RU2269460C2 - Solar sailing craft - Google Patents

Abstract

FIELD: spacecraft engine systems; construction of solar sails.

SUBSTANCE: proposed craft has hull, main and additional circular reflecting surfaces, units for forming such surfaces provided with twisting devices and control units for orientation of these surfaces. Orientation control units are made on base of gimbal mounts brought-out beyond craft hull. Each twisting device is made in form of hoop mounted on outer frame of gimbal mount for free rotation; it is engageable with electric motor. Units for forming reflecting surfaces are made in form of pneumatic systems with concentric pneumatic chambers and radial struts. Said struts are provided with flexible tubes with valves mounted at equal distances. Valves have holes. Built on said tubes are pneumatic cells in form of torus or spheres. Each pneumatic system is mounted on respective hoop and is communicated with compressed gas source through concentric hermetic groove found in hoop and in outer frame of gimbal mount.

EFFECT: reduced responsiveness of solar sail control; possibility of deploying solar sail according to preset program; reduction of mass per unit of surface.

4 cl, 11 dwg

Description

The invention relates to space technology, specifically to the construction of a solar sailing ship (SEC), used to control the movement of solar light pressure. In addition, SPK can be used as a reflector for illuminating ground objects at night.

The essence of the invention lies in the fact that the SEC contains the main and additional sails of a ring shape. They are mounted on gimbal suspensions. The additional sail acts as a compensator for the kinetic moment of the main sail. By controlling the relative angular speed of rotation of the additional sail, orientation is achieved relative to the longitudinal axis of the ship. Orientation relative to the transverse axes is achieved due to the procession of the system when changing the orientation of the additional sail mounted on the gimbal.

The invention relates to the use of solar energy to ensure the movement of a spacecraft (SC) using a solar sail, perceiving light pressure.

Known spacecraft with a solar sail, comprising a hull, a flexible surface, a means of its formation, including a spin device and a means of controlling the orientation of the flexible reflective surface [1]. The design of the spacecraft, taken as an analogue, is ineffective due to the loss of the effective area of the sail and an increase in the specific gravity of the SEC per unit surface area.

The closest known technical solutions is a spacecraft with a solar sail [2], which can be specified as a prototype.

The prototype contains a housing, a flexible surface, a means for its formation, including a spin device and means for controlling the orientation of the flexible reflective surface. The spacecraft body is made in the form of two pivotally connected parts, one of which is connected to a flexible reflective surface. In this case, the forming means is equipped with a transformable flywheel mounted on another part of the housing, made in the form of an additional flexible reflective surface. The spin device is made in the form of a counter-rotation mechanism of the main and additional sails. The control tool for the orientation of the main flexible reflective surface in space is made in the form of a device for changing the angle between the longitudinal axes of the housing parts.

The disadvantages of the prototype include the complexity of the design of the mechanism of fracture of the longitudinal axis of the spacecraft in a two-stage hinge, with which the orientation of the system relative to the transverse axes is achieved.

In addition, the flexible surface forming means including the twist device also has a complex structure and a large weight.

These disadvantages of the prototype lead to an increase in the specific gravity of the SEC per unit surface area.

The technical task of this invention is to reduce the inertia of control of the solar sail (SP), the deployment of a flexible surface of the joint venture according to a given program, as well as an increase in the thrust of the SEC and the mass of the payload by reducing the specific mass of the joint venture per unit surface area.

This technical problem is solved due to the fact that in a solar sailing ship containing a hull, main and additional flexible surfaces, the means for forming and controlling the orientation of the main and additional flexible surfaces are made in the form of pneumatic systems, including concentric pneumatic chambers and radial racks, consisting of separate pneumatic cells form a torus or ball.

Controls of flexible reflective surfaces are made in the form of cardan suspensions with electric drives.

On the external frames of the gimbal suspensions are installed the appropriate means of forming reflective flat surfaces and devices for their promotion, made in the form of pneumatic systems.

