飞行器系统动作聚类一体化设计方法

doi:10.12305/j.issn.1001-506X.2025.08.14

Abstract

Abstract:

Aiming at the problems of numerous and overlapping functional requirements in the design process of aircraft systems, which lead to a large amount of functional redundancy in the design results and the difficulty in fully utilizing the design space, an aircraft integrated design methodology via system action clustering is proposed. Based on the axiomatic design framework, the design process of subsystems and physical domain components is modeled, and the functional requirements, system behavior, and interaction relationships between actions are analyzed in depth. Similar actions are clustered to obtain several action subsets, and the integrated physical domain components corresponding to the action sets are obtained through branch and bound method to achieve integrated design and improve the utilization rate of design space. Taking the integrated design of the top-level subsystem architecture and the power subsystem of the orbital spacecraft as an example, the rationality of the method is verified. The design results showed that the proposed method can effectively reduce the number of subsystems and physical domain components, thereby reducing the redundancy of the aircraft system design.

Key words: integrated aircraft, axiomatic design, action clustering, branch and bound

CLC Number:

V 57

Zhe LIU, Changzhu WEI, Cheng WEI, Jialun PU. Aircraft integrated design methodology via system action clustering[J]. Systems Engineering and Electronics, 2025, 47(8): 2558-2569.

Figures/Tables 16

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References 31

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初始聚类簇数	$\max ( {{d_{m - j}}} )$范围
${n_1}$	[0,0.5)
${n_2}$	[0.5,0.8)
${n_3}$	[0.8,1]

参数	含义
FR1	系统能够满足入轨并在轨运行的基本需求
FR2	系统能够探测
FR3	系统能够导航增强
FR4	系统能够通信中继
BE1	运行系统
BE2	跟踪探测目标
BE3	生成导航信息
BE4	中继信号
AC1-1	提供支撑
AC1-2	控制载荷温度
AC1-3	传输遥测遥控信息
AC1-4	提供上升段姿轨控
AC1-5	提供上升段配电
AC1-6	提供入轨段姿轨控
AC1-7	提供入轨段配电
AC1-8	提供上升段姿轨控指令
AC1-9	提供入轨段姿轨控指令
AC1-10	提供星务管理数采控制
AC1-11	提供在轨段姿控
AC1-12	测量上升段姿态
AC1-13	测量入轨段姿态
AC1-14	测量在轨段姿态
AC1-15	提供在轨段配电
AC2-1	提供变轨/调姿动力
AC2-2	提供探测设备配电
AC2-3	控制探测任务载荷
AC2-4	获取光学探测信息
AC2-5	处理存储下传图像数据
AC3-1	下传导航信号
AC3-2	提供导航设备配电
AC3-3	控制导航任务载荷
AC4-1	传输通信信息
AC4-2	提供通信中继设备配电
AC4-3	控制通信中继任务载荷

序号	第一层次动作标签
1	时间−上升段
2	时间−入轨段
3	时间−在轨段
4	约束−单位时间所能发送的信息量
5	约束−单位时间所能接收的信息量
6	约束−姿态测量精度
7	约束−所能输出的力矩
8	约束−所能输出的功率
9	约束−所能输出的推力
10	约束−所能输出的支撑力大小
11	约束−输出单次指令的耗时
12	约束−输出图像的质量
13	输入−信息
14	输入信息类型−导航信号
15	输入信息类型−通信信号
16	输入信息类型−遥测量
17	输出−信息
18	输出−物料
19	输出−能量
20	输出信息类型−姿态信息
21	输出信息类型−导航信号
22	输出信息类型−控制指令
23	输出信息类型−目标图像
24	输出信息类型−通信信号
25	输出物料类型−支撑
26	输出能量类型−力矩
27	输出能量类型−推力
28	输出能量类型−热能
29	输出能量类型−电能

子动作集合	动作
电源系统	提供上升段配电
	提供入轨段配电
	提供在轨运行段配电
	提供探测设备配电
	提供导航中继设备配电
	提供通信增强设备配电
探测系统	获取探测信息
探测系统	交互信息
综合电子系统	提供上升段姿轨控指令
	提供入轨段姿轨控指令
	提供在轨段星务管理、数据采集控制
	控制探测任务载荷
	控制导航中继任务载荷
	控制通信增强任务载荷
测控系统	传输遥测遥控信息
	传输导航信号
	放大电磁波信号
动力推进系统	提供上升段姿轨控
	提供入轨段姿轨控
	提供在轨段变轨/调姿动力
结构系统	支撑载荷
热控系统	控制载荷温度
姿轨控系统	测量上升段姿态信息
	测量入轨段姿态信息
	测量在轨段姿态信息
	控制在轨段姿态

行为	物理域设计参数
提供能源I-BE1	电源系统DP1
探测信息I-BE2	探测系统DP2
产生指令I-BE3	综合电子系统DP3
传输信息I-BE4	测控系统DP4
提供姿轨控动力I-BE5	动力推进系统DP5
提供结构支撑I-BE6	结构系统DP6
提供热控I-BE7	热控系统DP7
提供姿态测量与力矩I-BE8	姿轨控系统DP8

Aircraft integrated design methodology via system action clustering

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参数	含义
FR81	系统能够提供上升段姿轨控制动力
FR82	系统能够提供入轨段姿轨控制动力
FR83	系统能够提供在轨段姿轨控制动力
BE81	提供上升段姿轨控制动力
BE82	提供入轨段姿轨控制动力
BE83	提供在轨段姿轨控制动力
AC81-1	输出上升段轨迹控制推力
AC81-2	输出上升段姿态控制力矩
AC82-1	输出入轨段轨迹控制推力
AC82-2	输出入轨段姿态控制力矩
AC83-1	输出在轨段轨迹控制推力
AC83-2	输出在轨段姿态控制力矩

传统设计		一体化设计
部件	质量/kg	部件	质量/kg
上升段大推力发动机	28	上升段大推力发动机	28
入轨段大推力发动机	28	入轨/变轨段大推力发动机	28
变轨段大推力发动机	28	上升/入轨RCS姿控发动机	4
上升段RCS姿控发动机	4	在轨机动RCS姿控发动机	4
入轨段RCS姿控发动机	4	—	—
在轨机动RCS姿控发动机	4	—	—

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