Novel imaging method in agile satellite maneuvering

A satellite and imaging technology, applied in special data processing applications, measuring devices, instruments, etc., can solve the problems that satellites cannot achieve pointing, cannot meet, and cannot meet the imaging pointing requirements during maneuvering

Active Publication Date: 2014-08-13
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

[0005] In the process of maneuvering imaging, it is necessary to control the three-axis attitude angle of the satellite to point to the ground trajectory planning target. In the existing imaging mode, except for the yaw angle control, the nominal value of the roll angle and pitch angle of the satellite is zero, and the satellite cannot Realize the pointing

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  • Novel imaging method in agile satellite maneuvering
  • Novel imaging method in agile satellite maneuvering
  • Novel imaging method in agile satellite maneuvering

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Embodiment Construction

[0035] Such as figure 1 As shown, the present invention provides a method for imaging in agile satellite maneuvers, the steps are as follows:

[0036] (1) set up the model of satellite and on-star sensor in simulation tool, set up satellite attitude and on-star sensor parameter; Described on-star sensor adopts TDICCD; Wherein, TDICCD is linear array time delay integral CCD; Described simulation tool is Satellite Toolkit STK.

[0037] In this step, STK is used as a simulation tool. Open the STK software, create a new satellite, and input orbital parameters, including epoch time, semi-major axis, eccentricity, orbital inclination, perigee depression angle, ascending node accuracy, and mean anomaly angle. The HPOP disturbance model of the earth is selected as the derivation model of the satellite orbit, and EOPv1.1 is selected as the pointing parameter of the earth model. Create a new sensor on the satellite, and set the field of view of the sensor according to the field of vi...

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Abstract

The invention relates to a novel imaging method in agile satellite maneuvering, which is capable of realizing imaging of satellite during a posture adjustment process. The method comprises the following steps: according to geographic latitude and longitude of on-board orbit forecast data and imaging object point, a triaxial attitude angle directional target imaging start point of satellite is arranged; a roll angle and a pitch angle are obtained through a modeling algorithm for determining the satellite optical axis directional target imaging point; establishing a CCD image plane in a satellite model, performing calculation to obtain image motion velocity vector and a drift angle through projection calculating, and yaw angle of the satellite is controlled for correcting the drift angle, calculating the image motion velocity vector to obtain TDICCD integration time for image motion compensation, and satisfying the image processing requirement of imaging in maneuvering. The design method is capable of using in a triaxial attitude maneuvering process of the satellite for starting optical payload for a dynamic imaging technology for imaging, so that target directional requirement and image processing requirement during an imaging process can be realized.

Description

technical field [0001] The invention relates to a novel imaging method during maneuvering of an agile satellite. Background technique [0002] In order to meet the needs of increasing the imaging width, realizing real-time observation of emergency areas, and realizing three-dimensional imaging on the same track, all countries in the world are vigorously developing agile satellites, and put forward strict requirements for the agile attitude maneuverability of satellites, requiring them to have Rapid attitude maneuver and rapid stabilization capability. However, the current requirement for the attitude control system of agile satellites is the need for an actuator that can provide a large output torque to achieve large-angle rapid attitude maneuverability. However, there are no specific index requirements and implementation methods for the satellite's high-precision angular velocity measurement capability and attitude control stability during maneuvering, so it is impossible ...

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Application Information

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IPC IPC(8): G01C11/02G06F19/00G01C25/00
CPCG01C11/00
Inventor 黄群东杨芳赵键
Owner AEROSPACE DONGFANGHONG SATELLITE
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