Pneumatic systems at the same time contain concentric pneumatic chambers and radial racks. They are made in the form of a flexible tube, inside of which there are equidistant valves with holes that allow gas to pass in only one direction when the pressure is higher than the set level. Around the valve openings on the tube, pneumatic cells of the shape of a torus or a sphere are interacting with each other.

Figure 1 shows a General view of the SEC, where:

1 - housing;

2 - the main flexible surface;

3 - additional flexible surface;

4, 5 - the first and second cardan suspensions;

6, 7 - the first and second promotion devices;

8, 9 - the first and second pneumatic systems of surface formation.

x _i y _i z _i ; α _i β _i ; (i = 1,2) - the coordinate system and the rotation angles of the universal joints 4 and 5;

ω _i (i = 1,2) - the angular velocity of rotation of the flexible surfaces 2 and 3.

Figure 2 shows the design of the gimbal with a pneumatic system for surface formation and a device for its promotion, where:

10 - installation racks;

11, 12 - inner and outer frames of the gimbal;

13, 14, 15 - the first, second and third electric motors, respectively;

16 - hoop;

17 - a wheel;

18 - internal pneumatic chamber.

Figure 3 shows the design of the device for swirling flexible surfaces 8 or 9 (I variant), where positions 11-18 are the same as in figure 2.

19 - groove;

20 - sealing gaskets;

21 - fitting;

22 - a hose;

23 - valve;

24 - bearings;

25 - spring mount bearings.

Figure 4 shows the design of the second variant of the promotion device, where the positions 11-24 are the same as in figure 3.

26 - winding of the rotor;

27 - stator winding;

28 - metal rings;

29 - dielectric rings;

30 - brushes;

31 - electric wires.

Figure 5 shows a General view of the pneumatic system of surface formation 6 and 7, where:

18 - internal pneumatic chamber;

32 - external pneumatic chamber;

33 - the average pneumatic chamber;

34 - radial racks;

35 - stretch marks;

36 - flexible reflective strip.

Figure 6 shows the installation location of the valve 37 for pneumatic cells toroidal shape 38, bound in a chain.

39 - elastic tube;

7, valves 37 are connected in series between pneumatic cells of a toroidal shape 40, forming a "garland".

In Fig. 8, the valves are connected together by pneumatic cells of the shape of a ball 41.

Figure 9 shows the design of the first embodiment of the valve 37, where:

42 - the sleeve is cylindrical;

43 - ball;

44 - spring;

45 - a stub;

46 - holes;

47 - electrical wire;

48 is a spiral.

Figure 10 shows the design of the second variant of the valve 37, where:

49 - positions 45-48 are the same as in Fig.7; second cylindrical sleeve;

50 - elastic strips;

51 - a second stub;

52 - hole in the flexible tube.

Figure 11 shows a view of figure 10.

Solar sailing ship (SPK) operates as follows.

SPK contains one-piece hull 1, main 2 and additional 3 sails. In the transport state, the sails are stacked and occupy a small volume. Sails are mounted on the same gimbal. When controlling and changing the orientation of the sails relative to the transverse axes OX _i and OY _i , their centers O _i do not change their position, which greatly simplifies their control algorithms.

The main flexible reflective surface (sail 2) is installed using the first gimbal 4. The gimbal rotates the sail 2 around the axes O ₁ X ₁ and O ₁ Y ₁ by angles ± α ₁ and ± β ₁ , respectively. The plane of the sail (X ₁ O ₁ Y ₁ ) at any position passes through the origin O ₁ . Similarly, with the help of a second gimbal suspension 5, a second additional flexible surface (sail 3) is installed. Turning around the axes O ₂ X ₂ and O ₂ Y ₂ ± α ₂ ± β ₂ provides a change in the orientation of the additional sail 3.

The origin of coordinates O ₁ and O ₂ , through which the planes of sails 2 and 3 pass, coincides with the longitudinal axis of the hull of the SEC of cylindrical shape.

