RU2002133269A

RU2002133269A - METHOD OF REUSABLE LAYING AND DEPLOYMENT IN SPACE OF EXTRA FRAMELESS FRAMELESS DESIGNS OF FLAT OR CONVEX-CONCAVED FORMS, AND SAILING-REFLECTOR SPACE APPAREGEROGO

Info

Publication number: RU2002133269A
Application number: RU2002133269/11A
Authority: RU
Inventors: Олег Александрович Александров (RU); Олег Александрович Александров
Original assignee: Олег Александрович Александров
Priority date: 2002-12-11
Filing date: 2002-12-11
Publication date: 2004-06-20

Claims

1. A method of laying and deploying in space a frameless structure with a rigid and flexible structure, including a frameless structure in the form of a thin film having only a disk-shaped and flat shape with sharply limited dimensions due to limited assembly areas, formed by centrifugal forces and laid by spiral winding to the body of the aircraft, after the aircraft is launched into outer space, the body of the device with the structure is oriented and stabilized using a rocket engine consuming the working fluid and spin the entire apparatus with the construction to an enormous speed dangerous for the structure of the order of several revolutions per second, using an accelerating block of the carrier or rocket engines to counter-rotate, while centrifugal forces rotate the sail by inertia, the moment of which is uncontrollable and quickly decreases by several orders of magnitude as the structure is deployed, the structure can be deployed only once, and the program of traction of the solar sail in acceleration or braking mode consists in a constant orientation control, where the plane of the sail is kept half the orbit of the sail perpendicular to the rays of the sun and the other half in their direction, characterized in that the frameless structure, for example, a solar space sail or film reflector, mesh metal sheet or film solar panel panels, etc. in order to expand geometric shapes, they are rectangular, square, rectangular, triangular, as well as convex-concave in the form of, for example, a paraboloid or a hyperboloid of revolution and other arbitrary shapes, which combine the center of sail construction of the CPU with the center of mass of the CM, and for the purpose of ease of installation flat or cup-shaped convex-concave structures in the form of, for example, paraboloids or hyperboloids of rotation and expanding the possibilities of controlling the process of their deployment and its reliability, the construction fits m helically winding a separate single drum having an outer surface radius R _B and stacking height L _B, mounted in the center of mass rotation-sail plane freeform design, which is provided with a control drive and fix the actuator on the aircraft body, wherein the actuator provides smooth step by step, as it unfolds, adjusts the speed and direction of rotation, as well as the magnitude of the forces (moments of rotation) applied to the drum, thereby providing twisting or braking during structure, thereby providing soft deployment with a constant predetermined speed, as well as the quality, direction and value of centrifugal forces acting on the helix of the frameless structure during deployment, while the counter-rotation of the sail in order to create maximum gyroscopic moment is provided using telescopic rods with adjustable length shoulders carrying masses at their ends and a cable (tape) flywheel of considerable length, at the ends of which loads are secured, for example, electric batteries a ronika or a payload in the form of, for example, residential modules, and solar panels, while the resulting centrifugal forces at the ends of the ropes and rods are used to create artificial gravity if the flight is manned, while after separating the apparatus with the drum on which the frameless structure is laid, from the carrier , in order to stop the random rotation (somersault) and the orientation of the entire apparatus, without the use of propulsion of rocket engines, the drum with the structure not yet opened and the counter-rotation flywheel are spun false sides with the help of drives applying significant torque, while gyroscopic forces and gyroscopic moments of rotation of the drum with the laid construction and the flywheel stop random rotation leading all chaotic tumbling moments and precession moments to a single common axis - the axis of rotation of the drum and flywheel, thereby stabilizing (reassuring) the body of the device in space and only after that they produce the process of target orientation, also without the consumption of rocket fuel using a break in the common axis of rotation max an ovik and a drum with a laid structure, and deploying the structure in space, and laying the frameless structure by wrapping it on a drum from the center of mass (rotation) to the periphery, while on the surface of the structure spiral fold-sleeves are formed (the surface is corrugated) before cutting in which traces of ridges and depressions on an open surface alternate when walking around a circle centered on the axis of the drum, and sections of the surface of the structure adjacent to each ridge are gr ani, and two such faces form an elementary corrugation in the form of two elementary areas with an angle of 2γ between the faces in the cross section perpendicular to the ridge, which are smoothed (flattened) during the opening, while the angle between the faces varies from 0 to

