A Study of a Reconnaissance Surveillance Vehicle
A Study of a Reconnaissance Surveillance Vehicle A Study of a Reconnaissance Surveillance Vehicle
System Elements NPS041003 34
Carbon wing, tail and engine nacelle 48” Ku-band Satcom antenna Satcom Radome Aluminum airframe EO / IR Sensor Northrop Grumman-RQ-4A (Tier II+ Air Vehicle) UHF Satcom antenna Synthetic Aperture Radar RR Allison AE3007H turbofan engine 5 psia and conditioned air for payload / avionics compartments Wing span - 116 feet Takeoff Wt - 25,600 lbs Payload - 2,000 lbs Endurance - 31.5 hrs Air vehicle avionics Redundant electromechanical actuators Common Data Link (CDL) Ground Control Panel Wing and fuselage fuel tanks used for cooling NPS041003 35
- Page 1 and 2: A Study of a Reconnaissance Surveil
- Page 3 and 4: GENERAL UAV ISSUES NPS041003 3
- Page 5 and 6: STRATEGIC • Worldwide OPS • Sel
- Page 7 and 8: Risk Reduction • Never attempt to
- Page 9 and 10: Design to Cost Lowest costs are ach
- Page 11 and 12: Redundancy • Level of Redundancy
- Page 13 and 14: DMS (Diminishing Mfg Sources) - Obs
- Page 15 and 16: Learn from Others’ Mistakes NPS04
- Page 17 and 18: Design Requirements NPS041003 17
- Page 19 and 20: 50,000 Ft Steady 20Kt Crosswind Com
- Page 21 and 22: System Selection NPS041003 21
- Page 23 and 24: Continuous coverage Analysis Approa
- Page 25 and 26: Original Design Objective Balance M
- Page 27 and 28: The HALE vehicle - (High Altitude L
- Page 29 and 30: Configuration Development NPS041003
- Page 31 and 32: Loral Systems, San Jose, CA Tier II
- Page 33: System Overview Wide-band data tran
- Page 37 and 38: Design Performance NPS041003 37
- Page 39 and 40: Wing Lift Coefficient 1.40 1.20 1.0
- Page 41 and 42: Design Implementation & Design Spec
- Page 43 and 44: Navigation & Guidance Schematic NPS
- Page 45 and 46: Maintainability / Accessibility Acc
- Page 47 and 48: Integrated Sensor Suite NPS041003 4
- Page 49 and 50: Daytime IR Imagery: March 26, 1999
- Page 51 and 52: Global Hawk Airborne Integrated Com
- Page 53 and 54: Air Vehicle-to-Ground Stations Inte
- Page 55 and 56: All-Encompassing System Development
- Page 57 and 58: . Pre-flight Checkout Remove before
- Page 59 and 60: Mission Start WPt • INS alignment
- Page 61 and 62: Temperature ~ Degrees F 100 60 20 -
- Page 63 and 64: VN Diagram Global Hawk Vn Diagram L
- Page 65 and 66: Gust Exceedance (1000 Hrs) Gust Exc
- Page 67 and 68: An Example of a Flight Control HCI
- Page 69 and 70: The Air Vehicle Status HCI H367-024
- Page 71 and 72: Examples of Autonomous Operations N
- Page 73 and 74: Post-flight Checks NPS041003 73
- Page 75 and 76: Summary 1. UAVs will demonstrate lo
- Page 77 and 78: Typical Dual VMS Aircraft Loss Rate
- Page 79 and 80: Design Requirements NPS041003 79
- Page 81 and 82: Affordability UFP COTS Interchangea
- Page 83 and 84: Design Implementation & Design Spec
Carbon wing, tail<br />
and engine nacelle<br />
48” Ku-band<br />
Satcom antenna<br />
Satcom<br />
Radome<br />
Aluminum<br />
airframe<br />
EO / IR<br />
Sensor<br />
Northrop Grumman-RQ-4A<br />
(Tier II+ Air <strong>Vehicle</strong>)<br />
UHF Satcom<br />
antenna<br />
Synthetic<br />
Aperture Radar<br />
RR Allison AE3007H<br />
turb<strong>of</strong>an engine<br />
5 psia and conditioned<br />
air for payload /<br />
avionics compartments<br />
Wing span - 116 feet<br />
Take<strong>of</strong>f Wt - 25,600 lbs<br />
Payload - 2,000 lbs<br />
Endurance - 31.5 hrs<br />
Air vehicle avionics<br />
Redundant electromechanical<br />
actuators<br />
Common Data<br />
Link (CDL)<br />
Ground Control Panel<br />
Wing and fuselage<br />
fuel tanks used for<br />
cooling<br />
NPS041003 35
Change language