On the outer frames of the gimbal suspensions 4 and 5, the first 6 and second 7 promotion devices are installed, respectively.

Spinning devices provide rotation of the main and additional sails with angular speeds of rotation + ω ₁ , and -ω ₂ in opposite directions.

On the rotating hoops 17 of the spinning devices 6 and 7, the first 8 and second 9 pneumatic systems of surface formation are installed, respectively.

аналогично прототипу [2].The main sail 2 is ring-shaped. The inner diameter of the ring is equal to the outer diameter of the additional sail 3. The additional sail acts as a compensator for the kinetic moment of the main sail. At the same time, an additional sail increases the effective area of the joint venture by

similar to the prototype [2].

In contrast to the prototype, the pneumatic systems for the formation of flat surfaces 8 and 9 are used to reveal the main and additional sails [3].

In addition, instead of a two-stage hinge with a drive used to control the angle of fracture of the longitudinal axis of the joint venture in the prototype [2], the proposed technical solution uses a gimbal 5.

If gyroscopic effects are used to change the triaxial orientation of the SEC with the main sail 2, then the need for the first gimbal suspension 4 disappears.

By controlling the relative angular velocity ω _{2 of} rotation of the additional sail, orientation with respect to the longitudinal axis of the ship is achieved.

Orientation with respect to the transverse axes OX ₁ and OY _{1 is} achieved due to the procession of the system when the angular position between the axes O ₁ Z ₁ and O ₂ Z _{2 of the} cardan suspensions in two control planes ZO ₁ X ₁ and ZO ₁ Y ₁ changes.

When the sails rotate in different directions, the system preserves the zero kinetic moment during operation and the configuration of flexible surfaces is maintained.

Figure 2 shows the kinetic layout of the gimbal (4 or 5) and the spin device (6 or 7) of the pneumatic system for the formation of flexible flat surfaces (8 or 9).

Cardan suspensions are mounted on the cylindrical housing of the SEC concentrically to its outer surface with the help of two struts combined with the vertical axis of its rotation (O ₁ Y ₁ ).

The inner 11 and outer 12 gimbal frames rotate respectively around the mutually perpendicular axes O _i Y _i and O _i X _i by angles ± α _i and ± β _i (i = 1,2). The origin (O ₁ and O ₂ ) is aligned with the longitudinal axis of the cone SPK. In addition, the X ₁ O ₁ Z ₁ plane is aligned with the X ₂ O ₂ Z ₂ plane, and the Y ₁ O ₁ Z ₁ plane is aligned with Y ₂ X ₂ Z ₂ .

This combination of control systems for gimbal suspensions and their placement relative to the housing 1 of a cylindrical shape significantly simplifies the control and orientation algorithms of the SEC.

At the end of the upper strut 10, the first electric motor (ED ₁ ) 13 is fixedly mounted. The axis of rotation of the rotor of this engine coincides with the axis O _i Y _i and is fixedly connected to the inner frame of the gimbal (11 or 12). The stator of the second electric motor (ED ₂ ) 14 is fixedly connected to the inner frame 11 of the corresponding gimbal.

The axis of rotation of the rotor of this engine coincides with the axis of rotation O _i X _{i of the} outer frame of the universal joint suspension 12.

установлено колесо 17, которое взаимодействует с обручем и приводит его во вращение.A hoop 16 is mounted on the outer frame 12 with the possibility of free rotation around it. For this purpose, a third electric motor ED ₃ 15 is used. The stator of this engine is fixedly connected to the internal frame of the universal joint suspension 11. At the same time, the external frame of the universal joint suspension 12, which rotates freely around it, is pivotally mounted on the motor shaft. On the motor shaft ED

a wheel 17 is installed, which interacts with the hoop and drives it into rotation.

An internal air chamber 18 of the corresponding pneumatic system for forming the surface 8 or 9 is installed on the hoop 16. Structural elements 15-17 are included in the device for twisting the flexible surfaces 6 or 7 (see FIGS. 2 and 3).

