Short-wave infrared large field of view light and small aircraft capture and tracking objective lens system

Abstract

A short-wave infrared large visual field light small aircraft catching tracking objective lens system belongs to the technical field of optical design and is provided with a flat filtering plate, a front lens group, a rear lens group and a charge coupled device (CCD) coaxially arranged from the left to the right. The front lens group sequentially comprises a first meniscus lens and a second meniscus lens from the left to the right, and the first meniscus lens and the second meniscus lens are both bent towards the CCD. The rear lens group sequentially comprises a third meniscus lens and a biconvex lens from the left to the right, and the third meniscus lens is bent towards the front lens group. Lenses in the front lens group and the rear lens group are all spherical lenses. Signal light is imaged on the CCD after passing through the flat filtering plate, the front lens group and the rear lens group. The system is suitable for a wave band ranging from 0.79 mum to 0.88 mum, a full field of view is 2 omega >=32 degrees, focal length f'=20 mm, relative aperture: D / f'=1 / 2.85, resolution rate in the full field of view ranges from 0.5m to 130m, full-wave band absolute distortion is smaller than 1.5 mum, color bias <=0.5 mum, and working temperature is -70 DEG C-+70 DEG C.

Description

technical field [0001] The invention belongs to the technical field of optical design, and relates to an objective lens system, in particular to a capturing and tracking objective lens system for a light and small aircraft with a short-wave infrared large field of view. Background technique [0002] To achieve in-orbit docking of two vehicles flying in orbit, a special docking mechanism is required. [0003] In the existing photoelectric equipment, the position and attitude measurement of the target aircraft usually uses star sensors to image stars, and the attitude and position of the target aircraft can be determined by looking up the ephemeris from the star images. But the star sensor is to image the infinitely distant stars, and the focal plane for imaging the infinitely distant stars is located on the surface of the CCD. There will be a large image motion on the sensor CCD, and it is impossible to accurately calculate the position of the center of mass of the marker li...

AI Technical Summary

Problems solved by technology

However, the system contains a parabolic reflective surface, a hyperboloid reflective surface, a high-order aspheric surface, and a concave ellipsoidal surface, which are difficult to process and detect. At the same time, the large diameter of the optical system results in a large volume and a small viewing angle. The observation field is too small when the object distance is not large

[0010] When the finite object distance of the imaging device in the above-mentioned patent changes, the position of the center of mass of the imaging energy of the incident light of a certain field of view will change, and the complex structure will occupy a large space volume, and the space adaptability is unknown. The launch cost brought by its own weight will also increase accordingly

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