S.P.EYE•UAV performing the observation mission •Enlarge the existing aircraft surveillance range
Principal Requirements and constrains: •Air-Borne, Air Released UAV •Min. extra range –100 nm •Real time air-borne mission control •Two UAV-s in ‘gondola’
King Air B200 – Mother Plane
Range 3283 km Endurance 8 hr Cruise speed 220 kt Top speed 292 kt Useful load 1790 kg
Dimensions: Length 13.16 m Wingspan 16.61 m Height 4.54 m
General Mission Scheme
airplane
3
on an airplane
• Airborne control ability
Doors open UAV ejected by
BRU-46 Doors close Inflating parachute
Parachute decrease velocity Stabilization in air UAV is releasing from its shell
The UAV is free in the open air
Wings unfolding, beginning of the mission
Simulation
33% Unknown,
80 km/hr 60 km/h 150 km/hr 111km/h Concept Speed
$100000 Concept n.a. $100000 30 000$ Concept Cost
picture
Conclusion: The “Non-Returnable UAV” concept was chosen.
MONGuard:
497
7
The Camera was placed in the front of the vehicle to ensure maximum spatial view The Antenna was placed in the same line as the wings, to prevent aerodynamic changes as best as possible. Generator, places next to the engine. The Transmitter and Receiver were placed arbitrary to balance the moment. Self-destruct Mechanisms: 1 placed near the camera, 2 placed on the transmitter and receiver and 3 was placed for balance and will detonate towards the fuel tank. Fuel Tank changed due to the rest of the configuration.
Camera Transmitter + Receiver
Self-destruct Mechanism Antenna
The new configuration has the same center of gravity
Hence we don’t need to make a new control system.
Dimensions Weight
Wide angle
2-4X electronic
The EO payload best suited to SP-EYE purpose is: MicroPop
D104mm
H180mm
“Pylons” with standard
launch units BRU-46
In addition it will contain •wiring • Doors opening mechanism •“Gondola”-’s reinforcements
Name Picture Weight ,kg Dimensions L, w, h mmxmmxmm
Quantity
~20 n/a n/a
10
Chosen geometric configuration
This configuration is optimal. Foregoing calculations will be based on it.
11
12
Gondola influences on the flow and aerodynamic performance:
• Drag • Roll • Yaw • Pitch • Side force • Lift Model scaling The chosen scale is 1:25 Wind tunnel constraints: • Wingspan must not exceed 65cm • Cross section area must not exceed 5% of the wind
tunnel’s cross section.
• General surface geometry (Parasolid) was received. Surfaces were translated to solid bodies
• Wind model creation process The scale was changed (1:25).
“Gondola” geometry (including configuration)
CAD model
14
15
Gondolas and other parts were connected with bolts and nuts. Nuts were fixed on the plastic surfaces with glue.
Nut
Assembly
16
•It was decided to connect the balance connector and wing reinforcement. • Usually axisymmetric balance connector is used. It was decided to design original connector to accomplish this task.
The back of the model is holed to install a balance. The hole diameter was chosen to enable possible balance displacements.
Balance connector assembly
Wind tunnel test preliminary calculations
Based on plane’s and gondola’s geometric properties only, the following results were obtained:
Wind tunnel test process
• Alpha- sweep to obtain plane’s longitudinal characteristics
• Beta- sweep to obtain plane’s lateral characteristics
• Smoke and tuft tests to understand the flow inside the cavity of the open gondola.
These tests held in three configurations: • Clean plane
•Short gondola •Long gondola
Test results
-8 -6 -4 -2 0 2 4 6 8 10 12 -0.8
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8
, deg
C L
-8 -6 -4 -2 0 2 4 6 8 10 12 -1
-0.5
0
0.5
1
1.5
, deg
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
-0.6
-0.4
-0.2
0
0.2
0.4
0.6
0.8
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
0.4
0.5
Lateral
-8 -6 -4 -2 0 2 4 6 8 10 12 0
0.05
0.1
0.15
C D
Original plane
Long gondola
Short Gondola
-25 -20 -15 -10 -5 0 5 10 15 20 25 0.02
0.025
0.03
0.035
0.04
C D
Original plane
Long gondola
Short Gondola
-6 -4 -2 0 2 4 6 8 10 12 0
0.05
0.1
0.15
expected: 3%YC 6%NC 9%RC
, 0.0104 (28.5%)
, 0.0083 (22.6%)
D Long
D Short
Reason for inappropriate results Stream Separation
For better evaluation of the drag in the wind tunnel test the Re number should be increased
to demonstrate the real CD. 24
Aircraft Model
From “Fluid-Dynamic Drag” by Hoerner S.F.
Reason for inappropriate results “Gondola” position
We have 2 releasing modes:
First release – smooth flow
FWD
25
25
What do we have: King Air B200 cabin dimensions:
Max. Width: 1.4 m
26
1400
1400
THE CHOSEN LAYOUT:
Requirements VS Achievements: Enlarging the surveillance range – possible within 100 NM
LOS communication – possible within Airborne Control Station ‘Gondola’ capability for carrying two UAVs – possible, including
equipment for each mission EO Sensor of 1.5 kg - The ‘MicroPop’ EO sensor fulfills the
requirement
Mr. Moti Ringel
Mr. Marcel Leventer
Mr. Prosper Shounshan
Mr. Danny Bodick
Mr. Tzvika Shahar
Dr. Ehud Kroll
Prof. Gill Iosilevskii
Prof. Gregory Kopp
Prof. Moshe Idan