CN201172484Y

CN201172484Y - Satellite bias solar panel adapting for local times of different southbound nodes

Info

Publication number: CN201172484Y
Application number: CNU2008200788630U
Authority: CN
Inventors: 崔玉福; 李琳琳; 李委托; 翟峰; 鄢婉娟
Original assignee: Aerospace Dongfanghong Satellite Co Ltd
Current assignee: Aerospace Dongfanghong Satellite Co Ltd
Priority date: 2008-01-31
Filing date: 2008-01-31
Publication date: 2008-12-31
Anticipated expiration: 2018-01-31

Abstract

The utility model relates to a satellite bias solar wing adaptive for different local times at different descending nodes, which comprises a connecting frame, an inner plate, a middle plate, an outer plate, a root hinge, a first inter-plate hinge, a second inter-plate hinge and a third inter-plate hinge. The utility model can adjust the angle of the first inter-plate hinge to realize bias solar wing, having simple structure. The unfolded solar wing has a certain bias angle (30 degrees at most) with the Y-axis of the satellite, therefore, the solar wing can attain 1.5 freedom degrees, to resolve the power supply problem of the whole satellite caused by the over large of the normal angle between the sunlight and the sailboard. The utility model keeps the former structure of satellite solar wings without additional units, to reduce the development cost.

Description

A kind of satellite biasing sun wing be adapted to different descending node local time

Technical field

The utility model relates to a kind of satellite sun wing, relates in particular to a kind of satellite biasing sun wing be adapted to different descending node local time.

Background technology

The sun wing of satellite is divided into the fixedly sun wing and two kinds on the rotation sun wing, and fixedly the sun wing generally is applicable to the track in morning and evening, i.e. 6:00 or 18:00 track; Rotate the sun wing and generally be applicable to track in non-morning and evening.For the rotation sun wing that is installed in satellite ± Y both sides, in the local time of the satellite descending node, be 12:00, make sunray vertical by rotating the sun wing with solar array, promptly the angle of sunray and windsurfing normal is 0 °.If in the local time of the satellite descending node be the morning or afternoon, 12:00 whenever differed one hour with noon, even the sun wing rotates, the angle of sunray and windsurfing normal also can increase by 15 °, thereby can influence the efficient of solar array electromotive power output, can not satisfy the demand of power supply on the star.For the morning track or afternoon track satellite, because the angle of sunray and windsurfing normal is bigger, in order to guarantee the demand of power supply on the star, design of satellites has following several method to improve the horsepower output of the sun wing: (1) adopts the mode that increases solar cell panel; (2) adopt more high efficiency solar cell piece; (3) adopt twin shaft BAPTA to drive the sun wing.All can increase cost in the local time of adopting these modes to adapt to different descending node, increase the design of satellites difficulty, also increase the problems such as interference of the flexible sun wing in addition.

The utility model content

Technology of the present utility model is dealt with problems and is: overcome the deficiencies in the prior art, a kind of satellite biasing sun wing be adapted to different descending node local time is provided, simple in structure, design cost is low.

Technical solution of the present utility model is: a kind of satellite biasing sun wing be adapted to different descending node local time comprises between link span, inner panel, middle plate, outside plate, root hinge, first plate between hinge, second plate hinge between hinge and the 3rd plate, link span is connected by the root hinge with windsurfing driver train on the satellite, inner panel and link span are connected to form 150 °～180 ° angle by hinge between first plate, inner panel is connected by hinge level between second plate with middle plate, and middle plate is connected by hinge level between the 3rd plate with outside plate.

Hinge is formed by colluding hinge, lock hinge, volute spiral spring, lock arm between described first plate, collude hinge, lock hinge, lock arm and pass through bolted connection with volute spiral spring respectively, collude hinge and have lock slots, collude hinge and of the angle of eccentricity biasing of lock hinge, make the sun span open the back and be bias state with satellite Y direction by setting.

The utility model advantage compared with prior art is: the utility model is only realized the biasing of the sun wing by adjusting between link span and the inner panel between first plate angle of hinge, simple in structure, make the sun span open the back and be certain angle of eccentricity (maximum 30 °) with satellite Y direction, be equivalent to the sun wing and have 1.5 degree of freedom, cause putting in order energy source of star problem in short supply thereby improve, local time applicable to different descending node because sunray and windsurfing normal direction angle are excessive; The utility model keeps satellite sun wing original structure, does not increase any assembly, and comparing increases the windsurfing area or adopt more high efficiency battery sheet or employing twin shaft windsurfing driver train, greatly reduces development cost.

Description of drawings

Fig. 1 is a constructional drawing of the present utility model;

Fig. 2 is the constructional drawing of hinge between the utility model first plate;

Fig. 3 is installed on scheme drawing on the satellite for the utility model.

