RU2554901C2 - Device for unfolding of spacecraft flat large-size structures - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to airspace engineering and can be used for one-time unfolding of spacecraft large-size structures, for example, radar antennas, solar batteries, etc. Device comprises fixed section (2) (FS) arranged at frame (1) secured at spacecraft and rotary sections (5) (RS), rotary assemblies with brackets (7), main and doubling spring-type drives (SD). The latter are arranged at FS (2). SD springs are arranged in tubular cases (16) to interact with cables (18). There are retainer of RS working position including adjustable stops (32), hooks (30) and latches (not shown), pressure retainers, ball locks, contact pickups CP, etc. With RS (5) released by the action of main SD start unfolding. At standard unfolding of sections said CP feed the device operation signal to spacecraft control system. At no signal from CP, doubling SD are operated to actuate the device. Distance (L) from rotational axes of SS to those of support rollers (21) and that from rotational axes of SS to grooves in bracket (7) are selected subject to total resistance moment of every SS and to total initial and final forces of SS springs.

EFFECT: simplified design and higher reliability.

10 dwg

Description

The invention relates to space technology and is intended for a one-time disclosure of large-sized flat structures of a spacecraft (SC), for example, radar antennas (RLA), solar batteries (BS), etc.

It is known that in devices of one-time disclosure of structures using a spring drive, dynamic loads arise at the moment of shutdown of the disclosed link.

The reason for their occurrence is that the components of the total moment of resistance to opening ΣMsopr. (from the inertial forces, from the friction forces in the rotation nodes, from the resistance forces of the electric cables of the links, etc.) have, basically, a constant value at the entire opening angle of the links φ, i.e. ΣMsop.nach. = ΣMsopr. End, and the spring drive has a “falling” characteristic Mp.sp. = F (φ), i.e. the initial moment of the spring drive more than the moment at the end of the expansion of the links Mp.con, in addition, the condition Mp.con.> Σ Msopr. must be met in order to ensure the retention (fixation) of the opened link in the final position.

The difference between the energy of the spring drive and the work necessary to overcome the resistance to opening, goes to the acceleration of the disclosed link, the angular velocity of which at the time of its stop reaches its maximum value.

To eliminate the negative impact of dynamic loads on the structure, there are two ways: either increase the rigidity of the structure (mass), or reduce the level of loads to an acceptable value.

In space technology, there are strict mass restrictions, so the effect of large dynamic loads can lead to deformations or destruction of structural elements, which ultimately reduces the reliability of the spacecraft.

It is known that the “Device for opening the links of onboard systems of spacecraft” according to the patent for invention RU No. 2424952, comprising a fixed link fixed to the spacecraft and pivotally connected to the spring-loaded bracket of the opening link fixed to the spacecraft in the initial position, the bracket of the open link is spring-loaded with a torsion spring, which is connected with a spacecraft by means of a tension regulator, the gear rims of which interact with a gear sector made on an axis rigidly connected to a fixed link, moreover, on the the braking unit, the spring-loaded rod of which interacts with the contactor pivotally mounted on the support sleeve mounted in the grooves of the bracket of the open link, the contactor also interacts with the surface of the cam sleeve made with a variable radius, and at the end of the rotation of the open link with a recess in the cam sleeve mounted in the grooves of the axis, wherein the support sleeve and cam sleeve have struts cooperating with the fastening elements.

In the described device, a decrease in the level of dynamic loads on the open link is achieved due to the fact that the characteristic ΣMsop. = F (φ) of the total moment of resistance of the spring drive is adjusted to the equidistant disposable characteristic of the spring drive Mp.sp. = F (φ) with a minimum difference between the energy of the spring drive and work of resistance forces.

The device has the following disadvantages:

- a method of reducing dynamic loads on the disclosed link is complicated, because requires the manufacture of a special profiled cam;

- the absence of duplication of the torsion spring, breaking the spring leads to a failure of the device;

- possible instability of the coefficient of friction in the pair "sleeve-cam contactor", while with an increase in the friction force, the opening of the link may stop, with a decrease - acceleration;

- when fixing the disclosed link due to the interaction of the contactor with the recess in the cam sleeve when opening large spacecraft flat structures, for example, radar, it is difficult to provide a strict requirement for the planes of the working surfaces of the fixed and moving sections of the radar to coincide after it is opened;

- the concentration of torque in one place can cause undesirable additional loads when using the device for opening flat large-sized structures;

All of these shortcomings ultimately lead to a complication of the design and a decrease in the reliability of the device, and hence the spacecraft as a whole.

The objectives of the present invention are to simplify the design and increase the reliability of the spacecraft.

