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CN-122015759-A - Large-view-field sun sensor and method for spacecraft

CN122015759ACN 122015759 ACN122015759 ACN 122015759ACN-122015759-A

Abstract

The application discloses a large-view-field sun sensor for a spacecraft and a method thereof, and relates to the technical field of light detection. The large-view-field sun sensor comprises a polyhedral base and a plurality of light intensity detection units, wherein the polyhedral base is provided with a plurality of detection surfaces arranged on the side edge of the polyhedral base, each detection surface is obliquely arranged in the same direction of the polyhedral base and is in convex and divergent distribution, the light intensity detection units are arranged on the detection surfaces, and the light intensity detection units are configured to output light intensity signals proportional to the effective coverage area of sunlight on the light sensitive surfaces of the light intensity detection units. The application uses the projection areas of the polyhedral base and the light intensity detection unit to detect the light intensity signals, replaces the wide-angle lens system required by the traditional imaging sensor, eliminates the problems of optical distortion and uneven energy distribution of the wide-angle lens in the edge view field, greatly expands the view field and simultaneously ensures high-precision measurement in the view field range.

Inventors

  • SHEN SHIAN

Assignees

  • 深圳滕星科技有限公司

Dates

Publication Date
20260512
Application Date
20260209

Claims (10)

  1. 1. A large field of view sun sensor for a spacecraft, comprising a polyhedral base, said polyhedral base comprising: the detection surfaces are arranged on the side edges of the polyhedral base, and each detection surface is obliquely arranged in the same direction of the polyhedral base; The light intensity detection units are arranged on the detection surfaces and are configured to output light intensity signals proportional to the effective coverage area of sunlight on the light intensity detection units.
  2. 2. The large field of view sun sensor for a spacecraft of claim 1, wherein said polyhedral base further comprises a vertical plane; The detection surfaces are arranged around the edges of the vertical surfaces, and the included angle between each detection surface and the vertical surface is an obtuse angle; the light intensity detection unit is also arranged on the vertical plane.
  3. 3. A large field of view sun sensor for a spacecraft as claimed in claim 2, wherein said vertical plane is a regular polygon plane and a plurality of said detection faces are connected to edges of said vertical plane.
  4. 4. The large field of view sun sensor for a spacecraft of claim 2, wherein the number of said detection faces is three or more, and said three or more detection faces are uniformly distributed along the circumference of said vertical face.
  5. 5. The large field of view sun sensor for a spacecraft of any one of claims 2 to 4, further comprising a filter unit connected to said vertical face of said polyhedral base and to said corresponding detection face and covering a photosensitive path of said light intensity detection unit.
  6. 6. The large field of view sun sensor for spacecraft of claim 5, wherein said filter unit is a quartz glass cover plate and an attenuation film system is plated on the surface of said quartz glass cover plate.
  7. 7. The large field of view sun sensor for a spacecraft of claim 2, wherein said light intensity detection unit comprises a first detection unit and a plurality of second detection units, The first detection unit is attached to the vertical surface; The second detection units are respectively attached to the corresponding detection surfaces.
  8. 8. The large-view-field sun sensor for spacecraft according to claim 1, wherein a plurality of independent installation cavities are arranged in the polyhedral base, and each light intensity detection unit is respectively accommodated in the corresponding installation cavity; and a plurality of independent light-isolating pieces are arranged between the installation cavities and used for isolating light rays reflected by different installation cavities.
  9. 9. A measurement method based on a sun sensor according to any one of claims 1 to 8, characterized by comprising the steps of: acquiring light intensity detection units positioned on a vertical plane and a plurality of detection planes with different preset angles, and respectively acquiring multiple paths of light intensity detection signals; screening the multipath light intensity detection signals to determine an effective measurement channel in a linear working interval; Based on the preset spatial angle relation of the light intensity detection unit on the polyhedral base, the solar vector is calculated by utilizing the light intensity detection signal combination of the effective measurement channel.
  10. 10. The method of claim 9, wherein said combining solar vectors using the light intensity detection signals of the effective measurement channel comprises: Selecting the light intensity detection units on at least two detection surfaces as a solution pair; Establishing a function analysis model of the solar incidence component angle by utilizing the ratio relation between the difference value and the sum value of the light intensity detection signals of the two light intensity detection units in the solution pair; and calculating projection component angles of solar rays in different projection planes of the polyhedral base based on the function analysis model, and synthesizing to obtain the solar vector.

