CN104058105A - Deep space solar sail spacecraft driven by utilizing sunlight pressure - Google Patents
Deep space solar sail spacecraft driven by utilizing sunlight pressure Download PDFInfo
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- CN104058105A CN104058105A CN201410286986.3A CN201410286986A CN104058105A CN 104058105 A CN104058105 A CN 104058105A CN 201410286986 A CN201410286986 A CN 201410286986A CN 104058105 A CN104058105 A CN 104058105A
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Abstract
The invention discloses a deep space solar sail spacecraft driven by utilizing sunlight pressure. The deep space solar sail spacecraft driven by utilizing the sunlight pressure comprises a support frame, four support arms, four isosceles right triangle sail covers, a first solar cell, an etching antenna, two sliders and four roll axis stabilization mechanisms. The deep space solar sail spacecraft disclosed by the invention has the advantages that an open support packaging structure and a gird are adopted, and an outer packaging structure of a traditional satellite is removed, so that the mass of the solar sail spacecraft is reduced; inflation systems and air storage structures in traditional inflatable deployment support arms can be removed due to the fact that the self-deployment support arms are adopted, so that the mass of the solar sail spacecraft is reduced; by applying the wireless communication technology, the use of a communication line is reduced, so that communication and data transmission can be performed respectively by all parts of the large-area solar sail spacecraft, and the mass of the solar sail spacecraft is reduced; the sliders and the roll axis stabilization mechanisms are used for attitude control, and thus, the triaxial attitude control of the solar sail spacecraft can be realized; compared with spin stabilization attitude control, the triaxial attitude control can be used for executing broader tasks.
Description
Technical field
The present invention relates to a kind of sail shape spacecraft, particularly a kind of utilize solar pressure as propulsive effort, there is the Solar sail spacecraft of carrying out survey of deep space ability.
Background technology
The sail shape detector that utilizes solar pressure to drive is called again Solar sail spacecraft, is to utilize sunshine to compress into the cosmonautic aircraft of row.In ideal conditions, Solar sail spacecraft is without any need for fuel, and it can obtain lasting thrust and fly to cosmic space from inexhaustible sunlight.As long as shape and inclination angle are suitable, Solar sail spacecraft can fly to any direction including light source, particularly aspect survey of deep space, has great preceence.
Photon strikes is to solar sail face and reflected back completely, solar sail is produced to antagonistic force and promote solar sail and carry out space travel, is called light pressure and drives.In order to make solar power that enough optical pressure are provided, solar sail must capture sunshine as much as possible, and this area that just means sail must be enough large, and in order to obtain larger acceleration/accel, the weight of Solar sail spacecraft must be light as much as possible.In the time of transmitting, because emission space is limited, need again solar sail to be stored in less space.Solar sail spacecraft has multiple mode classification: by sail face shape difference, can be divided into square sail, circular sail and leaf sail etc.; By expansion mode difference, can be divided into spin deploying solar sail and strut bar type solar sail.
A lot of national research of all carrying out Solar sail spacecraft in the world at present, the U.S. successfully enters near-earth orbit and has carried out launching experiment in the NanoSail-D solar sail of in November, 2010 transmitting.NanoSail-D sail face is square, has four chevron pointing hold-down arms, and strut bar and sail face adopt 5 points (center-point and four summits) connection mode.But the IKAROS of the self-rotary that Japan launched in May, 2010 for deep space mission is a unique successful story, and IKAROS folds the entirety of solar sail face, utilize spin centnifugal force to realize the stepwise development of sail face.But existing self-rotary solar sail is not suitable for large area to be launched, therefore at present for survey of deep space task, be badly in need of a kind of Solar sail spacecraft that launches in-orbit, has larger area-mass ratio, meets the hold-down arm form of survey of deep space mission requirements of research.
