Measurement method of stand-alone pointing accuracy in satellite simulated zero-gravity state

A technology of pointing accuracy and satellite simulation, which is applied in the field of satellite measurement, can solve the problems of not considering the change of installation accuracy, etc., and achieve the effect of simple implementation process and elimination of the influence of gravity factors

Active Publication Date: 2017-12-15
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0004] (1) The installation accuracy change caused by the gravity deformation of the structure itself is not considered;
[0005] (2) Changes in installation accuracy caused by assembly stress are not considered

Method used

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  • Measurement method of stand-alone pointing accuracy in satellite simulated zero-gravity state

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Embodiment Construction

[0028] The embodiments of the present invention are described in detail below. This embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation manners and specific operation procedures are given, but the protection scope of the present invention is not limited to the following embodiments.

[0029] figure 1 This is the implementation process of the present invention, and the specific steps are as follows:

[0030] (1) The satellite is in a fixed support state, which is marked as "state one";

[0031] Specifically, the satellite can be placed on a two-axis turntable through a parking tool, and the support can be tightened with fasteners. It should be ensured that the satellite is in a stable state during the measurement process without overall movement.

[0032] (2) Two reference theodolites respectively collimate the satellite reference prisms;

[0033] Specifically, the reference prism used as the reference for the satellite...

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Abstract

The invention discloses a method for measuring single machine pointing accuracy of a satellite in a simulated zero-gravity state. The method comprises the following steps: keeping a satellite in a clamped state, and marking the state as 'state I'; respectively collimating a satellite reference prism by two reference theodolite; aligning the two reference theodolite to each other; respectively collimating two tested surfaces of a single machine prism by two single machine theodolite; respectively aligning the two single machine theodolite to the reference theodolite; calculating to obtain vector representation of a single machine in a reference coordinate system in X, Y and Z directions; inverting the satellite for 180 degrees relative to an original state, and marking the state as 'state II'; repeating the steps; calculating to obtain vector representation of the single machine in the reference coordinate system in X, Y and Z directions; and performing vector summation on spatial vectors measured in the 'state I' and the 'state II'. By adopting the method, the influence of gravity factors can be theoretically substantially eliminated, and the single machine mounting precision of the satellite in an on-orbit zero-gravity state obtained by the method is more accurate than that obtained by a conventional measuring method.

Description

Technical field [0001] The invention relates to the technical field of satellite measurement, in particular, to a method for measuring the pointing accuracy of a satellite in a simulated zero gravity state. Background technique [0002] With the development of high-orbit, high-resolution remote sensing satellites, higher installation and measurement requirements are put forward for the pointing accuracy of a single satellite on the satellite. At present, ground accuracy measurements are all carried out in a gravitational environment. Due to the weight of the satellite structure and the gravity of a single aircraft on board, the difference in the installation accuracy of a single aircraft measured in a ground gravity environment relative to the zero gravity state of the satellite in orbit will reach angular classification. [0003] In order to overcome the influence of gravitational factors to a certain extent, in the current satellite development process, the accuracy measurement r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C1/00
CPCG01C1/02
Inventor 陶炯鸣周徐斌苏若斌孔祥森赵川胡梦遥
Owner SHANGHAI SATELLITE ENG INST
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