RFI Attachment 3 MQM-171 Demonstrated Performance.pdf

MQM-171

Unmanned Aircraft System – Target

(UAS-T)

Aerial Target

Demonstrated Performance

18 January 2021

MQM-171 Demonstrated Technical Performance

The design and prototypes for the MQM-171A/B UAS-T system have been demonstrated to meet all threshold requirements for a UAS-T specified in the Operational Requirements Document for Unmanned Aerial Vehicle Target (Revision 1), 25 Aug 03. The MQM-171 UAS- T air vehicle, ground control equipment, and systems components are detailed in the Griffon Aerospace drawing set 030-xxxxx. Essential physical size, operational characteristics, flight performance characteristics, and air vehicle control techniques include:

Minimum Operating Altitude: <100 ft AGL under manual control 1

<1000 ft AGL under autopilot control 1

Altitude Ceiling: 13,800 ft MSL 1

Minimum Cruise Airspeed: 60 knots true airspeed (KTAS) 1

Maximum Cruise Airspeed: 115.5 KTAS 1

Minimum Air Vehicle Control 5 Km under manual control 1 Slant Range: 25 Km under Piccolo ground station control 1

50 Km under TTCS-U control with range repeater stations 1

Unlimited when operated under SATCOM modem augmentation to the Piccolo autopilot system

Wing Span: 5.2 m 1

Overall Length: 4.2 m 1

Fuselage Diameter: 0.45 – 0.51 m 1

Propulsion Configuration: 3W Modellmotoren 684i B4, or equivalent, pusher prop 1

Loiter Endurance: Minimum of 1 hr at operational altitude and range (≈1.5 hr total flight time) 1

Extendable with installation of auxiliary fuel tanks

Infrared Signature: Low inherent infrared signature. 2

Radar Frequency Signature: Low inherent radar cross section.3

Visual Signature: As depicted in Griffon Aerospace, Inc., drawing

030-010000

Air Vehicle Payload: Capability of the air vehicle to accommodate onboard payload packages such as proximity scoring devices, identification friend or foe transponder, etc., weighing up to 15 pounds and requiring 28 volt dc electrical power. 4

Flight Termination: Manual landing, skid landing 1 Emergency parachute recovery system 1 Autopilot programmable for loss of link or loss of power options 1

Launch: Pneumatic launch 1

Recovery: Skid landing under manual control 1

Parachute landing under commanded or autopilot control 1

Operational Control: Manual control within line of site 1

Autopilot control beyond line of site Cloudcap Piccolo autopilot, or equivalent 1 TTCS-U compatible autopilot operation 1

Over-the-Horizon beyond line of site control using Cloudcap Piccolo II autopilot and and SATCOM modem

Navigation Accuracy: Altitude +/- 100 ft 1

Airspeed +/- 10 knots 1 Heading +/- 3° 1

Data Link: 380 – 400 MHz primary data link 1

900 MHz secondary data link 1

1 The physical appearance, flight performance, and mission control parameters of the MQM-171 target system are well defined for use in Department of Defense testing. Adjustments could result in significant impacts on the planning or execution of test programs for Department of Defense weapon systems under development.

2 Weapon system infrared seekers are sensitive to the heat signature provided by a target system.

Any adjustments to the primary sources of heat in the air vehicle, i.e., engine, batteries, avionic components, may effect the infrared signature of the air vehicle and impact seeker capabilities.

3 Radar cross section of both fiberglass and carbon versions of the MQM-171A/B, air vehicle were measured at Point Mugu, CA, Radar Reflectivity Laboratory in June 2007 and are on file at the Threat Systems Management Office.

4 Air Vehicle Payload. The provisions for space, weight, and power to accommodate a payload on the air vehicle provide for integration of Government owned range scoring, tracking, and emergency flight termination equipment, such as those listed in the “Compendium of Target Systems” into the air vehicle.