Summary of the invention
Technical matters solved by the invention is: overcome the deficiencies in the prior art, a kind of deep space Solar sail spacecraft that utilizes solar pressure to drive is provided, 4 hold-down arms that utilization has the performance of self-deploying are realized expansion and the support of sail face, adopt 5 connection modes to realize the stretching of sail face, have compared with facet value ratio, can meet the demand of survey of deep space task.
Technical scheme of the present invention is: a kind of deep space Solar sail spacecraft that utilizes solar pressure to drive, comprises bracing frame, four hold-down arms, four isosceles right triangle sail faces, the first solar battery sheet, etching antenna, two slide blocks and four wobble shaft stabilizing mechanisms;
Two slide blocks are arranged on respectively on two adjacent hold-down arms; Slide block comprises the second solar battery sheet, the first wireless communication module and remotely controlling exercise dolly, and the second solar battery sheet and the first wireless communication module are all positioned on remotely controlling exercise dolly, and remotely controlling exercise dolly is enclosed within on hold-down arm; The second solar battery sheet is the power supply of remotely controlling exercise dolly, the first wireless communication module and satellite body carry out the mutual of data and instruction, and the instruction of satellite body is exported to remotely controlling exercise dolly, remotely controlling exercise dolly moves on hold-down arm according to the instruction receiving, to adjust the centroid position of Solar sail spacecraft;
Wobble shaft stabilizing mechanism comprises pull bar, the 3rd solar battery sheet, the second wireless communication module, rotating mechanism, bracing frame and sleeve, bracing frame is hollow structure, the 3rd solar battery sheet and the second wireless communication module are arranged on the sunny slope of bracing frame, rotating mechanism is arranged on bracing frame inside, the turning cylinder of rotating mechanism is connected with the center of pull bar, bracing frame is arranged on sleeve, and sleeve is adhesive in the top of hold-down arm; The 3rd solar battery sheet is rotating mechanism power supply, the second wireless communication module and satellite body carry out the mutual of data and instruction, and the instruction of satellite body is exported to rotational structure, rotational structure can provide positive dirction or reciprocal rotating torque for Solar sail spacecraft according to the instruction receiving;
The summit, right angle of each isosceles right triangle sail face is connected in the central support posts of bracing frame, and another two summits are connected on the pull bar of adjacent wobble shaft stabilizing mechanism; Each isosceles right triangle sail face, by substrate and coating composition, is provided with the first solar battery sheet in substrate, be etched with etching antenna on coating; The first solar battery sheet is symmetrical on the square sail face of four isosceles right triangle sail face compositions;
Described satellite body refers to the summation of the various unit that on deep space Solar sail spacecraft, electronic devices and components form, and satellite body is positioned on bracing frame.
Also comprise band, Solar sail spacecraft is in the time of deployed condition not, and band, for the each device of Solar sail spacecraft is tightened, in the time that Solar sail spacecraft launches, is cut off band by control mechanism, the constraint of releasing to each device; Band adopts titanium alloy strip to make.
Support frame as described above adopts aluminum honeycomb panel to make.
Described hold-down arm is made up of carbon fiber composite material.
The substrate of described each isosceles right triangle sail face is Kapton, and coating is aluminium film.
On described hold-down arm, form coating antenna by coating.
The present invention's technique effect is compared with prior art:
(1) the present invention utilizes hold-down arm to carry out the expansion of sail face, need not consider rotor inertia problem, has avoided the increase along with area in spin expansion process, and rotor inertia increases gradually, causes rotative speed to reduce, thereby may produce situation about cannot launch;
(2) the present invention adopts the sail of square in configuration, compares circular sail and leaf sail, aspect mechanical property and stability, has advantage, and more excellent propulsion quality can be provided;
(3) the present invention has adopted open supporting package structure and band, has removed the external packing structure of conventional satellite, has alleviated Solar sail spacecraft quality;
(4) hold-down arm that self-deploys of the present invention can be removed air inflator system and the gas storage structure of tradition in inflating expanded, has alleviated Solar sail spacecraft quality;
(5) the present invention makes full use of existing structure, has used the coating antenna on sail face etching antenna and hold-down arm, has removed traditional antenna system, has reduced Solar sail spacecraft quality;
(6) the present invention has reduced the use of communication line by the employing wireless communication technology, and large area Solar sail spacecraft various piece all can be communicated and data transmission, has reduced the quality of Solar sail spacecraft;
(7) slide block and wobble shaft stabilizing mechanism are used for attitude control by the present invention, can realize the three-axis attitude control of Solar sail spacecraft, can carry out more wide in range task than the control of spin stabilization attitude.