Spin devices provide rotation of the main 2 and additional 3 flexible surfaces (sails) in opposite directions, thereby compensating for the kinetic moments of each other.

In addition, the rotation of the hoop 16 with the pneumatic system 8 or 9 due to centrifugal forces facilitates the process of opening the previously laid flexible surfaces and withstands their flat shape.

The design of the swirl device in figure 3 contains a hoop 16 with a concentric circular groove 19, which is pneumatically connected to the internal cavity of the pneumatic chamber 18. The outer frame 12 of the gimbal has the same concentric groove.

Sealing gaskets 20 of a ring shape, laid in two concentric grooves in the outer frame, ensure the tightness of the pneumatic connection between the compressed gas source installed in the SPK housing and the pneumatic surface formation system 8 or 9. Compressed gas enters the groove 19 through the fitting 21, the hose 22 and the valve 23.

To ensure the tightness of the seal between the outer frame of the gimbal 12 and the hoop 16, bearings 24 are used, which are mounted with perpendicular mounts around the perimeter of the frame 12 at equal distances.

For spinning the hoop 16 with a surface forming pneumatic system installed on it, a second embodiment of the spinning device design shown in FIG. 4 can be used.

The rotor winding 26 is mounted on the outer frame of the gimbal 12. The stator winding 27 is located on the inside of the hoop 16. The interaction of the electromagnetic fields of these windings leads to rotation of the hoop and the surface forming pneumatic system installed on it, in one direction or another, depending on the polarity of the applied voltage.

To supply voltage to the rotating hoop, metal dielectric rings 29 are used. The latter, in turn, are mounted concentrically on the side surface of the hoop. To supply voltage to the stator winding 27, brushes 30 and electric wires 31 are used.

The flexible surface is a dielectric film with a thickness of 4 ÷ 10 μm with an aluminum coating. Such a film reflects up to 94% of the incident solar radiation. When radiation is reflected, it exerts pressure on the film. The pressure force of solar radiation is constant in time and is used as the engine of the SEC.

One hector of the solar sail is sufficient to move in outer space satellite weighing 160 kg [1].

The main problems of creating a space sail: the first is how to make it easy; the second is how to control it in space.

The proposed technical solution allows to solve both of these problems. To disclose a flexible reflective surface (sail), a pneumatic system for forming the surface 8, 9 in Fig. 5 [3] is used.

The pneumatic system consists of an internal 18 and an external 33 pneumatic chambers, pneumatically connected to each other using radial struts 33.

The internal pneumatic chamber 18 has the shape of a torus - a bicycle chamber and is mounted on a rotating hoop 16.

The external pneumatic chamber 32 and the radial struts 33 are formed from separate pneumatic cells of the shape of a torus (donut) or a ball, interconnected by a tube of flexible material [3].

In the proposed technical solution, two more design options of the pneumatic system are used (see Figs. 5-7).

Similarly to the known reflector [3], the pneumatic system, when filled with gas, takes the form of a bicycle wheel.

Using stretch marks 34 attached to the ears, extended on the sides of the inner air chamber 18, and the air cells of the outer chamber 32, a flexible surface (reflective film) is opened.

In contrast to the known radiation reflector [3], in this embodiment, the pneumatic systems of the pneumatic cell forming radial rods and the external pneumatic chamber are connected to each other via valves 37.

The valves provide a predetermined sequence of filling the pneumatic cells with gas and increase the reliability of the pneumatic system. This is due to the fact that the loss of tightness of individual pneumatic cells does not affect the performance of the entire system as a whole.

Pneumatic systems of surface formation 8 and 9 of the main 2 and additional 3 flexible surfaces have a slight difference in their design. The first pneumatic system for surface formation 8 contains an additional middle pneumatic chamber 33 with a diameter equal to the diameter of the external pneumatic chamber 32 of the second pneumatic system 9. In addition, in the second pneumatic system, a flexible surface (reflective film) 2 is stretched between the inner 18 and external 32 pneumatic chambers.

