同一工程系统存在的系统输入受限、模型的不确定性、环境干扰输入、系统突变或出现系统故障等工程问题，传统的状态能控性、能观测性等定性理论难以用于工程实际。为此，通过对系统模型不确定性的描述，分析了传统系统状态能控性、能达性存在的问题，通过对飞机舵机的系统输入受限、阵风等运行环境干扰产生的额外输入、飞机重载空投或空天飞机分离等系统突变或者系统故障进行模型描述，研究了系统在不同情况下的能控性、能稳性的判定问题，在此基础上提出了同一系统的状态、输出工程一致能控性的定义、判定方法，同时给出了系统状态、输出的工程一致能观测性定义。研究结果能够统一传统的系统能控性、能达性、能稳性判定，而且与经典控制中快速性、准确性判定具有相似性。针对高性能飞行器研制，给出了设计、风洞与飞行试验的分析、验证要求，通过实际纵向飞行控制器的设计结果对工程一致能控性进行了说明。

In engineering systems， challenges such as constrained system inputs， model uncertainties， environmental disturbance inputs， system mutations， or system failures often arise， making traditional qualitative theories like state controllability and observability difficult to apply. This paper describes the issues of traditional system state controllability and reachability through the analysis of model uncertainties. By modeling scenarios such as input constraints in aircraft actuators， additional inputs from environmental disturbances like gusts， system mutations during heavy airdrop or aerospace vehicle separation， and system failures， the paper investigates the controllability and stability determination for systems under these different conditions. On this basis， the paper proposes definitions and determination methods for the engineering consistent controllability of system states and outputs within the same system， and also provides a definition for the engineering consistent observability of system states and outputs. These conclusions are able to unify traditional judgments on system controllability， reachability， and stability， and are analogous to the rapidity and accuracy determinations in classic control. For the development of high-performance aircraft， the paper outlines the analysis and verification requirements for design， wind tunnel， and flight tests. An explanation of engineering consistent controllability is provided through the design results of an actual longitudinal flight.