CN104058105B - One utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure - Google Patents
One utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure Download PDFInfo
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- CN104058105B CN104058105B CN201410286986.3A CN201410286986A CN104058105B CN 104058105 B CN104058105 B CN 104058105B CN 201410286986 A CN201410286986 A CN 201410286986A CN 104058105 B CN104058105 B CN 104058105B
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Abstract
The invention discloses one and utilize the power-actuated deep space Solar sail spacecraft of solar light pressure, comprise bracing frame, four hold-down arms, four pieces of isosceles right triangle sail faces, the first solar battery sheet, etching antenna, two slide blocks and four wobble shaft stabilizing mechanisms.The present invention has the following advantages: adopt open supporting package structure and band, eliminate the external packing structure of conventional satellite, alleviate Solar sail spacecraft quality; Self-deploy hold-down arm can remove Conventional pneumatic launch in air inflator system and gas storage structure, alleviate Solar sail spacecraft quality; Decreased the use of communication line by the employing wireless communication technology, make large area Solar sail spacecraft various piece all can carry out communicating and data transmission, reduce the quality of Solar sail spacecraft; Slide block and wobble shaft stabilizing mechanism are used for gesture stability, and the three-axis attitude that can realize Solar sail spacecraft controls, and can perform more wide in range task than spin stabilization gesture stability.
Description
Technical field
The present invention relates to a kind of sail shape spacecraft, particularly a kind ofly utilize solar pressure as propulsive effort, there is the Solar sail spacecraft carrying out survey of deep space ability.
Background technology
Utilizing solar light pressure power-actuated sail shape detector to be also called Solar sail spacecraft, is utilize solar light pressure to carry out cosmonautic aircraft.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 suitably, Solar sail spacecraft can fly to any direction comprising light source, particularly in survey of deep space, has great preceence.
Photon strikes to solar sail face is completely reflected back, antagonistic force is produced to solar sail and promotes solar sail and carry out space travel, be called that light pressure drives.In order to the optical pressure making solar power provide enough, solar sail must capture sunshine as much as possible, and this just means that the area of sail is sufficiently large, and in order to obtain larger acceleration/accel, the weight of Solar sail spacecraft must be light as much as possible.When launching, because emission space is limited, need again solar sail to be stored in less space.Solar sail spacecraft has multiple mode classification: different by sail face shape, can be divided into square sail, circular sail and leaf sail etc.; Different by expansion mode, spin deploying solar sail can be divided into and support rod-type solar sail.
A lot of country is all carrying out the research of Solar sail spacecraft in the world at present, and the U.S. successfully enters near-earth orbit in the NanoSail-D solar sail that in November, 2010 launches and carried out launching experiment.NanoSail-D sail face is square, has four timbering with rafter arch sets's arms, and strut bar and sail face adopt 5 points (center-point and four summits) connection mode.But the IKAROS of the self-rotary launched in May, 2010 for Japan deep space mission is a unique successful story, and the entirety of IKAROS to solar sail face folds, and utilizes spin centnifugal force to realize the stepwise development in sail face.But existing self-rotary solar sail is not suitable for large area to be launched, therefore current for survey of deep space task, be badly in need of a kind of Solar sail spacecraft launching in-orbit, there is larger area-mass ratio, meet 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, one is provided to utilize the power-actuated deep space Solar sail spacecraft of solar light pressure, utilize and there is expansion and the support that 4 hold-down arms self-deploying performance realize sail face, 5 connection modes are adopted to realize the stretching in sail face, there is less face amount ratio, the demand of survey of deep space task can be met.
Technical scheme of the present invention is: one utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure, comprises bracing frame, four hold-down arms, four pieces of 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 two adjacent hold-down arms respectively; 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 hold-down arm; Second solar battery sheet is that remotely controlling exercise dolly is powered, first wireless communication module and satellite body carry out the mutual of data and instruction, and remotely controlling exercise dolly is exported in the instruction of satellite body, remotely controlling exercise dolly moves on hold-down arm according to the instruction received, 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, 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; 3rd solar battery sheet is that rotating mechanism is powered, second wireless communication module and satellite body carry out the mutual of data and instruction, and rotational structure is exported in the instruction of satellite body, rotational structure can according to the instruction received for Solar sail spacecraft provides positive dirction or reciprocal rotating torque;
The right-angled apices in 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, substrate is provided with the first solar battery sheet, coating is etched with etching antenna; Symmetrical on the square sail face that first solar battery sheet forms in four isosceles right triangle sail faces;
Described satellite body refers to the summation of the various unit that electronic devices and components are formed on deep space Solar sail spacecraft, and satellite body is positioned on bracing frame.
Also comprise band, when Solar sail spacecraft is in non-deployed condition, band is used for tightening each device of Solar sail spacecraft, when Solar sail spacecraft launches, is cut off by band by control mechanism, removes the constraint 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 in described each isosceles right triangle sail face is Kapton, and coating is aluminium film.
