In active remote sensing

electrooptical countermeasures

wireless optical remote transmitting and so on

the space-borne laser source carried by a space vehicle is indispensable

the function is unique

powerful and irreplaceable. For accomplishing the intended result in astronautical engineering or in aeronautical engineering

it is necessary to make the intended aim

whose size is finite

be irradiated by laser beam emitting from a right space-borne laser source

and the energy density of the laser beam that irradiates the aim must be enough high. Phase-locked laser diode array is small in size and light in weight

it is quite fit for performing the function of high power space-borne laser whose size must be exigent proper. Meanwhile

in space

the space thermal environment will be influenced by star

planet and space heat sink

a space vehicle is heated and cooled by turns

the change in temperature is violent

to avoid being damaged in space

in this paper

a phase-locked laser diode array who acts as the space-borne laser source in a space vehicle is placed inside the space capsule

only is reflected by the extravehicular reflecting mirrors

the laser beam that emits from the phase-locked laser diode array can pass through the outgoing mirror of the space-borne laser source

and then can transmit into space

the structure of the whole space-borne laser source is periscopic

even so

induced by the varied surrounding space thermal environment

and aggravated by the laser beam that the extravehicular reflecting mirror's reflect

the extravehicular reflecting mirrors will deform stochastically

so the output energy of the space-borne laser source is diverged

at the same time

the normal line of each reflecting mirror surface turns due to the reflecting mirror thermal distortion

so corresponding transferred laser beam has a large deflect

therefore the energy density of the laser beam that can be transmitted to the intended aim and then can treat the aim to be detracted greatly

the performance of the space-borne phase-locked laser diode array will suffer seriously. By way of theoretical derivation

finite element analysis and pertinent experiment

this paper presents clear ideas on the configuration of the space-borne laser source whose emitter is just a phase-locked laser diode array

on characteristics of the space thermal environment that can impact the extravehicular reflecting mirrors

on the optoelectrical field distribution of the phase-locked laser diode array who irradiates the extravehicular reflecting mirrors. Then it makes the laws that govern the action of the deformation of the extravehicular reflecting mirror clear. After that

the novel predistortion technology is presented. To perform the proposed technology in the proposed periscopic space-borne laser source

firstly

the wavefront error induced by the deformation of the extravehicular reflecting mirrors is sensed by the special sensing probe by means of the special echo wave method

after processed by the special processor

the controlled quantity for compensating the outgrowth of the deformation of the extravehicular reflecting mirrors can be obtained

with suitable D/A

high voltage amplifier

the actuating mechanism makes the additive reflecting mirror inside the capsule shape correctly in time

so with right predistortion

after it to be done by the additive reflecting mirror

the laser beam that will be reflected by the extravehicular reflecting mirrors won't be deteriorated by the deformation of the extravehicular reflecting mirror

the experiment demonstrates that the proposed technology makes a space-borne laser diode array adapts to the space thermal environment

guarantees the quality of its output laser beam

this is significant for that laser diode array should be employed in space.