Rfp Long Endurance Uav

LONG ENDURANCE UAV I.

OPPORTUNITY DESCRIPTION

Currently a wide variety of intelligent gathering options are available as national resources. These are typically controlled at the highest levels within the government and are used primarily for strategic information gathering. Satellites and manned vehicles, such as the SR-71 have fulfilled these roles and continue to do so. The recent conflicts have demonstrated the utility of unmanned aerial vehicles (UAV) with their ability to identify targets, and perform battle damage assessment. The success of these systems and their strategic counterparts provides an opportunity to fill a gap that will provide intheater commanders with round the clock targeting intelligence on mobile targets. These can be used to support contingency operations throughout the world. Identified as a key aspect of the opportunity is the requirement to detect and target mobile targets, such as theater ballistic missile launchers. II.

PROJECT OBJECTIVE

The objective of the design is to develop a tactical reconnaissance system that fills the gap where cloud cover inhibits satellite and manned aircraft coverage or where these assets are unavailable. This system will be equipped with sensors and a data link furnished by the government. Commercial non-developmental items (NDI) are encouraged for use on this vehicle. III.

REQUIREMENTS AND CONSTRAINTS

The design shall be of an unmanned aircraft. All performance requirements shall be standard day and atmosphere unless noted otherwise. Technology availability date is 2015. Design Mission Profile 1. Warm up and system check for 10 min. 2. Take off 3. Climb at best rate of climb to cruising altitude. 4. Cruise for 500 nmi at speed and alt which minimizes time to station and fuel burn. 5. Climb at best rate of climb to 25000 ft. 6. Loiter for 24 hours at best endurance speed. 7. Descend to best cruise altitude, no credit for range.

8. Return cruise for 500 nmi. minimizing fuel burn. 9. Descend with no credit for range 10. Land, 10% fuel reserves. 11. Taxi for 5 minutes. Special Design Requirements 1. Payload = 523 lbs; space and power attached. 2. For transportability, the vehicle must fit into a 20' x 5' x 5' shipping container. 3. Must be capable of performing a sustained 2.5 g maneuver at speed for minimum power at 25,000 ft. 4. A method of controlling the vehicle including navigation and pilotage must be described in the stability and control section. 5. Two versions of the aircraft are to be sized. One with conventional propulsion systems and one using fuel cells. Both aircraft will be of the same configuration, but may be of different size to accommodate the mission as required. Safety Constraints: 1. Fuel reserves of 10% to account for contingencies. 2. The aircraft must have a T.O. field length of 900 feet at 5000 ft ISA. 3. A failure modes effect analysis must be performed to account for loss of communication with the aircraft so as to ensure the safety of personnel and property on the ground. A description of the results shall be provided. Economic Constraints: Production cost estimates should be based on a production run of 500 aircraft. Total flyaway cost and DOC are to be estimated. Manufacturability: The proposal must describe consideration of features that simplify manufacturability and assembly. Sustainability: The proposal must describe features of the aircraft design that maximize reliability, simplify maintenance, and minimize special ground support equipment and ground turnaround time. The aircraft must be able to be operated from austere sites. Environmental: The proposal must describe design features that minimize environmental impact as far a pollution and noise are concerned. V.

ENGINE DATA

Conventional engine data will be provided. VI.

PAYLOAD DATA Item

SAR EW Jammer Com Relay MTI Radar FLIR Data Link DL Antenna Flight Computer GPS Antenna Inertial Ref Sys

Weight (lbs) 88 11 100 110 100 50 8 40 2 14

Power (watts) 470 14 1000 1050 644 323 14 100 0 30

Vol (in) 1.25 cu ft 6x6x12 3.5 cu ft 3.5 cu ft 12 in Dia x 14 in H 8x10x14 10 in Dia x14 in H 14x8x6 3x3x.5 7x7x10

Comment Fixed Antenna

360 deg

Subsystems: (Provided below are specifications for conventional systems. Alternative/advanced subsystems are permitted with appropriate substantiation and assurances that they can be available within the specified technology timeframe) Landing Gear 1. Retractable gear shall be incorporated into the design. 2. Gear must withstand a 10 fps vertical velocity at the landing weight with no damage to gear or aircraft structure. 3. Brakes must be capable of stopping the aircraft at takeoff weight within the specified field length. 4. Landing gear must be positioned so that the aircraft possesses a 50 ft radius turning circle. Hydraulic 1. The system must be designed for operating pressures of at least 3000psi. 2. Emergency pressurization of the hydraulic system shall be provided in the case of primary system failure. 3. Burst testing of components shall exceed 2 times the operating pressure. 4. Emergency hydraulic power shall be sufficient to lower and lock landing gear in the down position as well as providing sufficient braking force for landing and ground taxi. 5. The hydraulic systems shall provide sufficient power for 30 minutes of flight maneuvers to include one landing approach sequence. Fuel 1. The fuel system shall be both pressure and gravity refuelable. The former shall

withstand pressures up to 50 psi. 2. The fuel system shall incorporate the ability to measure and display fuel quantities remotely to the crew during refueling and flight. 3. Shut off valves shall be incorporated to cut off supply of fuel to the engines in the event of an engine fire (in the case of multi-engine configuration). 4. The system shall allow the crew to manage fuel distribution in the aircraft.