Described hold-down arm forms 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, and avoid the increase along with area in spin expansion process, rotor inertia increases gradually, causes rotative speed to reduce, thus may produce situation about cannot launch;
(2) the present invention adopts the sail of square in configuration, compares circular sail and leaf sail, in mechanical property and stability, has advantage, can provide more excellent propulsion quality;
(3) present invention employs open supporting package structure and band, eliminate the external packing structure of conventional satellite, alleviate Solar sail spacecraft quality;
(4) of the present invention self-deploy hold-down arm can remove Conventional pneumatic launch in air inflator system and gas storage structure, alleviate Solar sail spacecraft quality;
(5) the present invention makes full use of existing structure, employs the coating antenna on sail face etching antenna and hold-down arm, eliminates traditional antenna system, reduce Solar sail spacecraft quality;
(6) the present invention decreases the use of communication line by the employing wireless communication technology, makes large area Solar sail spacecraft various piece all can carry out communicating and data transmission, reduces the quality of Solar sail spacecraft;
(7) slide block and wobble shaft stabilizing mechanism are used for gesture stability by the present invention, and the three-axis attitude that can realize Solar sail spacecraft controls, and can perform more wide in range task than spin stabilization gesture stability.
Accompanying drawing explanation
Fig. 1 is the Solar sail spacecraft structural representation under non-deployed condition;
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, and (b) is 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, and wherein (a) is schematic cross-section when hold-down arm launches, and (b) is schematic diagram when hold-down arm folds.
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 electronic devices and components are formed on deep space Solar sail spacecraft.
Fig. 2 is the deep space Solar sail spacecraft under deployed condition, describes the characteristic on sail face.Deep space Solar sail spacecraft mainly comprises four hold-down arms, 3, four pieces of sail faces 4, bracing frame 1, 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 root 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 two adjacent hold-down arms respectively.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 gesture stability function, and the detailed construction of slide block 9 is shown in Fig. 3.Slide block 9 includes the second solar battery sheet 14, first wireless communication module 15, can the remotely controlling exercise dolly 16 of remotely controlling exercise.Second solar battery sheet 14 and the first wireless communication module 15 are positioned on remotely controlling exercise dolly 16.Second solar battery sheet 14 is supplied to slide block 9 and moves the required energy.First wireless communication module 15 and satellite body carry out the mutual of data and instruction, and remotely controlling exercise dolly 16 is exported in the instruction of satellite body, remotely controlling exercise dolly 16 moves on hold-down arm 3 according to the instruction received, to adjust the centroid position of Solar sail spacecraft.The remotely controlling exercise dolly 16 of remotely controlling exercise can take the form that is sleeved on hold-down arm, that guarantees to move is stable and reliable.As shown in Figure 4, wobble shaft stabilizing mechanism 10 includes pull bar 17, the 3rd solar battery sheet 18, second wireless communication module 19, rotating mechanism 20, bracing frame 21 and sleeve 22.Wherein in Fig. 4, (a) is left view, and (b) is right elevation.Bracing frame 21 is made up of four pieces of stay bearing plates, and four pieces of stay bearing plates form square hollow structure.3rd solar battery sheet 18 and the second wireless communication module 19 are arranged on the stay bearing plate of bracing frame 21 sunny slope, rotating mechanism 20 is arranged on the stay bearing plate vertical with the stay bearing plate of sunny slope, and it is inner to be positioned at bracing frame 21, the turning cylinder of rotating mechanism 20 is connected with the center of pull bar 17, bracing frame 21 is arranged on sleeve 22, and sleeve 22 is adhesive in the top of hold-down arm 3; 3rd solar battery sheet 18 is supplied to rotating mechanism 20 and moves the required energy, second wireless communication module 19 and satellite body carry out the mutual of data and instruction, and rotational structure 20 is exported in the instruction of satellite body, rotational structure 20 can provide the rotating torque of positive and negative both direction according to instruction.Slide block and wobble shaft stabilizing mechanism are used for gesture stability, and the three-axis attitude that can realize Solar sail spacecraft controls.Meanwhile, the employing wireless communication technology decreases the use of communication line, makes large area Solar sail spacecraft various piece all can carry out communicating and data transmission, reduces the quality of Solar sail spacecraft.
The right-angled apices in 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.Substrate 12 is provided with the first solar battery sheet 5, coating 13 is etched with etching antenna 6 (low-gain antenna), as shown in Figure 5.The square edge length in sail face 4 is 160 meters.Substrate is the Kapton of thickness 1 micron-2 microns, and coating is the aluminium film of thickness 1000 dust.