in a flat state, in addition, the centers of gravity of the corrugations of the corrugations G form neutral lines that branch, forming the appearance of more and more branches due to the fact that with increasing distance from the axis of the drum, a large surface area of the structure is laid on its surface, and the faces adjacent to each crest in the laid state they touch each other and at each revolution around the drum they are evenly removed from the axis by the same distance according to the property of the Archimedean spiral, and the laying of frameless film structures, large sizes significantly exceeding the sizes of production areas, in order to reduce the production area of the assembly and create unlimited dimensions of the structure, it is performed according to the cycle: 1P winding - 1H building - 2Winding - 2H building ......... nP winding - nH building, where the building of additional panels is carried out, for example, by gluing, stitching or welding, and their length is commensurate with the size of the space having a radius Rst where the sail is rolled up, and as soon as it is laid (wound) on the drum for example er, the first part of the construction area (the first 1P cycle) is commensurate with the area of the assembly space, for example, the assembly room or stadium, a partial sequential expansion and flattening of the local folds of its peripheral part, wound on the drum and attaching (1 extension) of additional panels is performed the number of which increases with each step, since it is necessary to lay a larger surface of the structure around the circumference, which is also corrugated along the lines of ridges and depressions and with they wind it onto the drum by carrying out 2 windings, having previously applied a system of bending points and lines according to the cutting, after which the building process can be repeated a considerable number of times depending on the given final dimensions of the structure, while the number of winding and gluing processes (cycles) is selected from calculation

P = R _VK / R _ss ,

where P is the number of cycles (building) winding-building;

R _BK is the specified external final radius of the structure;

R _sc - the radius of the space of the assembly shop, and the dimensions of the structure can reach significant sizes Rvk / Rst> 100000, and to increase the reliability of deployment, the frameless structure is laid according to preliminary cutting with the creased and hollow bends, which are formed by the construction of sectors having the bisecting line B tangent to a circle with a radius of the outer surface of the drum stacking R _B, wherein the parallel bisectors at equal distance from each other equal to the width of the drum way and L _B or webs h width construct parallel lines that converge stykuya line joints Ac (line of nodes) with the parallel lines of other neighboring sectors, forming nodes branching U, wherein lines Ls nodes are also tangent to the circumference of the drum laying surface with a radius R _B, wherein the line of crests and troughs alternating determine when traversing circumferential sectors and through the joints, and the segments on the lines between the points U nodes, and connects the cloth according to the present reveal addition if frameless design MY is molded from a sufficiently elastic thin material, and the process of laying-unfolding in space is multiple, then the lines of bisectors B and the lines of joints Ls are built radially emanating from a common point O, and the winding on the drum (laying) is carried out in bulk, observing the uniform radial tension of the spiral arms of the surface a stackable structure when circumambulating, and a restriction on the height of laying on the drum when laying in bulk is provided by supplying the drum with restrictive cheeks (disks) having a diameter of several exceeding the diameter of the structure in the laid state, and if the frameless structure has a sufficiently rigid but elastic structure of the material, for example, a metal mesh, a canvas of hard carbon fibers (carbon web), or film solar panels, the edges of elementary corrugations are articulated along the lines of the “ridges” and “Troughs”, for example with an elastic tape with an adhesive base or by stitching, forming at the same time a kind of hinges, the axis of which passes along the lines of “ridges” and “troughs”, and the radius of the drum r _b p they are selected in such a way as to ensure elastic laying of the spiral arms of the structure without kinks, and if the sections of the bends on the lines of ridges and troughs of the hard edges of the corrugations are made of a material restoring the original shape, then the frameless structure with a rigid structure can be deployed practically without the participation of centrifugal forces, or with weak spin of the drum, and when laying convex-concave surfaces, first the surface is smoothed on a plane until concentric circles appear, Representing a wave and only then produce clotting on the drum.