In the first pneumatic system, the reflective film is stretched between the middle 33 and external 32 pneumatic chambers. When stretched, the flexible surface (main sail) 2 takes the form of a ring with an inner diameter equal to the outer diameter of the additional sail 3.

гдеThus, the total area of the main and additional sails is

Where

R _int. - radius of the external air chamber of the main sail.

When opening the valve 23, the compressed gas through the hose 22 and the fitting 21 enters the internal pneumatic chamber 18.

After filling it and reaching the pressure of the actuation level of the valve 37, the process of filling and opening the radial rods 34 begins. The process proceeds according to the relay principle. From the first pneumatic cell, the second, and then the third, and so on, are fed. After filling all the cells of the radial strut 32, the process of filling the pneumatic cells 38 (40, 41) of the external pneumatic chamber 32 of the additional sail 3 or the middle pneumatic chamber of the main sail 2 begins. There may be another option - the simultaneous filling of the middle and external pneumatic chambers. This is ensured by the construction of the pneumatic line, consisting of tubes 39, cells 38, 40, 41 and valves 37.

The disclosure of flexible surfaces (sails) can be accelerated by the use of centrifugal forces. For this, at certain stages of the disclosure of flexible surfaces, it is necessary to actuate the promotion devices 6 and 7.

Centrifugal forces will also increase the reliability of the design of pneumatic systems for surface formation and improve the quality factor of the tension of the reflective films of the main and additional sails.

Figure 6 shows a section of the chain, woven from pneumatic cells of a toroidal shape 38. When filling the torus and tube 39 with gas, the torus takes a circular shape, and the tube is straight. Since 1/3 of the tube passes through the diameter of adjacent pneumatic cells, the tori become in one row, and the tube 39 is straightened. This is how radial struts 34 are formed.

If the ends of the tube are connected, as is done in the external 32 and middle 33 pneumatic chambers, then the rectifying force created by the pneumatic cells (tori) 38 will give the pneumatic chambers 32 and 33 a round shape. The entire pneumatic system will take the form of a bicycle wheel.

With the help of ears built up on pneumatic cells and stretch marks, a flexible reflective surface (sail) is revealed [3].

To increase the strength, the reflective film can be “reinforced” with radial and concentrated threads of high-strength materials.

Figure 7 shows a section of "garland" consisting of toroidal pneumatic cells 40 in contact with each other, the diameter of which is tube 39. At the interface of the pneumatic cells, valves 37 are installed that allow gas to pass in one direction when the pressure is exceeded above the threshold level P ₁ . In this case, to straighten the tube 39, the interaction force between circular pneumatic cells (tori) having one point of contact is used.

In Fig. 8, pneumatic cells of the shape of a ball 41 are used to form a "garland", which are connected to each other through valves 37 of the pneumatic cell.

The straightening of the tube 39 occurs as a result of the interaction of ball pneumatic cells having one point of contact [3].

Figure 9 shows the construction of the first variant of the valve 37. The valve consists of a cylindrical sleeve 42, inside of which a ball 43 and a spring 44 are installed. At one end, the spring rests on the ball and the other on the plug 45. The hole in the tube at the other end has a smaller cross section. The spring ball seals the hole in the tube. The ball passes gas into the adjacent pneumatic cell only when the pressure in the previous cell becomes higher than the level of P ₁ . When this level is exceeded, the spring 44 is compressed and the ball passes gas into the next pneumatic cell through the hole 46 in the sleeve 42 and the tube 39.

Thus, one by one, all the pneumatic cells are filled one after another, forming radial struts 34, as well as the middle 33 and external 32 pneumatic chambers.