The problems are solved by the fact that in the inventive device for the disclosure of flat large-sized structures of the spacecraft "(hereinafter referred to as the" Device "), comprising a fixed section (NS) mounted on a frame mounted on a spacecraft, rotary sections (PS) articulated with it, rotation units , spring drives, while spring drives (PP) and newly introduced backup spring drives (DPP) by means of brackets are mounted respectively on the periphery of the PS and NS symmetrically with respect to the axis of rotation of the PS, the drive springs are placed in pipes housings and interact on the one hand with the covers of these cases, on the other hand, with cables through pistons equipped with cable tension regulators, and the cables themselves interact with support rollers mounted on the NS and PS below the junction plane of the sections and symmetrically with respect to the axis of rotation of the PS, and with grooves made in the brackets of the rotation nodes belonging to the PS, the axis of rotation of the PS lying in the junction planes of the sections, the distance from the axis of rotation of the PS to the axes of the support rollers L and from the axis of rotation of the PS to the grooves in the brackets r is defined Depending on the dependencies:

where Σ - the total moment of resistance to the disclosure of each of the PS;

ΣFstart., ΣFend. - the total initial and final forces of the springs installed in the OPP (ΣFnach. and ΣFend. springs installed in the DPP are the same as the forces of the springs installed in the OPP);

R is the radius of the support rollers;

in addition, in the brackets of the rotation units belonging to the PS, eccentricity is established with respect to the axis of rotation of the PS of the sleeve, interacting with the shafts of the rotation nodes, and the DPP is equipped with locking mechanisms that are rigidly fixed to the frame and the levers of different arms which at one end interact with the pistons and the other with the rods of the tricks of the locking mechanisms, the clamps-clamps are also installed on the frame, while the spring-loaded rotary latches installed in the clamps-clamps interact with hooks fixed to onshteynah mounted on the non-working surfaces of PS in PS mass center areas being on bracket also has adjustable stops, interacting with rods-actuators which are mounted in the clamps-holder, equipped with ball locks and contact sensors;

The design of the device is shown in the drawings.

Figure 1 - General view of the device;

Figure 2 - View A in figure 1;

Figure 3 - Callout B in figure 1;

Figure 4 - Callout In figure 1;

Figure 5 - Callout G in figure 1;

6 - Callout D in figure 1;

Fig.7 - View W in Fig.5;

Fig. 8 - Callout And in Fig. 3;

Fig.9 - View K in Fig.8;

Figure 10 - Callout E in figure 1;

The device contains mounted on a frame 1, mounted on a spacecraft, NS 2, pivotally connected to it (at the stages of assembly, transportation and launch of the spacecraft into orbit) by communication nodes 3 (conditionally shown) PS 4, 5, rotation nodes 6, including supporting brackets 7 belonging to HC 2, shafts 8, bearings 9 and brackets 10 with grooves 11 made therein, belonging to rotary sections 4, 5, PP 12 and DPP 13, by means of brackets 14 are mounted respectively on the periphery of the PS and HC symmetrically with respect to the axis of rotation PS, the springs of the actuators 15 are placed in a tube casing 16 and interact on the one hand with the covers 17 of these cases, providing adjustment of the initial efforts of the springs 15, on the other hand, with the cables 18 by means of pistons 19, equipped with nuts-regulators 20 of the tension of the cables 18, and the cables 18 themselves interact with the support rollers 21, installed on the NS and PS below the plane of the junction of the sections and symmetrically with respect to the axis of rotation of the PS, and with grooves 11, while the axis of rotation of the PS 4, 5 lie in the planes of the junction of the sections, and the distances from the axis of rotation of the PS to the axes of the support rollers 21 (L) and from the axes of rotation of the PS to the grooves 1 1 in brackets 10 (r) are determined by the dependencies:

where Σ - the total moment of resistance to the disclosure of each of the PS;

ΣFstart., ΣFend. - the total initial and final forces of the springs installed in the OPP (ΣFnach. and ΣFend. springs installed in the DPP are the same as the forces of the springs installed in the OPP);

R is the radius of the support rollers;

the brackets 10 of the rotation nodes 6 contain bushings 21 mounted with an eccentricity ε relative to the axes of rotation of the PS, which interact with the shafts 8;

DPP 13 is equipped with locking mechanisms 23, including brackets 24 attached to the frame 1, pyrochecks 25 and pivotally mounted on brackets 24 different spring loaded levers 26 interacting at one end with the pistons 19, the other - with rods 25, while in the mechanisms installation of technological stops 27 is provided; clamps-clamps 28 are fixed on the frame 1, spring-loaded rotary latches 29 of which interact with hooks 30 mounted on brackets 31 mounted on non-working surfaces of PS 4,5 in the areas of PS center of mass, and adjustable brackets 32 are also placed on brackets 31, interacting with actuator rods 33, which are installed in clamps-clamps 28, equipped with springs 34, 35, 36, stops 37, stops 38, pistons 39 with rods 40, clamps 41, ball locks 42 and contact sensors 43,