2. The method according to claim 1, characterized in that the width of the panels h of connecting and building up the structure is equal to the height of the drum R _B , and the connection (gluing) of the panels together and reinforcing with reinforcing materials is made along the lines of ridges and depressions.

3. The method according to claim 1, characterized in that in order to automatically compensate for the light pressure during the operation of the reflectors, the surface opposite to the influence of solar pressure is coated with a layer of the polonium isotope, (alpha emitter) alpha particles, which create a compensating reactive thrust commensurate with light pressure moreover, to compensate for the light pressure in the mode of using the sail as a reflector reflector, the surface opposite to solar radiation is coated with the polonium isotope, while the comp Compensation occurs automatically regardless of the position of the reflector, due to the fact that for any position of the reflector, the bisector of the angle of incidence-reflection of the sun’s ray, it is the thrust vector of solar pressure at any point of the reflector, is always normal to a given part of the reflector’s surface, therefore, on the opposite side, a layer of compensating alpha emitter, the thrust from which is always directed normally from the sail creates compensation for light pressure, at any position of the structure (reflector) to the sun's rays, to the limit x 180 ° with the condition not falling to the side of the sun's rays layer polonium compensating layer when folding occurs vectors rods.

4. The method according to claim 1, characterized in that in order to implement the process of multiple coagulation-deployment deployed in space, a rotating frameless structure made of a thin elastic film, braking forces or even reverse rotation forces are applied to the drum drive, in which the structure, having inertial forces of rotation, rotating around a braked drum starts the process of winding (winding) back onto the drum, while the direction of laying the structure changes to the opposite value, and the speed the rotation of the winding structure as it is wound around the drum increases, however, using the moments and different directions of rotation of the control drive of the drum, they control the laying speed, while after winding and overlapping the last turns of spiral arms (corrugations) onto the drum, the structure is quickly fixed using special fixing devices, and cutting of such a design is performed with radial outgoing from a common central point O, lines of bisectors B and lines of joints (nodes) LS.

