RU2089467C1 - Space vehicle light protection device - Google Patents

Abstract

FIELD: space engineering; protection of optical and electronic devices against external thermal and light flows. SUBSTANCE: device includes load-bearing frame and doors. Load-bearing frame holds electric drive kinematically linked with additional cover articulated on frame and provided with movable side doors equipped with opening mechanism. EFFECT: enhanced efficiency. 5 dwg

Description

 The invention relates to the space industry and serves to protect optoelectronic devices from external heat and light fluxes.

 Known optical hood, consisting of a housing and flat internal diaphragms mounted perpendicular to the longitudinal axis of the hood.

 The disadvantage of this lens hood is that when working in space it does not protect the optical system from background thermal influences, and also does not create conditions (a closed, opaque object) for focusing the optical system.

Known sun shade hood, consisting of a housing and diaphragms, which are made in the form of box surfaces of a truncated cone, the generatrix of which is with an extreme illumination beam for each diaphragm an angle in the range of 80 110 ^o .

 The disadvantage of this design is that when working in space, the lens hood does not protect the optical equipment from background heat and light fluxes, the effect of which leads to an optical system mismatch.

 When working in space as a result of exposure to heat fluxes, the lens mirror changes its geometric parameters relative to the nominal ones by approximately 1.5 2 angular minutes. This introduces errors in determining the coordinates of the photographed object (up to several tens of meters). To eliminate this drawback, optical compensators are used, with the help of which the magnitude of the deviation of the optical beam from the initial position is determined under real operating conditions before each photographing session.

 At the receiver, the angular and linear displacement (mismatch) of the light beam relative to the source is measured. The computer remembers this information and takes it into account when processing the results of photographing.

 The aim of the invention is to increase the accuracy of determining the coordinates of the photographed object by reducing the influence of the external radiant flux on the geometric parameters of the optical system.

 To achieve this, an electric drive is installed on the power frame of the light-shielding device, kinematically connected with an additional cover pivotally mounted on the frame with movable side flaps equipped with an opening mechanism.

 In FIG. 1 5 shows a light-protective device (SZU) of a spacecraft (SC).

 A power frame 2 is mounted on the spacecraft body (see Fig. 1), on which an electromechanical actuator 3 is mounted. Using kinematic links 4, the actuator 3 is connected to an additional cover 5, on which the side flaps are pivotally mounted 6. Mechanisms are mounted on the side flaps 6 disclosure 7 (see Fig. 5).

 In the folded position, structural elements must be placed in the area between the optical mirror 8 (see Fig. 1) and the drop hood 9. The mirror 8 is installed in a two-stage cardan 10 (see Fig. 2), which allows it to rotate relative to two mutually perpendicular axes.

 Light protection device operates as follows. After the SC is put into orbit, the shutters of the hood 9 (see Fig. 1) are opened and fixed. The optical system is turned on. Mirror 8 (see Fig. 3) rotates to the "F" position (focusing). The cover 5 and the side flaps 6 are in the "Closed" position and protect the mirror 8 and the optical systems from the background radiation of the Sun and the heat flux reflected from the Earth. The signal "C" generated by the optical system, reflected from the mirror 8 ("F"), is returned to the receiver of the optical system. The magnitude of the signal mismatch (angular and linear) the computer remembers and takes into account when processing information to determine the coordinates of the photographed object. A command is issued to the electromechanical drive 3 (see Fig. 4). Using the kinematic links 4 (rods and levers), the cover 5 is rotated to the "Open" position. Side flaps 6 using the opening mechanism 7 (see Fig. 5) synchronously with the cover 5 opens and locks in a position equidistant to the open flaps of the hood 9, freeing up the "Viewing Area" (see Fig. 4). A shooting session is being taken. The electromechanical actuator 3 transfers the cover 5 with synchronously rotating shutters 6 to the "Closed" position (see Fig. 3). Before the next session, the focus-shoot cycle is repeated.

 The folding hood 9 (see Fig. 1) is designed to protect the optical system of the spacecraft from the rays of the sun at various positions of the spacecraft relative to the sun.

 Reducing the influence of the intensity of radiant heat transfer when focusing the optical system of the spacecraft can improve the accuracy of determining the coordinates of the object and allows you to create products that are competitive in the world market.

Claims (1)

 A light-protective device of the spacecraft, consisting of a power frame and wings, characterized in that an electric drive is installed on the power frame kinematically connected with an additional cover pivotally mounted on the frame with movable side wings equipped with an opening mechanism.

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