Electric Landing Assist Device of Shipborne Helicopters and Its Key Characteristics Analysis

doi:10.12382/bgxb.2022.0523

Abstract

Abstract:

An electric landing assist device for shipborne helicopter is designed to address the problems of significant capture impact and high energy consumption of aircraft ship integrated secure and traverse(ASIST) system. The performance requirements of landing assist device during the capture and transshipment tasks are presented by analyzing the working conditions. According to this, a transmission scheme of electric landing assist device is proposed. A dynamics model of the transmission system is established based on the theory of power bond graph; The proposed dynamics model is compared with the hydraulic landing assist device through the simulation test. The results show that the capture speed is reduced by about 92%, and the maximum impact force is reduced by about 94%. The electric landing assist device can execute the helicopter transshipment tasks with an external load of 21kN and reduce energy consumption by about 29%. These research achievements are of great significance for broadening the application scope and reducing the energy consumption of ASIST. In addition, the introduced modeling method, which considers both the dynamic and energy consumption characteristics, also provides a reference for the dynamic modeling of other complex mechanical systems.

Key words: shipborne helicopter, landing assist device, landing assist system, aircraft ship integrated secure and traverse system, power bond graph, dynamic characteristics, energy consumption characteristics

CLC Number:

TH238

LIU Qian, ZHANG Zhuxin, ZHAO Dingxuan, WANG Hui, QIN Zhanyong. Electric Landing Assist Device of Shipborne Helicopters and Its Key Characteristics Analysis[J]. Acta Armamentarii, 2024, 45(1): 241-252.

Figures/Tables 28

Fig.1 Schematic diagram of ASIST

Fig.2 Capture diagram of landing assist device

Fig.3 Impact curve (2.5m/s)

Fig.4 Impact curve (0.2m/s)

Fig.5 Schematic diagram of transshipment of landing assist device

Fig.6 Connected coordinate system

Fig.7 Force analysis diagram

Table 1 Motion parameters under level-3 sea conditions

参数	数值	参数	数值
θ/(°)	10	g/(m·s^-2)	9.8
a_X/(m·s^-2)	1	a_Z/(m·s^-2)	0.5
M_H/kg	6 000	f	0.02
L/m	7	L_H/m	0.9
ρ/(kg·m^-3)	1.29	v_W/(m·s^-1)	12
A_XC_W	20	L_W/m	0.9
L_E/m	0.9	L_bc/m	3.5

Fig.8 Schematic diagram of transmission system for electric landing assist device

Table 2 Characteristic equation and bond graph model

名称	符号	特征方程
阻性元件	R	e(t)=Rf(t)
容性元件	C	e(t)= $q (t) C$
惯性元件	I	f(t)= $p (t) I$
流源	Sf	f(t)=Sf
势源	Se	e(t)=Se
转换器	TF	$e 2 = m e 1 f 1 = m f 2$
1结	1	$e 1 = e 2 = … = e n ∑ i = 1 n α i f i = 0$
0结	0	$f 1 = f 2 = … = f n ∑ i = 1 n α i e i = 0$

Table 2 Characteristic equation and bond graph model

名称	符号	特征方程
阻性元件	R	e(t)=Rf(t)
容性元件	C	e(t)= $q (t) C$
惯性元件	I	f(t)= $p (t) I$
流源	Sf	f(t)=Sf
势源	Se	e(t)=Se
转换器	TF	$e 2 = m e 1 f 1 = m f 2$
1结	1	$e 1 = e 2 = … = e n ∑ i = 1 n α i f i = 0$
0结	0	$f 1 = f 2 = … = f n ∑ i = 1 n α i e i = 0$

Fig.9 Bond graph model for transshipment

Fig.10 Bond graph model for capture

Fig.11 Capture velocity curve of mechanical claw

Fig.12 Velocity planning curve

Fig.13 Schematic diagram of simulation

Table 3 Parameters of transmission system for electric landing assist device

传动部件	参数	数值
电机	输出转速Sf/(rad·s^-1)
	转动转化为平动TF/(rad·m^-1)	20.61
同步带传动	同步带刚度C/(m·N^-1)	1.92×10^-7
	平动转化为转动TF/(m·rad^-1)	48.52×10^-3
减速机输入端	转动惯量I/(kg·m²)	4.25×10^-3
	转动阻尼R/(N·m·s)	4.7×10^-2
减速机	减速比TF	40
	丝杆刚度C/(rad·N^-1·m^-1)	7.8×10^-6
减速机输出端	转动惯量I/(kg·m²)	22.95×10^-3
	转动阻尼R/(N·m·s)	5.3×10^-3
动滑轮	质量I/kg	35.75
	转动转化为平动TF/(rad·m^-1)	628.93
链传动	链条刚度C/(m·N^-1)	1.49×10^-9
	倍行程效应TF	0.5
机械爪	摩擦阻尼R/N	30
	质量I/kg	44.328
直升机	阻力Se/N	2.1×10⁴
	质量I/kg	6×10³

Fig.14 Motor output speed and torque curves

Fig.15 Velocity and displacement curves of mechanical claw

Fig.16 Schematic diagram of a part of transmission system for hydraulic landing assist device

Fig.17 Bond graph model of hydraulic landing assist device

Table 4 Parameters of transmission system for hydraulic landing assist device

传动部件	参数	数值
电机	输出转速Sf/(rad·s^-1)
齿轮泵	转动转化为流量TF/(rad·m^-3)	2.09×10⁶
	内部泄漏R/(m³·s^-1·Pa^-1)	3.21×10^-12
液压管路	内部流阻R/(Pa·s·m^-3	0.91×10¹¹
单向阀	内部流阻R/(Pa·s·m^-3)	3.76×10⁹
换向阀	内部流阻R/(Pa·s·m^-3)	1.03×10¹⁰
	内部泄漏R/(m³·s^-1·Pa^-1)	3.3×10^-13
	液压油刚度C/(m³·Pa^-1)	2.51×10^-14
	内部泄漏R/(m³·s^-1·Pa^-1)	1.04×10^-12
液压缸	流量转化为平动TF/(m²·s^-1)	5.02×10^-3
	质量I/kg	46.32
	摩擦阻尼R/N	12.6
动滑轮	质量I/kg	35.75
	摩擦阻尼R/N	25.0
链传动	链条刚度C/(m·N^-1)	1.49×10^-8
	倍行程效应TF	0.5
机械爪	摩擦阻尼R/N	30
	质量I/kg	44.328
直升机	负载运动阻力Se/N	2.1×10⁴
	负载质量I/kg	6×10³

Fig.18 Motor output curve of hydraulic landing assist device

Fig.19 Motor output curve of electric landing assist device

Fig.20 Helicopter motion velocity curve

Fig.21 Energy consumption curves of energy storage elements

Fig.22 Energy consumpation curves of resistance elements

Fig.23 Energy curve of system input

Fig.24 Power curve of system input

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