SYSTEM FOR DEPLOYABLE SOLAR PANELS FOR NANOSATELLITES

Abstract

This invention relates to a system for deploying solar panels for nanosatellites, which will find application in science, in space research, and in particular in the equipment of nanosatellites of the CubeSats type. The developed system for deploying solar panels for nanosatellites consists of a fixing connection (11) for keeping the solar panels in a folded state and a hinged connection (10) for forming the solar panels in a common platform. The hinged connection (10) is formed as a hinge, including a central double-walled axis (9), on which a primary torsion spring (4) is centrally mounted, to which central double-walled axis (9) also the second arm (8) and the first arm (7) are connected in series. At one end of the central double-walled axle (9) are made channels for fixing by means of locking rings (6) of a ratchet gear (1), constantly in contact with a support pin (5) under the influence of a secondary torsion spring (3) mounted on axle (2), which is mounted to the first arm (7).

Claims

1. A system for deployable solar panels for nanosatellites, the system including: a fixing connection (11) for holding the solar panels in a folded state; and a hinged connection (10) for forming the solar panels in a common platform formed as a hinge comprising a central double-walled axle (9), on which a primary torsion spring (4) is centrally mounted, to which central double-walled axle (9) also the second arm (8) and the first arm (7) are connected in series; and at one end of the central double-walled axle (9) channels are made for fixing by means of retaining rings (6) of a ratchet gear (1), constantly in contact with a support pin (5) under the influence of a secondary torsion spring (3), mounted on an axle (2), which is mounted to the first arm (7).

2. The system for deployable solar panels for nanosatellites, according to claim 1, wherein the hinge (10) also comprises an additional torsion spring (16) located opposite the primary torsion spring (4) mounted to the second arm (8).

Description

BRIEF DESCRIPTON OF THE FIGURES

[0010] This invention is illustrated in the accompanying drawings, in which:

[0011] FIG. 1 is a general view of folded solar panels on a satellite body;

[0012] FIGS. 2a and 2b represent deployable solar panels;

[0013] FIG. 3a is a general sectional view of the hinged connection shaped like a hinge from a nanosatellite solar panel deployment system;

[0014] FIG. 3b is a top view of the hinge of FIG. 3a;

[0015] FIG. 4 is a side view of the hinge of FIG. 3a;

[0016] FIG. 5 is a rotated sectional view C - C of FIG. 3a; and

[0017] FIG. 6 is an axonometric view of the hinge with an additional torsion spring.

DETAILED DESCRIPRION OF EMBODIMENT OF THE INVENTION

[0018] The developed system for deployable solar panels for nanosatellites, shown in FIGS. 1, 2a and 2b, consists of a fixing connection 11 for holding the solar panels 14 in a folded state and a hinged connection 10 for forming the solar panels 14 in a common platform. The series of solar panels 14 are connected as a single solar array; one of the solar panels, which is connected to the satellite body 12, is deployable and is called a stationary satellite panel 15. The fixing connection 11 and the hinged connection 10 ensure retention of the solar panels 14 in a folded position with the possibility of their deployment and use as a single unit. Thus combined, the solar panels 14 are connected to the satellite body 12 by means of screws 13. The retention of the solar panels 14 in the folded position is carried out by means of a fixing cord 11, and their release is carried out by breaking or burning the fixing cord 11 by means of a thermal component, heated to a temperature in the range of 80-250° C. After releasing the fixing cord 11, the solar panels 14 are subsequently deployed by means of the hinged connection 10 until reaching the preset geometric configuration of 90°/135°/180° in order to achieve the maximum effective area.

[0019] The hinged connection 10 is formed as a hinge, shown in FIGS. 3a, 3b, 4 and 5, including a central double-walled axis 9 on which a primary torsion spring 4 is centrally fixed. The central axis 9 has two parallel walls which uniquely define the connection of a second arm 8 with consecutive connection of the first arm 7 as well. At one end of the central double-walled axis 9 grooves are made for fixing through retaining rings 6 of the ratchet gear 1. When deploying the solar panel 14, the central axis 9 is simultaneously rotating, with which the ratchet gear 1 also rotates simultaneously, in constant contact with the support pin 5 under the action of a secondary torsion spring 3 fixed on axle 2, which is mounted to the first arm 7. The construction of the hinge 10 is such that when rotating the second arm 8 at 45°, the support pin 5 is rotated simultaneously, followed by the prevention of the rotation of the second arm 8. The hinge 10 is designed as a drive mechanism that ensures the achievement of maximum effective area after deploying the solar unit.

[0020] Due to the state of microgravity - weightlessness, when used in space, the spring mechanisms create characteristic amplitude oscillations (oscillations) during their release, i.e. when activated in working condition, known as jitter. This is due to the lack of a damping environment, such as the Earth’s air.

[0021] The solar panel and the satellite can be considered as two separate bodies connected by a connection (hinge), which bodies after activating the hinge will have a momentum relative to each other and will move (oscillate) relative to their common center of mass. Although such vibrations are attenuated due to dissipation in the spring itself, its inhomogeneity and external influences, such as pressure from solar radiation, aerodynamic friction, or the influence of the Earth’s magnetic field, can continuously feed these vibrations. All these effects create torques that can consistently lead to further amplification of the amplitude of the oscillations and affect the final direction of the satellite for purposes such as: Earth observation; precise astronomical observations; other applications that require targeting accuracy of the order of 0.01-0.1 degrees.

[0022] An embodiment of the hinge 10 shown in FIG. 6 is possible, in which an additional torsion spring 16 is included, located opposite the primary torsion spring 4 mounted to the second arm 8. The use of two primary springs: a primary torsion spring 4 and an additional torsion spring 16, located opposite each other and mounted on the second arm 8 with different resistance coefficients, leads to a decrease in the effective spring coefficient, which is a prerequisite for increasing the damping coefficient of the hinge mechanism 10, and accordingly the solar panels 14 will be positioned to the set geometric configuration of 90°/135°/180° without additional oscillations.

[0023] The efficiency of the created system is expressed in the possibility of the solar panels to be used as a single unit, without being tied to a certain geometry of the main structure, which provides the possibility to achieve maximum delivered or accumulated power in the deployed state of the array when the sun is orthogonal relative to the solar array.