The specific embodiment

Below in conjunction with the drawings and specific embodiments the utility model is done to describe in further detail:

As shown in Figure 1, the present invention includes between link span 1, inner panel 2, middle plate 3, outside plate 4, root hinge 5, first plate between hinge 6, second plate hinge 8 between hinge 7 and the 3rd plate, link span 1 is connected by root hinge 5 with windsurfing driver train 9 on the satellite, inner panel 2 and link span 1 are connected to form 150 °～180 ° angle by hinge 6 between first plate, inner panel 2 is connected by hinge 7 levels between second plate with middle plate 3, and middle plate 3 and outside plate 4 adopts that hinge 8 levels are connected between the 3rd plate.

As shown in Figure 2, hinge 6 is mainly formed by colluding hinge 21, lock hinge 22, volute spiral spring 23, lock arm 24 between first plate, hinge 6 is formed by colluding hinge 21, lock hinge 22, volute spiral spring 23, lock arm 24 between described first plate, collude hinge 21, lock hinge 22, lock arm 24 and pass through bolted connection with volute spiral spring 23 respectively, collude hinge 21 and have lock slots, collude hinge 21 and angle of eccentricity (150 °～180 °) biasing of lock hinge 22, make the sun span open the back and be bias state with satellite Y direction by setting.

Between second plate between hinge 7, the 3rd plate between the structure of hinge 8 and first plate structure of hinge 6 identical, collude hinge and be hinged into lock and be horizontally disposed with.

Embodiment

Sun wing link span 1 main structure adopts two high-strength and high-modulus amount carbon fiber/epoxy resin composite material rectangle hollow to cut section bar, and its sectional dimension length and width are respectively 28mm * 26mm, two ends design of hinges jointing.Sun medial pterygoid plate 2, middle plate 3, outside plate 4 scantling of structure, length x width x thickness is respectively 1110mm * 850mm * 24mm, adopts carbon fiber/aluminium honeycomb interlayer design, the positive polyimide film that pastes 0.05mm.

Between link span 1 and the inner panel 2 between first plate angle of hinge 6 be set to 170 °, the structure design form of hinge between existing plate (between second plate between hinge 7, the 3rd plate hinge 8) has been inherited in the design of hinge 6 between first plate, 180 ° of latched positions that hinge between plate is original structurally change 170 ° into, and the sun span is opened the back and is 10 ° of angles with satellite Y direction.The structure of hinge 6 as shown in Figure 2 between first plate, collude of the requirement design of the lock slots position of hinge on 21 by 170 ° of angle of eccentricity, because rotational angle changes on this hinge lines, relevant interlock ratio has also been carried out accommodation, greatly between raw sheet 1.059 of hinge engaged wheel 35 times of the increasing diameters of engaged wheel 45 realize that by the interaction relation of 2R → 1.059R → R 90 ° → 170 ° → 180 ° expansion is synchronous.

After satellite is entered the orbit, detonate sun span opening mechanism action of priming system, the sun span is opened, 10 ° of+Y sun wing biased downward ,-Y the sun wing is to 10 ° of upper offsets, as shown in Figure 3.Along with satellite moves in orbit, the windsurfing driver train can corresponding rotation, guarantees that sunray and solar array normal direction angle are reduced to 12.5 ° from 22.5 °, put in order star not during side-sway the horsepower output of solar array will increase by 5.67%; When 35 ° of whole star side-swaies, the horsepower output of solar array will increase by 25.73%, thereby the nervous situation of whole star power in the time of can alleviating side-sway, satisfying on the star under the equal power demand, the number of substrates of solar array can be reduced or the lower battery sheet of efficient can be adopted, reduce more solar array flexible influence and reduction development cost to Control Subsystem, this technology still belongs to the first time at home.

The utility model not detailed description is a technology as well known to those skilled in the art.

Claims

1, a kind of satellite biasing sun wing be adapted to different descending node local time, it is characterized in that: comprise link span (1), inner panel (2), middle plate (3), outside plate (4), root hinge (5), hinge between first plate (6), hinge (8) between hinge between second plate (7) and the 3rd plate, link span (1) is connected by root hinge (5) with windsurfing driver train (9) on the satellite, inner panel (2) and link span (1) are connected to form 150 °～180 ° angle by hinge (6) between first plate, inner panel (2) is connected by hinge (7) level between second plate with middle plate (3), and middle plate (3) is connected by hinge (8) level between the 3rd plate with outside plate (4).

2, a kind of satellite biasing sun wing be adapted to different descending node local time according to claim 1, it is characterized in that: described inner panel (2) is 170 ° with the angle of link span (1).

3, a kind of satellite biasing sun wing be adapted to different descending node local time according to claim 1, it is characterized in that: hinge (6) is formed by colluding hinge (21), lock hinge (22), volute spiral spring (23), lock arm (24) between described first plate, collude hinge (21), lock hinge (22), lock arm (24) and pass through bolted connection with volute spiral spring (23) respectively, collude hinge (21) and have lock slots, collude hinge (21) and the angle of eccentricity biasing of lock hinge (22), make the sun span open the back and be bias state with satellite Y direction by setting.