Brief description of the drawings
Fig. 1 is the Solar sail spacecraft structural representation under deployed condition not;
Fig. 2 is the Solar sail spacecraft structural representation under deployed condition;
Fig. 3 is slide block schematic diagram;
Fig. 4 is wobble shaft stabilizing mechanism schematic diagram, and wherein (a) is left view, is (b) right elevation;
Fig. 5 is sail face etching antenna schematic diagram;
Fig. 6 is sail face coating schematic diagram;
Fig. 7 is hold-down arm schematic cross-section, schematic cross-section when wherein (a) launches for hold-down arm, the schematic diagram while (b) folding for hold-down arm.
Detailed description of the invention
Below in conjunction with specific embodiment, technical solution of the present invention is further described.
Satellite body is positioned at the center of bracing frame 1, refers to the summation of the various unit that on deep space Solar sail spacecraft, electronic devices and components form.
Fig. 2 is the deep space Solar sail spacecraft under deployed condition, has described the characteristic on sail face.Deep space Solar sail spacecraft mainly comprises four hold-down arms 3, four sail faces 4, bracing frame 1, the first solar battery sheet 5 (thin film solar cell sheet), etching antenna 6, two slide blocks 9 and four wobble shaft stabilizing mechanisms 10.
Four hold-down arms 3 are evenly arranged around the central support posts of satellite bracing frame 1, and one end of every hold-down arm 3 is fixed in the central support posts of bracing frame 1, and the other end is provided with wobble shaft stabilizing mechanism 10;
Slide block 9 is arranged on respectively on two adjacent hold-down arms.Wobble shaft stabilizing mechanism 10 is arranged on the top of four hold-down arms.Slide block and the wobble shaft stabilizing mechanism style of work realize attitude control function, and the detailed structure of slide block 9 is shown in Fig. 3.On slide block 9, include the second solar battery sheet 14, the first wireless communication module 15, can remotely controlling exercise remotely controlling exercise dolly 16.The second solar battery sheet 14 and the first wireless communication module 15 are positioned on remotely controlling exercise dolly 16.The second solar battery sheet 14 offers the slide block 9 needed energy that moves.The first wireless communication module 15 carries out the mutual of data and instruction with satellite body, and the instruction of satellite body is exported to remotely controlling exercise dolly 16, remotely controlling exercise dolly 16 moves on hold-down arm 3 according to the instruction receiving, to adjust the centroid position of Solar sail spacecraft.Remotely controlling exercise dolly 16 that can remotely controlling exercise takes to be sleeved on the form on hold-down arm, guarantees the stable and reliable of motion.As shown in Figure 4, on wobble shaft stabilizing mechanism 10, include pull bar 17, the 3rd solar battery sheet 18, the second wireless communication module 19, rotating mechanism 20, bracing frame 21 and sleeve 22.Wherein in Fig. 4, (a) is left view, is (b) right elevation.Bracing frame 21 is made up of four stay bearing plates, and four stay bearing plates form square hollow structure.The 3rd solar battery sheet 18 and the second wireless communication module 19 are arranged on the stay bearing plate of bracing frame 21 sunny slopes, rotating mechanism 20 is arranged on the stay bearing plate vertical with the stay bearing plate of sunny slope, and be positioned at bracing frame 21 inside, the turning cylinder of rotating mechanism 20 is connected with pull bar 17 center, bracing frame 21 is arranged on sleeve 22, and sleeve 22 is adhesive in the top of hold-down arm 3; The 3rd solar battery sheet 18 offers the rotating mechanism 20 needed energy that moves, the second wireless communication module 19 carries out the mutual of data and instruction with satellite body, and the instruction of satellite body is exported to rotational structure 20, rotational structure 20 can provide according to instruction the rotating torque of positive and negative both direction.Slide block and wobble shaft stabilizing mechanism, for attitude control, can be realized the three-axis attitude control of Solar sail spacecraft.Meanwhile, the employing wireless communication technology has reduced the use of communication line, and large area Solar sail spacecraft various piece all can be communicated and data transmission, has reduced the quality of Solar sail spacecraft.