The operation of the device is as follows:

upon command from the spacecraft control system, the communication nodes 3 are triggered and under the action of the springs 15 included in the PP 12, the rotary sections 4,5 begin to open; at the final stage of opening, the adjustable stops 32 and hooks 30 interact with the actuator rods 33 and the spring-loaded latches 29 of the clamps-clamps 28, respectively, while the actuator rods 33 compress the springs 34, open the ball locks 42 and become on the stops 37, and the latches 29, turning, they engage with the hooks 30 and after the ball locks 42 are activated, the adjustable stops 32 are pressed by the springs 35 to the locked rod-actuators 33 and at the same time interact with the contact pistons 39, rods 40 and clamps 41 and sensors 43, which issue to the spacecraft control system a signal about the operation of the device;

in the absence of a signal from the contact sensors 43, the spacecraft control system issues a command to activate pirochki 25 of the locking mechanisms 23, when triggered, the different levers 26, which disengage from the pistons 19 of the DPP 13, are released, and the device is actuated by the springs of the actuators 15 included in the composition of the DPP 13.

Thus, simplifying the design and increasing the reliability of the spacecraft is achieved:

an exception to the design difficult to manufacture special profiled cam;

installation of duplicate spring drives in the device, which are triggered by a command from the spacecraft control system in case of failure of the spring drives;

a decrease in the dynamic loads on the PS, without the manufacture of a special profiled cam, due to the constructive implementation of the increase in the radius of action of the actuator springs from the value r to the value (L + R), at which, at the entire opening angle, the total moment from the drives remains almost constant and only slightly larger than the total moment of resistance to disclosure;

ensuring strict correspondence of the planes of the working surfaces of the PS and NS in the working position of the device due to the fact that during the assembly of the device the position of the bushings installed with an eccentricity relative to the shafts in the brackets of the nodes of rotation of the PS and adjustable stops installed in the centers of mass of the PS and interacting with clamps-clamps mounted on the frame;

the exception of the concentration of torque in one place by fixing the PP and the DPP by means of brackets on the periphery of the PS and NS symmetrically with respect to the axis of rotation of the PS;

the installation of locking mechanisms on the frame and the use of low power squibs in the locking mechanisms (due to different levers), which reduces the level of shock load on the equipment, for example, radar elements installed on the NS and PS.

the installation of technological stoppers, allowing for the implementation of fire safety rules to transport the spacecraft to the launch site without installing pyromedicines in the device.

Claims (1)

A device for opening flat large-sized structures of a spacecraft, comprising a fixed section (PS) mounted on a frame fixed to the spacecraft, rotary sections (PS) articulated thereto, rotation units, spring drives, characterized in that the spring drives and newly introduced duplicate ones spring drives (DPP) by means of brackets are mounted respectively on the periphery of the PS and NS symmetrically with respect to the axis of rotation of the PS, the actuator springs are placed in tubular housings, interact with one the sides with the covers of these cases, and on the other, with the cables by means of pistons and equipped with cable tension regulators, and the cables themselves interact with the support rollers mounted on the NS and PS below the junction plane of these sections and symmetrically with respect to the axis of rotation of the PS, and with grooves, made in the brackets of rotation nodes belonging to the PS, and the PS rotation axes lie in the junction planes of the sections, the distances L - from the PS rotation axes to the axes of the support rollers - and r - from the PS rotation axes to the grooves in the brackets - are determined from the conditions:

;

,
where Σ Mcoпp. - the total moment of resistance to the disclosure of each of the PS;
Σ Fstart., Σ Fend. - the total initial and final forces of the springs installed in the spring drives (the same with the spring forces Σ Fach. and Σ Finch. installed in the DPP);
R is the radius of the support rollers;
in addition, in the brackets of the rotation nodes belonging to the PS, eccentricity is established with respect to the axis of rotation of the PS of the sleeve, interacting with the shafts of the rotation nodes, and the DPP is equipped with locking mechanisms that are rigidly fixed to the frame, and the different levers of which interact at one end with the pistons and the other - with the rods of the tricks of the locking mechanisms, the clamps-clamps are also installed on the frame, while the spring-loaded rotary latches installed in the clamps-clamps interact with the hooks fixed to the brackets mounted on the inoperative surfaces of the substation in the areas of the centers of mass of the substation, and the brackets also have adjustable stops that interact with the actuator rods, which are installed in the clamps-clamps equipped with ball locks and contact sensors.

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