Test Stand for Propellers and Rotors in VTOL Drone Systems

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Test stand overview [8–10]_

LY-70KGF Thrust Stand and Dynamometer Wing Flayng

WF-CO-30KGF Coaxial Thrust Stand Wing Flayng

Series 1780 Test Stand TYTO Robotics

Modular Stand for testing aircraft electric propulsion systems NASA

Rotor/propeller test stand in Hover Institute of Aviation

Test Stand	Thrust	Torque	Propeller diameter	Electric parameters	RPM
±70 daN	±50 Nm	Max ~ 1.52 m	Current: 0–300 AVoltage: 5-110 V	60,000 – 150,000 RPM
±30 daN	±20 Nm	Max ~1.00 m	Current: 0–150 AVoltage: 5–65 V	60,000 – 150,000 RPM
±75 daN	±48 Nm	Max ~1.77 m	Current: 0–500 AVoltage:0–100 V	100,000 RPM
±225 daN	±200 Nm	Max ~1.77 m	N/A	20,000 RPM
±3,000 daN	±4,800 Nm	Max ~10 m	Electric power: 315 kW	Min. 126 RPM, max. 1,500 RPM

Initial parameters, step function of the torque and the corresponding currents - 1st cycle_

No.	Starting point - torque (Nm)	RMS current corresponding to torque (A)	Ending point - torque (Nm)	RMS current corresponding to torque (A)
1			8.5	14.2
2	6.0	10.0	10.0	16.7
3			14.0	23.3
4			25.5	42.5
5	23.0	38.3	27.0	45.0
6			31.0	51.7
7			35.5	59.2
8	33.0	55.0	37.0	61.7
9			41.0	68.3
10			47.5	79.2
11	45.0	75.0	49.0	81.7
12			53.0	88.3
13			60.5	100.8
14	58.0	96.7	62.0	103.3
15			66.0	110.0
16			70.5	117.5
17	68.0	113.3	72.0	120.0
18			76.0	126.7

Initial parameters, step function of the torque and the corresponding currents — 2nd cycle_

No.	Starting point - torque (Nm)	RMS current corresponding to torque (A)	Ending point - torque (Nm)	RMS current corresponding to torque (A)
1	6.0	10.0	76.0	126.7
2	23.0	38.3
3	33.0	55.0
4	45.0	75.0
5	58.0	96.7
6	68.0	113.3

Comparison of actual results with the simulation results for the same RMS currents, Aerobat propeller_

	Experimental research		Numerical model research
Current (A)	Torque (Nm)	Rotational speed (RPM)	Torque (Nm)	Rotational speed (RPM)
3.86	2.4	640.0	2.3	720.0
8.76	5.3	1,065.0	5.3	1,087.0
17.45	10.7	1,550.0	10.5	1,534.0
29.08	18.0	2,030.0	17.5	1,980.0
36.80	22.7	2,280.0	22.1	2,226.0
44.70	27.8	2,520.0	26.8	2,456.0
53.6	33.1	2,755.0	32.2	2,688.0
66.5	40.5	3,020.0	39.9	2,995.0

Adjustment time for Łukasiewicz — Institute of Aviation propeller — 2nd cycle_

Lp.	Starting point - torque (Nm)	Ending point - torque (Nm)	Adjustment time (s)
1	6.0	76.0	3.4
2	23.0	76.0	3.1
3	33.0	76.0	3.0
4	45.0	76.0	2.9
5	58.0	76.0	2.8
6	68.0	76.0	2.2

Comparison between the actual results and the simulation results for the same RMS currents, for the carbon composite Łukasiewicz — Institute of Aviation propeller_

	Experimental research		Numerical model research
Present current (A)	Torque (Nm)	Rotational speed (RPM)	Torque (Nm)	Rotational speed (RPM)
11.09	7.62	565.0	6.65	540.0
23.99	15.35	825.0	14.39	794.0
38.96	24.40	1,045.0	23.38	1,011.0
54.32	33.37	1,215.0	32.69	1,195.0
63.99	38.73	1,305.0	38.39	1,296.0
75.37	45.15	1,405.0	45.22	1,406.0
89.29	52.30	1,515.0	53.57	1,531.0
103.81	59.35	1,615.0	62.29	1,651.0
121.99	66.91	1,715.0	73.19	1,789.0
137.16	72.61	1,770.0	82.30	1,897.0

Moments of inertia of elements included in the model_

	I (kg mm2)
The knot from the engine to the propeller attachment	13,503
Propeller mounting hub	4,350
Propeller	246,083

Adjustment time for Aerobat propeller — 1st cycle_

No.	Starting point - torque (Nm)	Ending point - torque (Nm)	Adjustment time (s)
1	6.0	8.5	3.9
2		10.0	3.9
3		14.0	3.9
4	23.0	25.5	2.5
5		27.0	2.5
6		31.0	2.5
7	33.0	35.5	2.1
8		37.0	2.1
9		41.0	2.1
10	45.0	47.5	2.0
11		49.0	2.0
12		53.0	2.0

Adjustment time for Łukasiewicz — Institute of Aviation propeller — 1st cycle_

No.	Starting point - torque (Nm)	Ending point - torque (Nm)	Adjustment time (s)
1		8.5	6.0
2	6	10.0	6.0
3		14.0	6.0
4		25.5	4.7
5	23	27.0	4.5
6		31.0	4.5
7		35.5	3.7
8	33	37.0	3.7
9		41.0	3.7
10		47.5	3.0
11	45	49.0	3.0
12		53.0	3.0
13		60.5	2.8
14	58	62.0	2.7
15		66.0	2.7
16		70.5	2.2
17	68	72.0	2.2
18		76.0	2.2

Adjustment time for Aerobat propeller — 2nd cycle_

No.	Starting point - torque (Nm)	Ending point - torque (Nm)	Adjustment time (s)
1	6.0	53.0	2.5
2	16.0	53.0	2.4
3	23.0	53.0	2.3
4	32.0	53.0	2.3
5	40.0	53.0	2.2
6	47.0	53.0	2.0