Figure 10 shows the construction of the second variant of the valve 37. The valve also consists of a cylindrical (second) sleeve 49, a ball 43 and two elastic strips 50 fixed mutually perpendicularly, and the second plug 51. The hole 52 in the flexible tube coincides with the hole 46 of the valve.

Unlike the first option (Fig. 9), the ball closes the hole in the sleeve 49 due to the tensile forces of the elastic strips 50. When the pressure rises above the set level P _{1, the} elastic strips stretch, the ball is squeezed and gas through the openings 46 enters the next pneumatic cell.

Thus, the entire pneumatic system as a whole is filled.

In case of damage to individual pneumatic cells, the system retains its shape, as valves do not allow gas to flow towards a damaged pneumatic cell. Thus, the reliability and durability of the entire system as a whole increases.

If necessary, coagulation (assembly) of the pneumatic system in the design of the valves can be made the following design changes.

Throughout the tube 39, passing through the radial struts 34 and air chambers 32 and 33, it is necessary to pass an electric conductor 47 connecting the spirals 48 to each other. The spirals are made of a material with high electrical resistivity (for example, nichrome). Spirals are installed inside balls 43 (50). Balls, in turn, are made of a material that easily melts when it is heated (for example, from plexiglass). When the system works out, the ends of the electric wire 47 are connected to a source of EMF. The current passing through the spirals heats them. This causes the balls to melt. When this valve 37 lose their properties, the tube 39 becomes through. Having disconnected the hose 22 from the valve 23 and the source of compressed gas, the gas contained in the pneumatic system is released into the surrounding space. Then, pulling the tube 39 with the electric wire 47, you can roll the entire pneumatic system together with a flexible reflective film.

This design of the SEC has greater reliability, efficiency (determined by the ratio of the sail area to the total mass of the structure), a lower specific gravity, which leads to an increase in the thrust of the SP and acceleration of the spacecraft.

Information sources

1. Polyakova E.N. Space flight with a solar sail. Science, 1986, p. 138-441.

2. Syromyatnikov B.C., Bryanets VP, Koverina IP Spacecraft with a solar sail. RU patent No. 2053940; 6 B 64 G 1/40, 02/10/96, Bull. No. 4 (prototype).

3. Aliev A.S. Radiation reflector. RU, patent No. 2185695, 07.20.2002, bull. No. 20.

Claims (4)

1. A solar sailing ship comprising a hull, primary and secondary reflective surfaces of an annular shape, means for forming these surfaces, including twisting devices, and means for controlling the orientation of the flexible reflective surfaces, characterized in that the orientation control means for the flexible reflective surfaces are based on gimbal suspensions made outside the ship's hull, each spin device is made in the form of a hoop mounted on the outer frame of the gimbal with the possibility of free rotation and interacting with the electric motor, the means of forming reflective surfaces are made in the form of pneumatic systems, including concentric pneumatic chambers and radial racks, consisting of flexible tubes, inside of which valves with holes are equidistantly installed, on which pneumatic cells are built in the form of a torus or a ball, interacting with each other, with each pneumatic system mounted on the corresponding hoop and pneumatically connected through a concentric sealed groove, ennuyu in the hoop and outer gimbal frame, the source of pressurized gas mounted in the hull. 2. The solar sailing ship according to claim 1, characterized in that each said valve comprises a sleeve with holes, inside of which a spring-loaded ball is mounted to overlap these holes, interacting with compressed gas in the cavity of the specified flexible tube. 3. The solar sailing ship according to claim 1, characterized in that each said valve comprises a sleeve with holes, inside of which a ball is installed with the possibility of overlapping these holes, as well as two elastic strips fixed mutually perpendicularly, and the ball interacts with the compressed gas in the cavity the specified flexible tube and with the specified elastic strips. 4. The solar sailing ship according to claim 2 or 3, characterized in that said ball is made of fusible material, such as plastic, and inside it there is a spiral made of a material with high electrical resistance, such as nichrome, and the spirals in the balls are connected in series with each other with a friend and connected to a voltage source.

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