5. The device according to claim 1, characterized in that the plane or convex-concave continuous sail-reflector rotating with the help of drives has an external radius rн, a center of symmetry and, accordingly, a center of rotation, with a center of mass of which is fixed to the drum the main static axis of rotation, which is pivotally attached to the static axis of rotation of the counter-rotation flywheel, wherein the hinge is made in the form of a skew assembly, which creates a break in the axis of rotation of the sail and the flywheel by an angle α and, accordingly, change the angle between the axes of the drum and the flywheels ika, while the concentrated efforts of breaking the axis are transmitted to the frameless structure, the sail-reflector, made for example of a thin metallized film, uniformly distributed around a circle with an inner radius Rv located on its plane, through cables, which are two continuous cone-shaped bowls made of for example, from the same film material as the sail-reflector, and the truncated tops of such cones are attached to the ends (cheeks) of the drum, and their bases equal to the inner circle with radius Rv, the sail The a-reflector is mounted between itself and the edge of the inner circle of the reflector sail, while the surface of such film cables is metallized or made of film solar batteries and used as a useful working (reflective or photo converting) area, and counter-rotation of the sail-reflector provides a rotation-driven drive cable flywheel with rigid telescopic shoulders with rods, and the outer ends of the cable flywheels, in order to increase gyroscopic moments at a given length, provide loads, in e power elements, solar panels, appliances, fuel reserves, and payload, for example, in the form of residential modules, in which, simultaneously due to centrifugal forces, artificial gravity is provided (if the device is manned), and the cable functions in the manned version are performed in the form of, for example, gas-filled soft hermetic pipes of the sleeves, which are spirally laid during transportation like a soft fire hose to the central drum, similar to a reflector sail, and equipped with mating rings at the ends For docking with residential modules, the drives for rotating the reflector sail and counter-rotation flywheel are made in the form of electric drives having a stator and rotor, and the torque is transmitted by a gearless circuit directly from the power electromagnetic interaction of the rotor with the stator, and to increase the torque interactions, without the use of a gearbox, strive to create the maximum shoulder L of the torque forces of the electromagnetic interaction of the rotor and stator from the axis of rotation, for which the torus and the stator are placed around a circle with a maximum radius from the axis of rotation, in addition, the stator with the winding is placed on static non-rotating elements of the apparatus and sealed with a casing (shell) of non-magnetic material, with the possibility of thermoregulation of the stator winding, by circulating a heat agent inside the casing shell, while the power electromagnetic interaction of the rotor with the stator is carried out through the walls of the casing, and the surface of the sail-reflector can be made in the form of flat solid forms about a disk, a rectangle, a cross, a star, a triangle of a square, etc., with the center of rotation of the center point at the point O, located in the center of mass of the center center and the center of sail of the center, or thin-film three-dimensional convex-concave forms such as a paraboloid of revolution, and with the aim of high-energy spiral acceleration or deceleration in the vicinity of the planets in the solar sail mode, as well as with the aim of automatically orienting according to a given traction program, using only inertia forces, the developed plane of the reflector sail is twisted around the center of mass along the bp axis making the sail parallel to the plane, with such an angular speed and rotation period, so that passing through the orbit angle of 90 ° with the vertex in the center of the planet, the plane of the sail rotates by inertia by 45 °, or passing through the orbit one full turn, the plane of the sail rotates 180 ° in this case, the plane of the sail with the coincidence of the flight speed vector with the direction of the sun's rays (passing course) should be perpendicular to the rays of the sun, and when moving towards the rays, the plane is turned by an edge towards their direction, respectively, with the direction of the vector speed to incident rays equal to 90 °, the sail plane is rotated 45 °, so the sail plane orientation program has the form of a “herringbone” with the base at that point A of the orbit where the plane is oriented edge to the sun's rays, and if from this point A draw a beam before crossing with any point of the orbit, then at the point of intersection of the beam with the orbit, the plane of the sail should be oriented parallel to the beam, and to compensate for changes in the parameters of the orbit, due to spiral acceleration or deceleration, the rotation period of the sail is relative the axis parallel to its plane is reduced if the sail accelerates, or increased if it is braked according to the law of spiral planetocentric motion of spacecraft with low thrust, in addition, in order to increase thrust during flight of the device in solar sail mode, its reflective working (solar) surface is covered a layer of the polonium isotope (alpha emitter), which creates additional reactive thrust up to 2.6 · 10.5 kgf per square meter, casting alpha particles at a speed of 80,000 km / s away from the sail, while the radiation of alpha particles in the opposite direction is absorbed by the sail material, in addition, to create additional thrust, the sail-reflex apparatus is equipped with an additional (auxiliary) propulsion system with reserves of the working fluid, for example, it is equipped with low-thrust engines by an electric rocket propulsion system (ERE) by attaching to the static elements of the apparatus for example, on the end part of the static axis of a drum with a sail or counter-rotation flywheel, and the power plant is made of solar film Atar representing a thin metal foil coated with amorphous silicon, pasted on the sail surface and partially replacing it e.g. central area and placed in the drum together with the sail.

6. The device according to claim 5, characterized in that the sail plane is continuous until it is attached to the stacking drum, and the cables are made of tapes or threads fixed at one end on the cheeks of the drum and the other end on the surface of the structure on a marked (outlined) conditional circle fastening the cables (cable-stayed ring) on the surface of a frameless structure of radius Rv, and the cable-mounting with the surface of the film structure is made through the ring catenary load balancer from the cable-stayed cables to the inner cable-stayed ring on the surface of the reflector sail.

7. The device according to claim 5, characterized in that the sail plane has an inner empty space within the inner radius Rv, while the cables are attached to its inner edge, and the empty inner space of the reflector sail is filled with an additional plane made in the form of a counter-rotation flywheel, having its own drum for laying similarly to the main sail-reflector, while the projection of the auxiliary film structure on the inner space with a radius Rv of the main sail-reflector fills it, thereby carrying useful functions of the useful area and working mass of the counter-rotation flywheel.

