| With fast development of aerospace technologies,the remote detection of electrooptical loads has been highly required by fast aerospace platforms,such as reconnaissance and detection satellites,high-altitude long-endurance aircraft and hypersonic missiles.The technical requirements are increasingly high.The existing electro-optical detection technologies can barely meet the need of platform development.Centered on electrooptical remote detection technology of fast aerospace platforms,the thesis addresses the overall design method of multi-disciplinary rapid collaborative design with parallel electro-optical common elements,the macro-micro two-level composite stabilization platform control and step-stare scanning technologies based on the fast steering mirror(FSM)and the multi-band common aperture detection technology,so as to realize the remote rapid detection capability of fast aerospace platforms through the technical path of improving the "optical pod ratio" of the system.The main innovations are as follows:1.The overall design method of multi-disciplinary rapid collaborative design with parallel electro-optical common elements is studied to greatly improve the quality level and progress of complex electro-optical system development.By extracting the main system indexes that cannot be achieved by any single discipline or the core components of the multidisciplinary functions(such as optics and control),and using them as the common elements,parallel design method is adopted to obtain the optimal solution through only one iteration of system design,so that the coupling and control accuracy of the system are improved,and the size and weight of the electro-optical system are reduced.This solves the problems of long development cycle and difficult balancing of system indicators in the traditional cascade and simple parallel overall design method that caused by multiple iterations and lack of coupling design.2.The macro-micro two-level composite stabilization platform control and stepstare scanning technologies based on FSM are studied to significantly improve stabilization precision and imaging quality of the platform.By improving the traditional two-axis two-frame or two-axis four-frame mechanical stabilization platform,enhancing the precise stabilization level of the fast steering mirror,and using its high control precision and high bandwidth characteristics,the platform's stabilization accuracy is improved by an order of magnitude;the step-stare scanning is realized by the image space anti-scan compensation of the fast steering mirror,namely the servo stabilization platform,is in continuous stable angular motion and the fast steering mirror is in reverse angular motion according to the optical magnification in the optical path,so that the optical axis remained static to complete the staring imaging during the integration time of a millisecond detector,to increase the effective integration time of the infrared focal planar array detector and significantly improve the imaging quality.3.Based on the above researches,the "optical-pod ratio"(ratio of optical aperture to pod diameter)is adopted as an indicator to measure the integration degree of complex electro-optical detection systems and realize the optimal electro-optical system performance under the volume-mass constraints of the aerospace platform.By further researching multi-band common aperture detection technology and using diode pumped solid laser(DPL)technology,macro-micro two-level control stabilization platform technology,fast step-stare scanning technology and multi-detector multiplexing technology,the optical aperture and focal length of the system are improved to the maximum extent to achieve the long-range detection.4.The above theoretical research results are applied to the infrared detector of a lowaltitude fast flying platform and the infrared detector of a high-altitude fast flying platform.Then an engineering prototype is successfully developed under severe conditions such as short development cycle,small volume and weight and harsh operating environment,and the overall requirements are met.The multi-disciplinary rapid collaborative design method with parallel electro-optical common elements is adopted during the overall design.Then,the parallel sub-space multi-option rapid conceptual design and permutation optimization are transformed into the common element constraints of engineering design,to further guide the distribution of design weights between the optical system and the servo stabilization system.Next,the dynamic evaluation and iterative optimization of comprehensive performances are carried out for the design scheme on the electronic prototype to determine the overall technical solution.During development of the infrared detector of a low-altitude fast flying platform,in light of the requirement of small window and large scanning angle,the design weighting is that servo stabilization platform is primary and optomechanical system is secondary and the object space scanning scheme based on the gyro-stabilized mirror is adopted,which has high-precision and high-dynamic image stabilization capability and is a breakthrough in fast highdefinition scanning and imaging technology under the premise of small window,large scanning angle and high-angle resolution,and the design specifications are fulfilled;during development of the infrared detector of a high-altitude fast flying platform,the design weighting is that the optomechanical system is primary and the servo stabilization platform is secondary,and the fast step-stare scanning technology based on fast steering mirror composite axis control is adopted for the airborne fast scanning electro-optical imaging system;the optomechanical structures of the two-axis frame platform stabilized by three-axis fiber gyro,the telescopic system and the rear imaging system are designed and the fast steering mirror with small inertia is also adopted to carry out one-dimensional anti-sweeping,finally realizing 300 km long-range high-precision and high-dynamic stable infrared imaging and achieving the design specifications.The above theoretical results are applied in the development of the UAV electro-optical aiming pod: firstly,based on the core demand of improving the "optical pod ratio",the overall design method of multi-disciplinary rapid collaborative design with parallel electro-optical common elements is adopted to formulate the overall scheme of the electro-optical targeting pod;secondly,the coaxial and shared-aperture optical system is designed for the optomechanical system and the laser director subsystem is additionally adopted to form the overall optomechanical structure with multiple optical systems.Then,for the servo control system,the macro-micro control stabilization platform technology based on fast steering mirror is used to make the whole system have the characteristics of small size,light weight,high precision and high dynamic aiming ability.Finally,the design specifications are achieved through design simulation,which is at the international advanced level,and now engineering trial production is ongoing.The theoretical research and engineering development in this thesis provide theoretical methods and technical basis for the development of remote electro-optical detection systems on fast aerospace platform. |
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