Mid-wave infrared imaging has the advantages of all day, high resolution, strong adaptability to the environment, so it is widely used. In high-speed target tracking and aiming. The target flying speed is extremely fast and the DOF (depth of field) of the fixed focal lens is limited, so the zoom lens is required. In order to ensure that the tracking target will not be lost, a fast zoom requirement of no more than 0.3s is proposed. According to the requirements, a compact athermalized mid-wave infrared dual field fast zoom lens is designed. The focal length is 400 mm and 200 mm, and the passive athermalization design is adopted which can meet the working temperature of - 40° to + 60°. the lens can match the cooling detector with effective pixel of 640 × 512, size of 15 μm and F/4 .The volume of the detector can be controlled in the range of L (196mm) × w (116mm) × H (185mm). The zoom group structure is considered in the design, and the switching time is less than 0.12s, and the image plane is stable when the zoom group switching.
With the development of infrared surveillance technology, the short focus zoom LWIR lens has been paid to more and more attention. In this paper, dual fields zoom lens with the fields of 20°×25°/8°×10° are designed by two different methods. The main specifications of the lens include: aperture is 1 / 2, detector resolution is 640 × 512, pixel size is 15 μ m, temperature adaptability is -40 ° to + 60 °. And we compare the volume, weight, imaging transmission, transmissivity and economy of the lens by different methods. It is found that the re-imaging method has smaller volume, weight and economy. While another imaging method has better transmittance, so the imaging system can reach higher noise equivalent power at the same image quality
In the light of optical-electronic imaging system ,designed a continuous zoom lens with a optical aperture of 60mm and a zoom range of 18-246mm. Summarized the disadvantages of the former zoom lens and a low temperature resistant and high precision structure ,named the special-shaped slide and cam zoom structure is proposed, and carrying out the theoretical analysis and the detailed structural design. Theoretical analysis shows that this kind of structure can make the sliding friction between the cam and the main mirror tube turned into rolling friction ,thus reducing the torque demand.it also helps to eliminate the stuck phenomenon of the cam in low temperature environment .The special-shaped slide frame structure can help eliminate the tilt Angle of the moving mirror group in the zoom process ,thus reducing the variation of optic axis .In the he final test, the zoom time is not longer than 8s in the environment which temperature is only -45°C,and the variation of optic axis is smaller than 0.3milliradian,both meet the target requirement.
When the aerial camera photograph,a variety of image motion is caused by prior to the flight, pitching, rolling and vibration and other reasons,thus leading to the existence of relative motion of the illuminated objects in the focal plane of a photosensitive medium, the image is blured,and the imaging quality of the camera is seriously affected. Various causes of image motion and effects on image is analyzed by this paper,the necessity of image motion compensation is expounded. By analyzing existed methods of image motion compensation ,and on this basis, a new multi degree of freedom motion compensation method is designed,through the parallel mechanism motion,for image motion compensation by optical image motion compensation principle,a variety of airborne camera to take pictures of the image motion also can be eliminated.
Thermal control and temperature uniformity are important factors for space remote sensing cameras. This paper describes the problems with existing systems and introduces the thermal design of a space optical remote sensing camera. Firstly, based on the theory of wave-front aberration distribution, the thermal control index of a space remote sensing camera is proposed. Then on the basis of the analysis of the heat flux environment outside the camera space, the thermal optical analysis of the camera is performed by using the finite element analysis method at high and low temperature conditions. The results show that the transfer function of the optical system with the resolution of 50 lp in the full field of view is more than 0.4. The optical design index can be satisfied, and the rationality of the thermal design is verified. The simulation result meets the requirements of optical design very well. Therefore the study in this paper can be used as an important reference for other space optical systems, which has certain engineering significance.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.