The global market for very small aircraft and UAVs modified or designed specifically for intelligence, surveillance, and reconnaissance (ISR) and/or weapons platforms appears to be growing.  This is a niche market for aerial vehicles that are simple but have a proven design lineage.  The system must not require sophisticated maintenance or complex operating procedures.  For these reasons, HeloWerks has created the Unmanned Aerial Vehicle (UAV) version of the successful WASP HX-2 helicopter.  This design configuration is known as the HX-3 HORNET.  The following information describes the general characteristics, performance differences, payloads, and flight control system for the HORNET UAV.
 

 DESIGN PHILOSOPHY

1. Use as much of the existing HX-2 components to reduce initial cost.

2. Provide reliable aerial platform for a number of weapon systems/ISR in a rapid “plug and play” reconfiguration system.

3. Stable, easily flown platform.

4. Low radar cross section.

5. Reduced maintenance due to infinite life rotor blades and composite construction.

6. Provide stable ground handling.

7. Dedicated weapons mount to easily accommodate a variety of payloads.

8. Use of heavy fuel (JET-A).
    

 THREE VIEW OF HX-3 HORNET UAV

PERFORMANCE

1. Total useful load capability: 544 lbs

ISR Ball: 37 lbs

Two rocket tubes (8 FFAR rockets): 214 lbs

Two ASRR machine guns: 124 lbs

40 gallons JET A: 276 lbs

2. Maximum cruise endurance: approximately 4 ½ hours

3. Maximum fuel capacity:  60 gal. JET-A

 POTENTIAL PAYLOADS

LETHAL

1. 8 FFAR rockets in two HURL pods.

2. ARSS machine gun pod using the SAW 249 light machine gun.

NON-LETHAL

1. Laser

2. Acoustic beam immobilizer

FLIGHT AVIONICS DESCRIPTION

CPU – Central Processing Unit.  1.86 GHz Intel core 2 Duo, 8GB flash,2 GB RAM, Ethernet, RS244/232 and USB serial ports.  RTD Corporation CMA22MVD1860HR-2048.

MCU – Micro Controller Unit.  This unit allows the helicopter to be flown by the pilot in case of a CPU failure.  Two SX28 micro-controllers and one PIC16F877.

Wireless LAN – The CPU communicates with the GCS via the wireless LAN telemetry system.  Proxim RangeLAN2.

IMU – Inertial Measurement Unit.  This unit provides temperature compensated data from three gyros, three accelerometers, and triaxial magnetometer.  Analog Devices ADIS16405.

GPS – Global Positioning System.  Provides a robust PVT solution.  Novatel OEMV-1

Altimeter – Barometric altimeter provides additional altitude information to the GPS measurement.  Honeywell HPB200A.

Servos – Linear actuators sized by individual use.  W – series.  CK Design.

OCU – Operator Control Unit.  This station could be located on an accompanying aircraft, ground station, or boat.

FLIGHT AVIONICS DIAGRAM

There will also be an appropriate communications subsystem that will integrate an advanced digital networking radio with one or more low-bandwidth/high reliability radios.  In addition, the control system will support a variety of external interfaces to the various payloads.  These interfaces will include RS232/488 (serial), discrete, and USB I/O.  Weapons interfaces will require 1553 (or other) military bus compatibility.
 

SolidWorks rendering credit: Bryan Cuervo, Accurate Automation Corp.