The summit, right angle of each isosceles right triangle sail face 4 is connected in the central support posts of bracing frame 1, and another two summits are connected on the pull bar 17 of adjacent wobble shaft stabilizing mechanism 10 by rope.Each isosceles right triangle sail face 4 forms by substrate 12 and coating 13, as shown in Figure 6.The first solar battery sheet 5 is installed in substrate 12, on coating 13, is etched with etching antenna 6 (low-gain antenna), as shown in Figure 5.The square edge length of sail face 4 is 160 meters.Substrate is the Kapton of 1 micron-2 microns of thickness, and coating is the aluminium film of thickness 1000 dusts.
Four isosceles right triangle sail faces 4 form a square sail face, and the first solar battery sheet 5 is directly contained on square sail face Kapton, according to the folding mode piecemeal of sail face.The gross area of the first solar battery sheet 5 is 10 sq ms, centered by satellite body, according to square symmetrical.
It is just passable that 6 needs of etching antenna carry out etching at aluminium coated.On sail face, can lay multiple etching antennas and use as middle low-gain antenna, and redundancy each other.On four hold-down arms 3, also lay etching antenna as high gain antenna.
Deep space Solar sail spacecraft has and does not launch and launch two states, and when deep space Solar sail spacecraft is during in deployed condition not, four hold-down arms 3 are in folded state, and four isosceles right triangle sail faces 4 are also in folded state.Fig. 1 is the shape deep space spacecraft that lowers the sail of deployed condition not.The deployed condition shape deep space spacecraft that lowers the sail does not also comprise band 2, bracing frame 1 and band 2 play constraint and supporting role to the sail shape deep space spacecraft under deployed condition not in Spacecraft Launch process, utilize the function of tightening of band 2 to prevent the damage to hold-down arm and sail face in emission process.Bracing frame 1 and band 2 adopt respectively the aluminum honeycomb panel and the titanium alloy strip that in conventional satellite, use.
The cross section of four hold-down arms is two Ω configurations, adopts the carbon fiber composite material with the performance of self-deploying to make.One end of hold-down arm is connected by flange with the central support posts of bracing frame 1.Expansion that can be controlled in order to ensure hold-down arm is controlled by add nylon press strip 11 on hold-down arm, and nylon press strip 11 is bonded in the outside of housing 1 along the center shaft symmetry of housing 1.Hold-down arm is squeezed into yi word pattern when folding, as shown in (b) in Fig. 7, is then curled into plate-like.Schematic cross-section when hold-down arm launches is as shown in (a) in Fig. 7, and hold-down arm diameter is 30 centimetres, and length is 113 meters.
In the time that Solar sail spacecraft launches, four hold-down arms 3 launch to drive four isosceles right triangle sail faces 4 to launch.
Adopt after said structure and component part, the pass between quality and the area of spacecraft is 200 kilograms, 25600 sq ms, and the needed solar sail face amount ratio that meets survey of deep space requires.Spacecraft possesses system and ability necessary in all conventional spacecrafts simultaneously, can realize survey of deep space task.
