CN106595708A - Polar ground model track changing earth simulating method based on linear array earth sensor - Google Patents

Abstract

The invention discloses a polar ground model track changing earth simulating method based on a linear array earth sensor. Firstly, the temperature difference of a heat plate and a cold diaphragm in each earth infrared boundary radiation simulating unit is set, accordingly, earth boundary infrared radiation is obtained, and simulation of different postures is achieved by calculating the displacement of a horizontal movement mechanism A, a horizontal movement mechanism B, a horizontal movement mechanism C and a horizontal movement mechanism D. The method has the advantages that the problem about testing of the postures of linear array earth sensors on a satellite under different tracks is simply and effectively solved, the problem that installation is not convenient on the satellite is effectively solved, and meanwhile the purpose of posture measurement checking is achieved.

Description

A kind of polarity ground moding track earth analogy method based on linear array earth sensor

Technical field

The present invention relates to the surface detection technique of spaceborne infrared earth sensor, particularly relates to a kind of quiet suitable for linear array The earth simulator for earth attitude simulation method of state infrared earth sensor, it is suitable for linear array static state infrared earth sensor Attitude measurement when detecting on star.

Background technology

Infrared earth sensor, is the attitude of satellite optical sensor based on earth sensitive for infrared radiation principle, can be used for Spacecraft is relative to spacecraft when the pitching of the local vertical line of the earth, the measurement of roll attitude angle signal, original state to the earth The gesture stability of spacecraft when capture and steady-state operation.

Whether contain mechanical scanning mechanism according to inside infrared earth sensor, scan-type and static two class can be divided into：Wherein Scan-type can be divided into two kinds of conical scanning formula (single circular cone, double cone) and oscillatory scanning formula again, and static state is then divided into linear array dough-making powder Two kinds of battle array.

Wherein in linear array infrared earth sensor, detector is located on the focal plane of optical system, belongs to gazing type structure. When spacecraft runs on space-time on the earth, terrestrial time is observed from spacecraft, obtained equivalent in 4K cold-scarce scapes Individual average bright temperature is about the disk of 220K～240K, edge referred to as the flat round of disk.Spacecraft runs on space-time on the earth, red Outer earth sensor detects the earth of 14 μm～16.25 mu m wavebands in 4 orientation of ground flat round by alignment array infrared detector Infrared energy, determines the azimuth position of alignment array infrared detector accordingly 4 points of flat round, and the geometry according between is closed System, realizes the measurement to the attitude of satellite, obtains the angle of pitch and roll angle of the spacecraft relative to earth local vertical.

Because the in-orbit object of observation of infrared earth sensor is the earth, ground cannot directly carry out checking test.In order to ensure In-orbit is normal, proper use of, and it is inevitable that ground carries out performance test in the face of infrared earth sensor.So design linear array is infrared Earth sensor earth simulator for earth (analog optical signal improves light excitation source), to the survey for matching corresponding infrared earth sensor Try and using needs.

The content of the invention

The purpose of the present invention is exactly to provide a kind of suitable ground detection for linear array static state infrared earth sensor product to use Earth simulator for earth attitude simulation method.

It is described that four 1 Hes of earth border infra-red radiation analogue unit are included based on the polarity topotype of linear array earth sensor System control unit 2.The temperature of the hot plate and cold stop in earth infra-red radiation analogue unit 1 is controlled by system control unit 2 Degree differential mode intends earth border infra-red radiation, carries out the infra-red radiation simulation of earth border, changes in earth infra-red radiation analogue unit 1 Cold stop position simulation multiple orbital attitudes under the earth, so as to realize in linear array infrared earth sensor ground test.

Polarity ground moding track earth analogy method step based on linear array earth sensor is as follows：

1) temperature difference T of earth border infra-red radiation analogue unit hot plate and cold stop is set；

2) ground flat round subtended angle θ when orbit altitude is H is calculated respectively_HHighly it is H with nominal track₀When ground flat round subtended angle θ_H0：

θ (H)=2 × arcsin (6371+40)/(6371+H),

Wherein H represents orbit altitude；

3) calculate the displacement L of translation mechanism A_A：

And manual rotation translation mechanism moves to correspondence scale, wherein P is pitch attitude angle to be simulated, and R is to simulate Roll attitude angle, A₀For the system zero-bit of translation mechanism, f is infra-red radiation mock up flat optical system focal length；

4) calculate the displacement L of translation mechanism B_B：

And manual rotation translation mechanism moves to correspondence scale, B₀For the system zero-bit of translation mechanism；

5) calculate the displacement L of translation mechanism C_C：

And manual rotation translation mechanism moves to correspondence scale, C₀For the system zero-bit of translation mechanism；

6) calculate the displacement L of translation mechanism D_D：

And manual rotation translation mechanism moves to correspondence scale, D₀For the system zero-bit of translation mechanism.

