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Simulation method of Mars object for deep space exploration

A technology for deep space exploration and target simulation, which is applied to the simulation device of space navigation conditions, space navigation equipment, transportation and packaging, etc., and can solve the problems that Mars body simulation has not yet appeared in engineering practice.

Inactive Publication Date: 2017-04-26
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The current star simulation technology mainly focuses on the simulation of star image points, and there are no examples of engineering practice in the simulation of Mars itself

Method used

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  • Simulation method of Mars object for deep space exploration
  • Simulation method of Mars object for deep space exploration
  • Simulation method of Mars object for deep space exploration

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specific Embodiment approach 1

[0025] Specific implementation mode one: the Mars target simulation method for deep space exploration of the present implementation mode, such as figure 1 As shown, it includes Mars coordinate simulation step SA, Mars imaging size simulation step SB, Mars imaging contour simulation step SC, Mars imaging orientation simulation step SD and Mars imaging grayscale simulation step SE: among them,

[0026] The Mars coordinate simulation step SA is used to transform the center coordinates of Mars from the heliocentric ecliptic coordinate system to the display plane coordinate system.

[0027] The Mars imaging size simulation step SB is used to calculate the imaging size of Mars according to the imaging field of view of the Mars probe and the relative distance relationship between Mars and the Mars probe.

[0028] The Mars imaging profile simulation step SC is used to simulate the areas of Mars illuminated by the sun and the areas not illuminated by the sun.

[0029] The Mars imaging...

specific Embodiment approach 2

[0039] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that the method further includes a preprocessing step performed before each step, and the preprocessing step is specifically:

[0040] The parameters in each data item in the SKY2000 star catalog are deleted, and only the parameter information of the star's right ascension, declination, and magnitude of each data item under J2000 is retained, and all data items are as large as Small to arrange.

[0041] figure 2 It is a schematic diagram of SKY2000 simplified star catalog.

[0042] Such as figure 2As shown in the figure, a star catalog is a file in astronomy that records information about stars, positions, and magnitudes. The present invention uses the SKY2000 star catalog, and deletes the star catalog, only retains the magnitude within the range that can be recognized by the human eye, including three parameter information of the right ascension, declination, and magnitude o...

specific Embodiment approach 3

[0044] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is:

[0045] The Mars coordinate simulation steps include:

[0046] Step A1: Determine the center coordinate boresight of the Mars rover.

[0047] Step A2: Convert the attitude quaternion used to describe the Mars rover into the right ascension and declination of the boresight.

[0048] Step A3: Convert the Mars coordinates and the Mars rover coordinates of the heliocentric ecliptic coordinate system under the star catalog into coordinates under the attitude sensor coordinate system.

[0049] Step A4: Determine the center coordinates of Mars in the display plane coordinate system and the projector coordinate system.

[0050] Specifically, the method for determining the visual axis in step A1 and the determination method for the expressions of right ascension and declination of the visual axis in step A2 are:

[0051] The present invention assumes that the attitude sen...

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Abstract

The invention relates to a simulation method of a Mars object for deep space exploration, which belongs to the field of deep space exploration application. In order to solve the problems in the prior art of lacking of a method for simulating the location, size, contour, imaging orientation and imaging gray level of Mars and existing technical gaps in engineering practices, the simulation method of the Mars object for deep space exploration is proposed. The simulation method includes transforming a center coordinate of Mars from a heliocentric ecliptic coordinate system to a display plane coordinate system and a projector coordinate system, calculating an imaging size of Mars according to an imaging field of view of a Mars explorer and the relative distance between Mars and the Mars explorer, simulating illuminated areas of Mars which are illuminated by the sun and unilluminated areas which are not illuminated by the sun, calculating an imaging orientation of the contour of Mars according to the relation of relative positions among the sun, Mars and the Mars explorer, and mapping a magnitude of Mars to the gray level of a computer to display on an interface. The simulation method of the Mars object for deep space exploration is applicable to the simulation software of deep space exploration.

Description

technical field [0001] The invention relates to a method for simulating a Mars target for deep space exploration, belonging to the application field of deep space exploration. Background technique [0002] The cost of the Mars rover is extremely expensive, and it takes a lot of manpower and material resources to improve the accuracy of the Mars rover and reduce the failure of the Mars rover has become an inevitable requirement. However, it is unrealistic for the attitude sensor of the Mars rover to capture the actual starry sky in real time, and it is expensive, and it is difficult to achieve real-time and dynamic performance, which puts forward requirements for Mars target simulation. [0003] In space target simulation, the mainstream technology used is the dynamic star simulator. The working principle of the dynamic star simulator is: according to the received star attitude angle and orbital position output by the simulation computer, the direction corresponding to the o...

Claims

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Application Information

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IPC IPC(8): B64G7/00
CPCB64G7/00
Inventor 王骢丁明理韦双余陈玉明宋旭伟张永强李贤杨光磊
Owner HARBIN INST OF TECH
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