SURV-A1

The SURV-A1 Unmanned Aircraft Systems (UAS)

Shannon Gibson

ASCI 530- Unmanned Aerospace Systems

Module 7, Activity 7.4 & 7.5

Embry-Riddle Aeronautical University-Worldwide

27 September 2015

         The mission I have chose for the development of an unmanned aircraft system is the SURV-A1 (S1). The SI will be used to find life in disaster areas, where exploration would be difficult. This SI system would have the ability for easy setup and launch for aerial reconnaissance to find life using infrared (IR) technology and shorten the search time and lessen the area to allow access for life saving missions. This development and first real-time deployment for operations has been given a one-year expectancy.

Transportability:

- Entire system (all elements) shall be transportable (in hardened case) and weigh less than 50 lbs. (one person lift), with back-straps for the ability to set up in hard to reach areas that vehicles may not be able to reach.

- Air vehicle element and control element shall fit in single hardened case no larger than 2.5 cubic feet, with top and side handle and wheels. The case shall be able to withstand constant jostling and heat/flame retardant.

- In this pack, there shall be two parts, the ground control station, and the actual UAS. The UAS shall have the ability to break down into two parts for easy stowage, and the ability to simply click it together for easy readiness.

Payload:

-      Shall have IR cameras with the ability to send real-time video to the GCS, where the operator can radio in findings, such as how many human bodies or animals have been found

-      The IR shall give enough detail to see the shape of the contact, such as if it is human or other type of mammal

-      Camera shall have the ability for 360 degree view of area being surveyed

-      The thermal sensitivity should have the ability to be adjusted for various types of disasters

-      GPS system shall allow for exact coordinates to within 2 feet to be given back to operator

-      Camera shall have the ability to film and transmit up to 500 feet AGL and 2 miles from operator/GCS

-      Shall be powered by air vehicle element, less than 12 volts

-      Daytime, nighttime and foul weather IR capable inclusive of rain and wind up to 25 knots

Air vehicle element:

-      SI shall be capable of flight up to 500 feet AGL and 1 miles from GCS

-      No flight interruption and be able to withstand heat up to 850 degrees Fahrenheit

-      Easy assembly from two pieces into a complete unit

-      The S1 shall have the ability to orbit as well as proceed to a latitude and longitude with an error margin of 2 feet.

-      Shall be able to remain airborne for longer than 1 hour

-      Shall be able to recover, change batteries and re-deploy immediately

Datalink (Communications):

-      Shall use VLOS, up to 2 miles

-      If lost link occurs, hover for 30 seconds and return to GCS for reboot

-      Data link shall use less than 12 volts

Test Requirements and time line:

Testing requirements shall ensure the SI can meet all standards listed above. Time line start date, October, 2015.

October, 2015: Division of responsibility for requirements and definition of system and subsystems

November 2015 – January 2016: Designing system with details on allowable payload characteristics

February –April 2016: Initial inclusion of all parts into a complete system; GCS and air asset.

March 2016: Subsystem and system testing

April – May 2016: redesign of systems that failed operational testing

June –July 2016: Trial 2: inclusion of all parts into a complete system; GCS and air asset.

August- September 2016: System with subsystem testing

October 2016: Full operational capability