Description

Large-view-field sun sensor and method for spacecraft Technical Field The application relates to the technical field of light detection, in particular to a large-view-field sun sensor for a spacecraft and a method. Background The sun sensor is a key component in a spacecraft attitude control and navigation subsystem, and mainly determines the direction of a solar vector by measuring the incident angle of solar rays relative to a spacecraft body coordinate system. The sun is used as a reference target, the viewing radius is small, the illumination intensity is high, the relative position is determined, and the sun sensor is widely applied to attitude measurement of various satellites, spacecrafts and other spacecrafts and attitude capture tasks of sailboards. In the existing sun sensor, a digital sun sensor adopting an imaging principle is generally adopted, a front-end optical system of the digital sun sensor mainly comprises a small hole, a slit or a lens group, a rear-end area array photoelectric detector mainly comprises a CCD or CMOS image sensor, and a signal processing circuit is also built. However, the prior art has the following disadvantages in practical application: The prior art adopts a combination mode of a front-end optical system and a rear-end array photoelectric detector, is limited by the geometric characteristics of a planar imaging device and the aperture limitation of the front-end optical system, and the effective measurement view field is generally limited to be within +/-60 degrees, so that the hemispherical space is difficult to cover. In pursuit of a larger field of view, the prior art has had to attempt to introduce a wide angle or fisheye lens system. This forced expansion of the field of view can cause serious optical distortion problems. As the angle of incidence increases, significant morphological distortion and energy maldistribution of the spot projected onto the detector edge area can occur. The optical characteristics of morphological distortion and uneven energy distribution can destroy the premise assumption of a centroid extraction algorithm, so that the angle resolving precision of the edge area of the field of view is greatly reduced, and the requirement of high-precision measurement of the full airspace without blind areas can not be met on the premise of ensuring the high-precision measurement of the full field of view. Therefore, the application aims to solve the technical problems that the existing imaging type sun sensor is limited by the geometrical characteristics of plane imaging and cannot achieve both large-view-field coverage and edge measurement accuracy. Disclosure of Invention The application mainly aims to provide a large-view-field solar sensor for a spacecraft and a method thereof, and aims to solve the problems that the view field range of the existing solar sensor is limited and the edge measurement precision cannot be improved. In order to achieve the above object, the present application provides a large-view-field solar sensor for a spacecraft, including a polyhedral base, the polyhedral base includes: the detection surfaces are arranged on the side edges of the polyhedral base, and each detection surface is obliquely arranged in the same direction of the polyhedral base; The light intensity detection units are arranged on the detection surfaces and are configured to output light intensity signals proportional to the effective coverage area of sunlight on the light intensity detection units. The application finally forms a convex polyhedral base structure through the vertical plane and the detection surface surrounding the periphery of the vertical plane, and the obtuse angle is arranged between the vertical plane and the detection surface, and replaces the wide-angle lens system required by the traditional imaging sensor by combining the effective coverage area of the light intensity detection unit. The polyhedral base divergent structure ensures no structural shielding in a hemispherical view field range of +/-90 degrees or more, replaces lens imaging by utilizing a linear relation of geometric projection areas, eliminates the problems of optical distortion and uneven energy distribution of a wide-angle lens in an edge view field, greatly expands the view field and simultaneously ensures high-precision measurement in the view field range. Further, the polyhedral base further comprises a vertical plane; The detection surfaces are arranged around the edges of the vertical surfaces, and the included angle between each detection surface and the vertical surface is an obtuse angle; the light intensity detection unit is also arranged on the vertical plane. Further, the vertical plane is a regular polygon plane, and the plurality of detection faces are correspondingly connected to edges of the vertical plane. Further, the number of the detection surfaces is more than three, and the three or more detection surfaces are uniformly distributed along the