A Study of a Reconnaissance Surveillance Vehicle
A Study of a Reconnaissance Surveillance Vehicle A Study of a Reconnaissance Surveillance Vehicle
A Real-world Turbulence Event • Date: January 22, 1999 • Time: 17:22Z • Location: 36.126° N Latitude, 118.007° W Longitude • Altitude: 55,000 ft • Event Description: Over a period of 30 seconds the aircraft experienced a Mach Number increase from 0.60 to 0.65 before the control system compensated for the speed change. Altitude rate, during the event, varied between +3,000 fpm and -1,000 fpm. Maximum load factor attained was 1.25 g’s. • Mission Summary: Excluding the turbulence event the aircraft experienced altitude rate variations from +2,000 fpm to -2,000 fpm and load factor varied from +0.6 g to 1.3 g during the cruise climb. Mach Number varied between 0.57 and 0.63. NPS041003 90
AV2 -4 T urb ulence Even t.5 Altitude Altitude Rat e Mach No. Air spe ed Err or Load Fac tor Ft Ft/Min Kt cas 60000 55000 60000 60500 61000 61500 62000 4000 2000 0 -2000 60000 0.65 60500 61000 61500 62000 0.60 GLOBAL HAWK PROGRAM INFORMATION Altitude Rate 0.55 60000 60500 61000 61500 62000 10 6 2 -2 -6 Velocity Error -10 60000 1.5 60500 61000 61500 62000 1.0 g 50000 AV2-4 Turbulence Event Data NPS041003 91 Mach Load Factor 0.5 60000 60500 61000 61500 62000 TIME Sec Altitude 85
- 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
- Page 85 and 86: Electrical Power Schematic NPS04100
- Page 87 and 88: Vehicle Fuel System Schematic NPS04
- Page 89: Single Event Upsets >≅ 40 K Ft Co
- Page 93 and 94: Turbulence Event Conclusions � Fl
- Page 95 and 96: Typical Fault Logic, Lost Carrier N
- Page 97 and 98: Airspace Coordination Requirements
- Page 99: Civil Surveillance Requirements NPS
AV2 -4 T urb ulence Even t.5<br />
Altitude<br />
Altitude<br />
Rat e<br />
Mach No.<br />
Air spe ed<br />
Err or<br />
Load<br />
Fac tor<br />
Ft<br />
Ft/Min<br />
Kt cas<br />
60000<br />
55000<br />
60000 60500 61000 61500 62000<br />
4000<br />
2000<br />
0<br />
-2000<br />
60000<br />
0.65<br />
60500 61000 61500 62000<br />
0.60<br />
GLOBAL HAWK PROGRAM INFORMATION<br />
Altitude Rate<br />
0.55<br />
60000 60500 61000 61500 62000<br />
10<br />
6<br />
2<br />
-2<br />
-6<br />
Velocity Error<br />
-10<br />
60000<br />
1.5<br />
60500 61000 61500 62000<br />
1.0<br />
g 50000<br />
AV2-4 Turbulence Event Data<br />
NPS041003 91<br />
Mach<br />
Load Factor<br />
0.5<br />
60000 60500 61000 61500 62000<br />
TIME Sec<br />
Altitude<br />
85
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