8. The device according to claim 5, characterized in that the period of rotation of the sail around an axis parallel to its plane is changed depending on changes in the parameters of the orbit, during spiral acceleration, the period of rotation of the sail is slowed down, and when braking is increased, using the electronic control system of the traction program, by measuring the angles between the sail plane and the direction to the planet and the sun, consisting of a solar sensor, a vertical sensor of the planet and a gyroscopic sensor of the position of the sail in space, while the signals from the sensors to a logical device (on-board computer), where, according to the given algorithms, the sensor data are processed, which are compared with the position of the sail plane in space and the orbit parameters, adjusting the period of the sail’s own rotation with the apparatus using the executive organs of orientation of the kink of the axis of rotation of the sail and flywheel, while if the angle between the direction to the sun and the direction to the earth is 0 °, the plane of the sail is oriented at 135 ° to the local vertical to the planet, and if the angle to the sun and the planet is 180 °, then the plane The sails should make an angle of 45 ° with the planetary vertical, and accordingly, if the angle of the sun with the planet is 90 °, then the plane is oriented toward the sun's rays at 90 or 180 °, depending on the data of the gyroscopic sensor.

9. The device according to claim 5, characterized in that for the purpose of easy access without spacesuits for repair and access to the stator with a winding, electric rocket motors, the system of the mechanism of fracture of the axis, as well as for temperature control and increase the shoulder of the electromagnetic interaction L, in a manned sail -reflector apparatus, as well as to provide emergency manual power control of the mechanisms of breaking the axes of the drum and flywheel, as well as manual spinning of the drum with a sail and a flywheel, their static axes are made in two, articulated in the central end parts of the inhabited module, moreover, one end part of each module has a convex bottom and the second is concave, while the modules are connected via convex bottoms, while at the junction of the cylindrical part of the modules with a convex end part (bottom) they provide a power ring a hoop to which at least three opposed power rods are attached, which, changing their length, provide swinging relative to the central cardan of the hinge of the longitudinal axes of the modules by an angle α, the modules being connected along the periphery between each other with a hermetic shell in the form of a bellows, while the inner junction of the concave bottoms with cylindrical parts is made of non-magnetic material, and on the inner sealed surface around a circle equal to the diameter of the module, stators with a winding and a thermal control system of windings are attached, and from the center of the longitudinal axis end concave parts come out of a cylindrical pipe tunnel with anti-rotation nodes and pressure bearings equipped with mechanisms of manual manual rotation used in emergency maintenance In this case, the pipes are static axes on which they are mounted, and with respect to which the drum with a sail and the counter-rotation flywheel rotate through the bearings, the end parts of the axle pipes protruding beyond the drum and the flywheel are provided with sealing hermetic elements to which the sealed motor modules are docked, or others inhabited modules, for example, descent vehicles, while film solar panels replace part of the central surface of the reflector sail, and cables and tow cables are attached to the inner to the radius through the catenar, in addition, film solar batteries can be laid together with tubular sleeves by the method of laying the reflector sail on a similar drum and deployed together with the sleeves.

10. The device according to claim 1, characterized in that in order to combine the functions of the flywheel with useful functions, the frameless design is divided into two parts, rotating in different directions, having both the same area and rotation speed and different, while stacking drums and cables can have the same design, while the inner cutout of the main structure is filled with the projection of the area of the auxiliary structure.

11. The method according to claim 1, characterized in that for clamping the rolled structure to the laying drum, as well as for force crimping the surface of the laid structure, to prevent swelling of the turns of the structure when exiting in high vacuum, use a crimp power bandage made in the form of a cloth of durable elastic material, the width of which is equal to the length of the drum (the distance between its cheeks), while the bandage is equipped with a pyrozam, which, when triggered, breaks the bandage, and the centrifugal forces of rotation of the drum cast it far into defense.

12. The method according to claim 1, characterized in that the frameless structure is super-large in size, with slightly pronounced parabolicity and a focal length of hundreds of kilometers, is used to concentrate narrow solar temperature or electronic effects on distant objects, for example, on the surface of the earth.