall provide depict telemetry in all navigation requirements.
3.3.1.1 Shall have visually depicted sensor views for payloads.
4. Payload
4.1 Shall the system have video operation for more than 500 feet AGL?
4.2 Shall be capable of color daytime and night time video with infrared cameras use a thermographic camera that can perceive infrared radiation.
4.2.1 Shall have use the wavelength of infrared for fog or warm objects different that night vision with operates in visible light and near-infrared ranges (0.4 to 1.0 um).
4.2.2 Shall capable to use infrared video operation up or exceeding 500 feet AGL
5. Data-link (communications)
5.1 Shall be capable of communication range of three miles visual line of sight (VLOS)
5.2 Shall has redundant communication capability for C2
5.3 Shall provide with an Intelligent-LiPo battery keep charge for more than 1hour.
5.3.1 Shall allow interoperability data-link by using sufficient power from the UAV.
Support equipment
Not support equipment is required to support operation
System development overview
The system will be tested for performance and reliability. This system shall comply with the necessary safety, reliability and capability require for the certification. The system development life cycle will be composed by the reduction of cost given to new electronics that are less expansive. The time for complete development of the project is two years as it is show in the table below.
For demonstrate the chronologic phases of the project. The 10 phase waterfall method is going to be use. See the table below.
PHASES
|
Years
|
|||||||
Concept Design
|
1
|
|||||||
Concept Research
|
2
|
|||||||
Preliminary Design
|
1
|
|||||||
Detail Design
|
1.5
|
|||||||
Specimen Test
|
0.5
|
|||||||
Development
|
1
|
|||||||
Certification
|
2
|
|||||||
Production
|
2
|
|||||||
Support
|
5
|
|||||||
Five
|
Years
|
|||||||
 |
||||||||
Template of this table was taken from template (University, 2015)
System development UAS design requirements
The requirements of the user has been taken in consideration as cost, performance, radios of action, endurance, operating altitude, maximum altitude, maximum speed, climb rate. Also, Design considerations for control station as a mobile unit with portative transportation for deployment.
The system mission, planning and control that monitor the system, offers the possibility of operation LOS and BLOS. Also, the system has the communication and control C23 interfaces for transmitting, processing, and receiving the information. For safety and security, the system will have the future of autonomous landing, take off and take any decision of safety during the system emergency.
For the system considerations for the payloads the number of pay loads will be define by the amount of disaster areas provide for the user, are based in the power consumption and price of the payload. The design considerations for data link are the protection from the external treats and it is done by the use of algorithms and appropriated use of frequencies and the deployment area. The system requirements for traceability are base in the satisfaction, verification and dependency of the system.
For certification of the system the request of the certificate of authorization COA will be obtained with the FAA. During the system development with the FAA regulations is necessary to outline the objective of the use of the system. For establishing the reliability, the revision of the possible failures of the system, the mission and the components and redundancies that directly affecting the life-cycle cost of the system have to be considered.
Components testing is necessary for determine the commercial-off-the-shelf (COTS) of electrical components of the system. Also, evaluation for resistance, temperature, acceleration, strength, materials fatigue life, wear and functionality. Testing of the subsystem is done by capture effects of stress and assemblies to be test as undercarriages, flight control system, and power plant. Integration of the testing is done by check for wear, fluid leaks, and signs of overheating, security of connectors. And check of all communications with antennae. The flight test is performed at the beginning of the life-cycle process. For the process of system certification it will be granted, after the system performance report is done base on endurance and reliability and considering the system limitations and restrictions of range and airspace operating limitations (University, 2015).
References
Aeryon, A. l. (2016). Aeryon Scout.
Case, C. D. (2015). Case Club. Retrieved from www.caseclub.com.
University, E.-R. A. (2015). Unmanned Systems: System Development and Test & Evaluation (T&E).
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