The invention has the advantages that：Simply, efficiently solving linear array earth sensor carries out the appearance under different tracks on star State test problem, efficiently solves the problems, such as inconvenience is installed on star, while also having reached the examination purpose of attitude measurement.

【Description of the drawings】

Fig. 1 is the structure chart of earth simulator for earth of the present invention.

Fig. 2 is analogy method flow chart of the present invention.

【Specific embodiment】

Below by embodiment and accompanying drawing, the present invention is described in further detail.

1st, first have to simulate space earth infra-red radiation；It is by Electric heating and red using the temperature controller control earth The temperature difference of hot plate and cold drawing in external radiation analogue unit is T=26 °.

2nd, the earth sensor orbit altitude that design tests that nominal track is 500 kilometers is 200 kilometers, ground flat round subtended angle point Wei 137.83 ° (500km) and 154.66 ° (200km)；

3rd, the earth simulation at R=-5 ° of P=5 ° of pitch attitude angle and roll attitude angle is carried out, is proposed according in above method Computing formula, show that four translation mechanisms need the scale for moving to be respectively：

The system zero-bit of wherein four translation mechanisms is 12.5mm, and focal length is 32.95mm.

Translation mechanism is adjusted manually to position as above, you can realize the earth simulation of corresponding state.

Embodiment as above its object is to make the common skill of this area only for the technological thought of the explanation present invention Art personnel will appreciate that present disclosure and implement according to this that the scope of this patent is not limited merely to above-mentioned specific embodiment, I.e. all equal changes made according to disclosed spirit or modification, still cover in protection scope of the present invention.

Claims (1)

1. a kind of polarity ground moding track earth analogy method based on linear array earth sensor, described is quick based on the linear array earth The polarity topotype of sensor includes four earth borders infra-red radiation analogue unit (1) and system control unit (2).By system control The temperature difference simulation earth border of the hot plate and cold stop in unit (2) control earth infra-red radiation analogue unit (1) processed is infrared Radiation, carries out the infra-red radiation simulation of earth border, and the cold stop position changed in earth infra-red radiation analogue unit (1) is simulated not With the earth under orbit altitude, so as to realize in linear array infrared earth sensor ground test；It is characterized in that described side Method is comprised the following steps：

1) temperature difference T of earth border infra-red radiation analogue unit hot plate and cold stop is set；

2) ground flat round subtended angle θ when orbit altitude is H is calculated respectively_HHighly it is H with nominal track₀When ground flat round subtended angle θ_H0：

θ (H)=2 × arcsin (6371+40)/(6371+H),

Wherein H represents orbit altitude；

3) calculate the displacement L of translation mechanism A_A：

$L_A=A_0+tan\left(\sqrt{2}\·\left(P-R\right)/2+\left({\mathrm{\θ}}_H-{\mathrm{\θ}}_{H0}\right)/2\right))\·f,$

And manual rotation translation mechanism moves to correspondence scale, wherein P is pitch attitude angle to be simulated, and R is rolling to be simulated Dynamic attitude angle, A₀For the system zero-bit of translation mechanism, f is infra-red radiation mock up flat optical system focal length；

4) calculate the displacement L of translation mechanism B_B：

$L_B=B_0+tan(\sqrt{2}\·(-P-R)/2+({\mathrm{\θ}}_H-{\mathrm{\θ}}_{H0})/2)\·f,$

And manual rotation translation mechanism moves to correspondence scale, B₀For the system zero-bit of translation mechanism；

5) calculate the displacement L of translation mechanism C_C：

$L_C=C_0+tan\left(\sqrt{2}\·\left(-P+R\right)/2+\left({\mathrm{\θ}}_H-{\mathrm{\θ}}_{H0}\right)/2\right))\·f,$

And manual rotation translation mechanism moves to correspondence scale, C₀For the system zero-bit of translation mechanism；

6) calculate the displacement L of translation mechanism D_D：

$L_D=D_0+tan\left(\sqrt{2}\·\left(P+R\right)/2+\left({\mathrm{\θ}}_H-{\mathrm{\θ}}_{H0}\right)/2\right))\·f,$

And manual rotation translation mechanism moves to correspondence scale, D₀For the system zero-bit of translation mechanism.