The above; be only the detailed description of the invention of the best of the present invention, but protection scope of the present invention is not limited to this, is anyly familiar with in technical scope that those skilled in the art disclose in the present invention; simple deduction or replace, within all should being encompassed in protection scope of the present invention.
The content not being described in detail in specification sheets belongs to those skilled in the art's known technology.
Claims (6)
1. a deep space Solar sail spacecraft that utilizes solar pressure to drive, is characterized in that: comprise bracing frame (1), four hold-down arms (3), four isosceles right triangle sail faces (4), the first solar battery sheet (5), etching antenna (6), two slide blocks (9) and four wobble shaft stabilizing mechanisms (10);
Four hold-down arms (3) are evenly arranged around the central support posts of bracing frame (1), one end of every hold-down arm (3) is fixed in the central support posts of bracing frame (1), and the other end is provided with wobble shaft stabilizing mechanism (10);
Two slide blocks (9) are arranged on respectively on two adjacent hold-down arms; Slide block (9) comprises the second solar battery sheet (14), the first wireless communication module (15) and remotely controlling exercise dolly (16), it is upper that the second solar battery sheet (14) and the first wireless communication module (15) are all positioned at remotely controlling exercise dolly (16), and remotely controlling exercise dolly (16) is enclosed within on hold-down arm (3); The second solar battery sheet (14) is remotely controlling exercise dolly (16) power supply, the first wireless communication module (15) carries out the mutual of data and instruction with satellite body, and the instruction of satellite body is exported to remotely controlling exercise dolly (16), remotely controlling exercise dolly (16) above moves at hold-down arm (3) according to the instruction receiving, to adjust the centroid position of Solar sail spacecraft;
Wobble shaft stabilizing mechanism (10) comprises pull bar (17), the 3rd solar battery sheet (18), the second wireless communication module (19), rotating mechanism (20), bracing frame (21) and sleeve (22), bracing frame (21) is hollow structure, the 3rd solar battery sheet (18) and the second wireless communication module (19) are arranged on the sunny slope of bracing frame (21), rotating mechanism (20) is arranged on bracing frame (21) inside, the turning cylinder of rotating mechanism (20) is connected with the center of pull bar (17), bracing frame (21) is arranged on sleeve (22), sleeve (22) is adhesive in the top of hold-down arm (3), the 3rd solar battery sheet (18) is rotating mechanism (20) power supply, the second wireless communication module (19) carries out the mutual of data and instruction with satellite body, and the instruction of satellite body is exported to rotational structure (20), rotational structure (20) can provide positive dirction or reciprocal rotating torque for Solar sail spacecraft according to the instruction receiving,
The summit, right angle of each isosceles right triangle sail face (4) is connected in the central support posts of bracing frame (1), and another two summits are connected on the pull bar (17) of adjacent wobble shaft stabilizing mechanism (10); Each isosceles right triangle sail face (4) is by substrate (12) and coating (13) composition, the first solar battery sheet (5) is installed in substrate (12), on coating (13), is etched with etching antenna (6); The first solar battery sheet (5) is symmetrical on the square sail face of four isosceles right triangle sail faces (4) composition;
Described satellite body refers to the summation of the various unit that on deep space Solar sail spacecraft, electronic devices and components form, and satellite body is positioned on bracing frame (1).
2. a kind of deep space Solar sail spacecraft that utilizes solar pressure to drive according to claim 1, it is characterized in that: also comprise band (2), Solar sail spacecraft is in the time of deployed condition not, band (2) is for tightening the each device of Solar sail spacecraft, in the time that Solar sail spacecraft launches, by control mechanism, band (2) is cut off, remove the constraint to each device; Band (2) adopts titanium alloy strip to make.
3. a kind of deep space Solar sail spacecraft that utilizes solar pressure to drive according to claim 1 and 2, is characterized in that: support frame as described above (1) adopts aluminum honeycomb panel to make.
4. a kind of deep space Solar sail spacecraft that utilizes solar pressure to drive according to claim 1 and 2, is characterized in that: described hold-down arm (3) is made up of carbon fiber composite material.