Four isosceles right triangle sail faces 4 form one piece of square sail face, and the first solar battery sheet 5 is directly contained on the Kapton of square sail face, according to the folding mode piecemeal in 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 etching antenna 6 needs carry out etching at aluminium coated.Sail face can be laid multiple etching antenna to use as middle low-gain antenna, and redundancy each other.Four hold-down arms 3 are also laid 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 in non-deployed condition, four hold-down arms 3 are in folded state, and four pieces of isosceles right triangle sail faces 4 are also in folded state.Fig. 1 to lower the sail shape deep-space spacecraft for non-deployed condition.The non-deployed condition shape deep-space spacecraft that lowers the sail also comprises band 2, bracing frame 1 and band 2 play constraint and supporting role to the sail shape deep-space spacecraft under non-deployed condition in Spacecraft Launch process, and what utilize band 2 tightens the damage that function prevents to hold-down arm and sail face in emission process.Bracing frame 1 and band 2 adopt the aluminum honeycomb panel and titanium alloy strip that use in conventional satellite respectively.
The cross section of four hold-down arms is two Ω configurations, and employing has the carbon fiber composite material self-deploying performance and makes.One end of hold-down arm and the central support posts of bracing frame 1 pass through Flange joint.Expansion that can be controlled in order to ensure hold-down arm controls by adding nylon press strip 11 on hold-down arm, and nylon press strip 11 is along the symmetrical outside being bonded in housing 1 of center shaft of housing 1.Be squeezed into yi word pattern when hold-down arm folds, as shown in (b) in Fig. 7, be 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.
When Solar sail spacecraft launches, four hold-down arms 3 launch drive four pieces of isosceles right triangle sail faces 4 and launch.
After adopting said structure and component part, the pass between the quality of spacecraft and area is 200 kilograms, 25600 sq ms, and the required solar sail face amount ratio meeting survey of deep space requires.Spacecraft possesses necessary system and ability 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 thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; simple deduction or replace, all should be encompassed within protection scope of the present invention.
The content be not described in detail in specification sheets belongs to the known technology of those skilled in the art.
Claims (6)
1. utilize the power-actuated deep space Solar sail spacecraft of solar light pressure, it is characterized in that: comprise bracing frame (1), four hold-down arms (3), four pieces of 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 root 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 two adjacent hold-down arms respectively; Slide block (9) comprises the second solar battery sheet (14), the first wireless communication module (15) and remotely controlling exercise dolly (16), second solar battery sheet (14) and the first wireless communication module (15) are all positioned on remotely controlling exercise dolly (16), and remotely controlling exercise dolly (16) is enclosed within hold-down arm (3); Second solar battery sheet (14) is remotely controlling exercise dolly (16) power supply, first wireless communication module (15) and satellite body carry out the mutual of data and instruction, and remotely controlling exercise dolly (16) is exported in the instruction of satellite body, remotely controlling exercise dolly (16) above moves, to adjust the centroid position of Solar sail spacecraft at hold-down arm (3) according to the instruction received;
Wobble shaft stabilizing mechanism (10) comprises pull bar (17), 3rd solar battery sheet (18), second wireless communication module (19), rotating mechanism (20), second bracing frame (21) and sleeve (22), second bracing frame (21) is hollow structure, 3rd solar battery sheet (18) and the second wireless communication module (19) are arranged on the sunny slope of the second bracing frame (21), it is inner that rotating mechanism (20) is arranged on the second bracing frame (21), the turning cylinder of rotating mechanism (20) is connected with the center of pull bar (17), second bracing frame (21) is arranged on sleeve (22), sleeve (22) is adhesive in the top of hold-down arm (3), 3rd solar battery sheet (18) is rotating mechanism (20) power supply, second wireless communication module (19) and satellite body carry out the mutual of data and instruction, and rotating mechanism (20) is exported in the instruction of satellite body, rotating mechanism (20) can according to the instruction received for Solar sail spacecraft provides positive dirction or reciprocal rotating torque,
The right-angled apices 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, substrate (12) is provided with the first solar battery sheet (5), coating (13) is etched with etching antenna (6); First solar battery sheet (5) is symmetrical on the square sail face that four isosceles right triangle sail faces (4) form;
Described satellite body refers to the summation of the various unit that electronic devices and components are formed on deep space Solar sail spacecraft, and satellite body is positioned on bracing frame (1).
2. one according to claim 1 utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure, it is characterized in that: also comprise band (2), when Solar sail spacecraft is in non-deployed condition, band (2) is for tightening each device of Solar sail spacecraft, when 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. one according to claim 1 and 2 utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure, it is characterized in that: support frame as described above (1) adopts aluminum honeycomb panel to make.
4. one according to claim 1 and 2 utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure, it is characterized in that: described hold-down arm (3) is made up of carbon fiber composite material.
5. one according to claim 1 and 2 utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure, 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. one according to claim 1 and 2 utilizes the power-actuated deep space Solar sail spacecraft of solar light pressure, it is characterized in that: described hold-down arm (3) forms coating antenna by coating.
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Cited By (1)
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| CN109515752A (en) * | 2018-12-07 | 2019-03-26 | 上海宇航系统工程研究所 | A kind of deployable solar array and its compress relieving mechanism |
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