5. a kind of deep space Solar sail spacecraft that utilizes solar pressure to drive according to claim 1 and 2, it is characterized in that: the substrate (12) of described each isosceles right triangle sail face (4) is Kapton, and coating (13) is aluminium film.
6. a kind of deep space Solar sail spacecraft that utilizes solar pressure to drive according to claim 1 and 2, is characterized in that: described hold-down arm (3) is upper forms coating antenna by coating.
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| CN106394933A (en) * | 2016-09-28 | 2017-02-15 | 西北工业大学 | Solar-sail spacecraft structure provided with distributed satellites for traction |
| CN106428635A (en) * | 2016-10-14 | 2017-02-22 | 南京理工大学 | Solar sail spacecraft three-axis attitude control and execution mechanism |
| CN108820229A (en) * | 2018-06-22 | 2018-11-16 | 李帷笳 | Hybrid power unmanned plane based on computer mode control |
| CN109000783A (en) * | 2018-09-30 | 2018-12-14 | 华南理工大学 | A kind of contactless vibration detection device and method of solar sail structure |
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| CN110119153A (en) * | 2019-05-10 | 2019-08-13 | 北京航空航天大学 | A kind of optical pressure moment actively assist under underactuated spacecraft attitude control method |
| CN110371324A (en) * | 2019-07-22 | 2019-10-25 | 哈尔滨工业大学 | A kind of solar sail being unfolded by multistable curved beam intelligent drives |
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| CN112340066A (en) * | 2020-11-23 | 2021-02-09 | 中国人民解放军国防科技大学 | Formula of can throwing solar sail spacecraft |
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| CN106394933B (en) * | 2016-09-28 | 2018-07-13 | 西北工业大学 | A kind of distributed satellites traction Solar sail spacecraft configuration |
| CN106394933A (en) * | 2016-09-28 | 2017-02-15 | 西北工业大学 | Solar-sail spacecraft structure provided with distributed satellites for traction |
| CN106428635A (en) * | 2016-10-14 | 2017-02-22 | 南京理工大学 | Solar sail spacecraft three-axis attitude control and execution mechanism |
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| CN109000783B (en) * | 2018-09-30 | 2023-09-26 | 华南理工大学 | Non-contact vibration detection device and method for solar sail structure |
| CN109606658A (en) * | 2018-11-26 | 2019-04-12 | 墨宝股份有限公司 | A kind of unmanned plane with long battery life |
| CN110119153A (en) * | 2019-05-10 | 2019-08-13 | 北京航空航天大学 | A kind of optical pressure moment actively assist under underactuated spacecraft attitude control method |
| CN110371324A (en) * | 2019-07-22 | 2019-10-25 | 哈尔滨工业大学 | A kind of solar sail being unfolded by multistable curved beam intelligent drives |
| CN110371324B (en) * | 2019-07-22 | 2022-03-01 | 哈尔滨工业大学 | Solar sail driven to be unfolded intelligently by multi-stable curved beam |
| CN110518327B (en) * | 2019-08-23 | 2020-10-20 | 中国电子科技集团公司第三十八研究所 | Annular foldable mechanism for human-shaped rod of film antenna |
| CN110518327A (en) * | 2019-08-23 | 2019-11-29 | 中国电子科技集团公司第三十八研究所 | A kind of humanoid burr shape telescopic mechanism of film antenna |
| CN110723314A (en) * | 2019-10-12 | 2020-01-24 | 上海宇航系统工程研究所 | Space film structure unfolding mechanism |
| CN112340066A (en) * | 2020-11-23 | 2021-02-09 | 中国人民解放军国防科技大学 | Formula of can throwing solar sail spacecraft |
| CN112340066B (en) * | 2020-11-23 | 2022-04-19 | 中国人民解放军国防科技大学 | Formula of can throwing solar sail spacecraft |
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